EP3988767A1 - Radial-flow gas turbine with supporting bearing - Google Patents
Radial-flow gas turbine with supporting bearing Download PDFInfo
- Publication number
- EP3988767A1 EP3988767A1 EP21203258.5A EP21203258A EP3988767A1 EP 3988767 A1 EP3988767 A1 EP 3988767A1 EP 21203258 A EP21203258 A EP 21203258A EP 3988767 A1 EP3988767 A1 EP 3988767A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bearing
- wing
- spring
- gas turbine
- axial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
- F05D2250/241—Three-dimensional ellipsoidal spherical
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
Definitions
- the invention relates to a radial gas turbine with (a) a turbine wheel and (b) a gas supply device for supplying a gas to the turbine wheel, which has (i) a first boundary plate, (ii) a second boundary plate, (iii) adjustable guide vanes between the first boundary plate and the second restriction plate, and (iv) a pitch mechanism for collectively rotating the guide vanes, (c) the guide vanes each having (i) a vane for directing the gas and (ii) a pitch axis for rotating the vane, and (iii ) are stored in a main bearing on the first boundary plate.
- Such radial gas turbines are often components of exhaust gas turbochargers.
- exhaust gas turbochargers are used in cylinder engines, for example in diesel or gasoline engines, usually in vehicles.
- the task of radial gas turbines is to extract energy from the inflowing gas flow, usually the exhaust gas flow. This energy is often used to compress charge air.
- gas supply devices are known. The guide vanes can be adjusted collectively by means of the adjusting device in such a way that the inflow onto the turbine wheel can be varied.
- a disadvantage of known radial gas turbines is that they have suboptimal efficiency compared to the maximum possible efficiency.
- One of the reasons for this is that comparatively large gaps have to be provided between the vanes and the boundary plates.
- the reason for this, in turn, is that vibrations and transverse forces that occur during operation of the radial gas turbine, as well as temperature fluctuations with corresponding component distortions, could otherwise lead to the blades becoming stiff and/or jamming. This can lead to significant wear and even destruction of the radial gas turbines.
- the object of the invention is to reduce the disadvantages of the prior art.
- the invention solves the problem by means of a generic radial gas turbine in which at least one guide vane is mounted in a support bearing on the second boundary plate and is prestressed against the second boundary plate by means of an axial spring.
- this radial gas turbine is that the at least one guide vane is mounted on two sides. This limits the tendency of the wings to tilt and minimizes the tolerance chains, so that smaller gaps between the wings and the limiter plates can be set. This in turn increases the efficiency of the radial gas turbine.
- the second bearing is usually comparatively less complex.
- the support bearing is not a roller bearing, that is, a bearing with roller bearing bodies.
- the bearing system consisting of a main bearing and a support bearing, is designed such that a force acting on the support bearing in the axial direction simultaneously has a force component acting radially inward, which acts on the adjustment axis in the area of the main bearing.
- the adjustment axis can wobble to a limited extent in the support bearing.
- a support bearing can usually be manufactured comparatively easily.
- such a support bearing is often robust and relatively insensitive to component distortions in the event of temperature fluctuations.
- the boundary plates are understood to mean those elements between which the guide vanes are arranged.
- the boundary plates are disc-shaped, which means that they have a larger dimension in two surface areas than in one area perpendicular to them.
- the delimiting plate it is possible, for example, for the delimiting plate to have projections which can be larger than the extension of the surface area.
- Guide vanes are devices that have a vane that is designed to conduct the gas.
- the wings preferably have an airfoil geometry. This means in particular that they are designed to divert the gas.
- the vanes are designed to vary an inflow direction under which the gas flows onto the turbine wheel.
- the boundary plates are preferably held together and/or positioned relative to one another by connecting elements.
- the support bearing has a concave bearing shell and a spherical cap that is accommodated in the bearing shell.
- the spherical cap is in particular a spherical structure.
- a cap is understood to mean a convexly curved section of a component.
- the spherical cap is a part of an object with a circular border.
- the bearing shell can be arranged on the second delimiting plate and the spherical cap on the adjustment axis of the wing or vice versa.
- the support bearing - as provided for in a preferred embodiment - a separate spherical element, namely a so-called Bearing ball, the second delimiting plate and the adjustment axis of the wing each have a bearing shell. If there is a bearing ball, it is preferably made of steel or ceramic.
- the radius of curvature of the bearing shell is at least as large as the radius of curvature of the bearing shell at the point at which the bearing shell and the bearing shell are in contact with one another.
- the spherical cap can preferably wobble in the bearing shell.
- a deflection of the adjustment axis from its desired position causes a restoring force, which can be achieved, for example, via parabolic geometries in the bearing shell and spherical cap.
- the axial spring is bent in a wave shape.
- This waveform is related to the radial component.
- the axial spring is curved in a wavy shape in cross section.
- the axial spring can be a plate spring, for example, which can have recesses.
- the axial spring has an outer ring to which the individual shaft elements are connected and have a rectangular or trapezoidal geometry. This also makes it possible to press the axial spring into the bore of the first delimiting plate.
- the shaft elements can also be connected via an inner ring, which can be fixed in the area of the adjustment axis of the guide vane.
- the axial spring is made of steel. It is particularly advantageous if the prestressed axial spring has a limited setting behavior at high temperatures above 800 °C and adapts to the counter-contour while maintaining a residual prestressing force, which can be done with suitable types of steel. This increases the surface contact and reduces the surface pressure, which has a favorable effect on wear. However, it is also possible to produce the axial spring from a different material.
- This bearing bush is preferably made of steel and/or ceramic. This enables optimization of the friction pairing.
- the ceramic is preferably zirconium oxide, since this has a similar coefficient of expansion as steel.
- the main bearing preferably has a disc element.
- This disk element supports the wing and prevents the wing from tilting too much.
- an end face of the disc element - connected or unconnected - on the wing It is possible that the end face is connected or not connected to the wing.
- the axial spring is arranged to press the disc element in the direction of the wing.
- the disc element it is possible, but not necessary, for the disc element to be movable relative to the wing.
- the axial spring is arranged to exert a spring force between the first delimiting plate and the support bearing.
- the axial spring is designed in such a way that a spring curve, which describes the dependency of a spring force on a deflection of the axial spring from a zero position, has a first section with a first spring constant and a second section with a second spring constant, with the first spring constant is less than the second spring constant.
- the axial tolerances of the components are compensated for by means of small forces and the spring force in the second section has the desired higher forces, so that a suitable restoring force is generated on the wing, which pushes the wing back towards the target position. This counteracts jamming of the wings.
- the first section runs from the beginning of the spring curve to the point at which the first derivative of the spring curve after the deflection has an inflection point. It is favorable if the axial spring is mounted in such a way that it is activated at low deflection, ie when the spring curve is in the first section a predetermined number of support points on an axial spring bearing structure. If the deflection becomes greater, then the axial spring rests against at least one further support point on the axial bearing spring structure, which means that the spring constant increases. In other words, the axial spring becomes harder.
- the first spring constant can be calculated, for example, from the straight line in the first section, the second spring constant from a second straight line through the second section.
- the axial spring preferably has an outer or inner axial spring ring and two or more axial spring elements are arranged on the axial spring ring.
- the disk element is preferably designed as a sealing disk which rests against the wing.
- This sealing washer is designed in particular in such a way that it reduces a gas flow past the side of the wing.
- the disk element has a sealing section which extends in the axial and circumferential direction and lengthens a gas flow path past the wing.
- the sealing section of the disk element acts like a labyrinth seal.
- the sealing section runs at least in sections and at least partially in the axial direction.
- the feature that the sealing section extends in the circumferential direction means in particular that it is at least predominantly designed to be continuous in the circumferential direction. In principle, it is possible for the sealing section to have gaps, but this generally leads to a lower sealing effect, which is why it is favorable if the disk element is largely continuous, in particular completely continuous, in the circumferential direction.
- the disc element preferably engages in a recess, in particular a circular one, in the first delimiting plate.
- the recess preferably has an outer contour which essentially corresponds to an outer contour of the disk element.
- the outer contour of the sealing disk is smaller by a small amount than the outer contour of the recess. The smaller the difference between the outer contour of the recesses and the outer contour of the sealing disc, the greater the flow resistance for gas that flows past the wing.
- the recess preferably also has a cylindrical border.
- the difference in the radii is preferably less than 10%, in particular less than 5%.
- the sealing washer preferably has an outer diameter of the sealing washer which is at least 50% larger than the diameter of the adjustment axis of the guide vane. A good sealing effect is thus achieved with a comparatively small diameter of the adjustment axis.
- the outer diameter of the sealing disk is at most 20% smaller than the inner diameter of the recess.
- the recess inner diameter is the diameter of the compensating circle through the edge of the recess. As described above, this leads to a good sealing effect.
- a rotation axis distance between two adjacent adjustment axis rotation axes is at most 1.5 times, preferably 1.2 times or less, the outer diameter of the sealing disk. This contributes to an increased sealing effect.
- the outer diameter of the sealing disk also exists if the sealing disk is not cylindrical in the strict mathematical sense. In this case it is the outside diameter of a perimeter.
- the circumcircle is the minimum diameter circle that can be placed around the cross section of the recesses.
- the disc element preferably has a collar towards the adjustment axis of the wing, which collar counteracts the tilting of the wing. It is advantageous if the collar has a greater axial height and thus forms a bearing bush at the same time.
- the bushing has a bushing collar of greater radial extent towards the vane, located within the circular recess of the first restriction plate is arranged. In other words, the collar of the bearing bush forms the disc element or the sealing disc.
- the bearing bushing collar of the bearing bushing is preferably arranged within the circular recess.
- the distance between the adjustment axis of the guide vane and the wing trailing edge of the wing is at least as large as the sealing disk radius. In other words, the trailing edge of the wing protrudes beyond the sealing disk or closes with it.
- the disk element in particular the sealing disk, has a wing support surface facing the wing and is connected to the wing in a rotationally fixed manner, the wing support surface having a local axial depression to prevent a collision with the wing trailing edge of the adjacent wing.
- the background to this preferred feature is that the trailing edge of the wing always hits the sealing washer of the adjacent guide vane at the same point when rotating back (closing rotation) from the maximum open position.
- the sealing disk preferably has the indentation and a ramp which rises in the direction of the closing rotation.
- the sealing washer preferably has an essentially circular outer contour. Under is to be understood in particular that a deviation from an ideal circular outer contour is preferably on average at most 10%, in particular at most 5%.
- the sum of the wing lengths of all guide vanes is preferably greater than the circumference on which the adjustment axes are arranged.
- the vanes are designed in such a way that the trailing edges of the vanes sweep over the adjacent sealing discs when the gas supply device is closed and/or (b) during the transition, when the trailing edges of the vanes move from the axial depression to the planar vane support surface, the Guide vanes and the sealing washers are collectively leveled.
- a first limiting plate thickness of the first limiting plate is at most 30%, in particular at most 20%, larger than a second limiting plate thickness of the second limiting plate and/or (b) a first limiting plate mass of the first limiting plate is at most 50%, in particular at most 20% larger as a second constraint plate mass of the second constraint plate.
- a sealing disk radius of the sealing disk in the area of a wing leading edge of the wing is larger than the average radius of the sealing disk.
- a radius means the ray that runs radially outwards from the axis of rotation of the turntable.
- a radius is also spoken of when the sealing washer is not strictly circular. Because the sealing washer radius in the area of the wing leading edge of the wing is larger than the average radius, the axial gap between the wing and the first boundary plate minimized and become.
- the sealing disk radius in the region of the leading edge of the wing corresponds at least essentially to a distance between the leading edge of the wing and the sealing disk.
- the relative deviation between the two is at most 10%, in particular at most 5%.
- a deviation of 0% would be ideal, but this is practically unattainable from a technical point of view.
- the seal radius equals the distance of the wing leading edge of the wing from the axis of rotation of the seal, and there is no gap between the wing and the seal for gas leakage to occur. This is particularly cheap.
- sealing disk radius of the sealing disk in the area of the leading edge of the wing is greater than the average radius of the sealing disk means in particular that this is present over an angular range of up to 25°.
- the wing has a more strongly curved upper side of the wing and a less curved lower side of the wing.
- the upper surface of the wing and the lower surface of the wing are separated by the chord of the wing.
- the angular range in which the sealing washer radius is greater than average is preferably on the wing top side.
- the adjustment device preferably has levers for rotating the guide vanes about their respective adjustment axis and also has a connecting ring, by means of which the levers are connected to one another without play.
- the levers are connected to the connecting ring with play. This has the disadvantage that the vibrations that occur during operation of the radial gas turbine due to the pulsating gas forces lead to wear between the connecting ring and the levers. However, the greater the play, the greater the wear. With increasing service life of the radial gas turbine, there is not only progressive wear, but also an increasing rate of wear, which is undesirable. Because the connecting ring is connected to the levers without play, Vibrations of the wings are greatly dampened or even suppressed. This reduces wear.
- a radial gas turbine of the generic type which has (a) levers for rotating the guide vanes about the adjustment axis and (b) a connecting ring, by means of which the levers are connected to one another without play.
- the connecting ring has spring sections between which the levers are clamped without play. This allows the connection ring to be connected to the levers without play, despite production-related tolerances.
- a preferred design has spring elements that are more rigid in the circumferential direction, i.e. in the direction of actuation, than in the radial direction.
- the higher spring constant in the circumferential direction than in the radial direction eliminates the vibrations that occur and the lower spring constant of the spring elements in the radial direction provides the desired flexibility when the point of application between the lever and spring element moves downwards or upwards from the central position when actuated.
- the connecting ring is open at the ends and is designed in the form of a loop there. This makes assembly easier. It is advantageous if the gas supply device has an actuating element that has two pin-shaped elements and engages with them in a form-fitting manner in the loops. It is then only necessary for assembly to introduce the pin-shaped elements into the loops in a form-fitting manner.
- the actuating element can have a holder and pin-shaped sections.
- the pin-shaped sections are preferably with the holder positively and/or non-positively connected.
- the pin-shaped sections can be designed in one piece as a U-part.
- the holder can have a holder slot into which the U-part engages in a positive and/or non-positive manner.
- the actuating element can have a holder and a U-part on which the pin-shaped sections are formed and which is positively connected to the holder.
- Such an actuator is particularly easy to manufacture and assemble.
- the dimensions or thickness and in particular the mass of the first delimiting plate is at most 30%, in particular at most 20%, greater than that of the second delimiting plate.
- the first delimiting plate is designed to be significantly stronger than the second delimiting plate, since the one-sided bearing of the guide vanes is arranged in the first delimiting plate and, for technical reasons, has a greater axial length.
- this has the disadvantage that different thermal expansions occur between the delimiting plates during heating and cooling, which leads to an offset of the delimiting plates and promotes jamming of the guide vanes.
- this is avoided by the support bearing, which makes it possible to design the main bearing to be compact in the axial direction.
- an exhaust gas turbocharger with an exhaust gas turbine according to the invention.
- a land vehicle in particular a passenger car or a truck, with an exhaust gas turbocharger according to the invention.
- Figure 1a shows a partially sectioned side view of a radial gas turbine 10 according to the invention with a turbine wheel 12 and a gas supply device 14.
- the gas supply device 14 can be used to direct gas 16 from a supply channel 18 to the turbine wheel 12 at different angles of attack.
- the guide vanes 24.i can be rotated collectively about a respective adjustment axis Ai by means of an adjustment device 26.
- Each vane 24.i has a wing 28.i (cf. Figure 1b ) for conducting the gas 16.
- the guide vanes 24.i are mounted on the first delimiting plate 20 in a respective main bearing 30.i.
- the first restricting plate 20 is arranged on a turbine shaft side with respect to a turbine shaft 32 , whereas the second restricting plate 22 has a greater distance from the turbine shaft 32 .
- Figure 1b shows a partially exploded view of the gas supply device 14 with connecting elements 23 and spherical bearings 40.
- the connecting elements position the limiting plates 20 and 22 relative to one another, have a shoulder and act as spacers. Spacers are cheap but not necessary.
- the boundary plates 20 and 22 can be held together as in Figure 1b Type shown take place directly via the connecting elements, for example via a rivet or indirectly via adjacent components.
- the masses of the delimiting plates are used to optimize the size, it also being the case that the mass deviation is preferably not more than 30%.
- Figure 2a shows a schematic view of the gas supply device 14, in which the support bearing 34 is also shown schematically.
- the guide vane 24 is prestressed against the second delimiting plate 22 by means of an axial spring.
- Figure 2b shows a further schematic cross-sectional view through a part of the gas supply device 14 according to a further embodiment.
- the support bearing 34 (reference numerals without a suffix refer to all corresponding objects) comprises a concave bearing shell 38 and a bearing cap 40 , with the bearing cap 40 being formed on a bearing ball 42 in the present case.
- the bearing ball 42 can be firmly connected to an adjustment axis 44 of the vane. Alternatively, it is accommodated in a second bearing shell 46 which is formed on the adjustment axis 44 .
- Figure 2b also shows that the main bearing 30 has a disk element 48, the end face 50 of which bears against the vane 28 and thermally shields the inner region of the main bearing 30 from the extremely hot gas flow 16, which protects the functionality of the axial spring.
- a disc element 48 made of ceramic, for example, provides excellent shielding effects.
- the limiting plates are positioned and held together by a connecting element 23 so that the axial spring 36 presses the bearing ball 42 into the bearing shell 38 .
- the connecting element 23 has shoulders as spacers, which is cheap but not necessary. It can be seen that the disc element has a ramp 52 so that the axial spring 36 exerts a radially inward centering force on the adjustment axis 44 when the latter is deflected from its desired position.
- Figure 2b also shows that the contour of the axial spring 36 and the contour of the disk element 48 are matched in the area of the ramp, which is particularly favored by a limited setting behavior of the axial spring.
- Figure 2c shows the axial spring 36 in a preferred design, which has a closed axial spring ring 37.1 as the outer ring, on which rectangular wave-shaped axial spring elements 37.2 are arranged.
- Figure 2d shows the axial spring 36 in the same preferred design as in FIG Figure 2c , in which the axial spring elements 37.2 have a trapezoidal shape, which has a harder spring characteristic.
- Figure 3a shows another part of a gas supply device 14, in which the disk element 48 is designed without a ramp and has a counter disk 49 with a collar. It can be seen that the axial spring 36 bears against the collar of the disk element 48 and the counter disk 49 in the circumferential direction, which leads to the increase in the spring rate.
- the thermal shielding of the axial spring is particularly favorable here if the disk element (48) and the counter disk (49) are made of well-insulating materials, for example ceramics
- Figure 3b shows another part of a gas supply device 14, in which the disk element 48 is designed as a sealing disk.
- this sealing disk has a sealing section 54 which extends in the axial direction.
- the sealing disc is accommodated in a recess 56, which preferably has a circular border. In other words, a cross section with respect to a plane perpendicular to the adjustment axis 44 is circular.
- the inner diameter of the recess D 56 is greater than the outer diameter of the sealing disk D 48 .
- Figure 3b also shows that the main bearing 30 has a bearing bushing 58 with a pronounced collar.
- the axial spring 36 presses the bearing bush against the disk element in the form of the sealing disk 48 via the collar, which in turn presses against the vane 28 .
- the axial spring 36 can be designed as a disk spring.
- Figure 3c shows the analog structure Figure 3b , wherein the sealing washer 48 is integrated into the vane 24, ie the vane 24 and sealing washer 48 form one part, the integrated sealing washer having a shoulder which protrudes into the recess 56.
- Figure 3d shows a guide vane 24 with an integrated sealing disk 48 as a one-piece component according to FIG Figure 3c .
- Figure 4a shows a schematic sectional view in relation to a plane perpendicular to the adjustment axis 44.1.
- the sealing disks 48 are arranged flush, taking into account a minimum distance, ie the possible continuous radius of the sealing disks has a maximum value. Starting from the wing leading edge in the opening direction, a circle segment can be seen that has a larger radius r than the continuous radius rd and completely covers the wing leading edge, i.e. the radius r corresponds to the distance between the tip of the wing leading edge and the center of the Adjustment axis 44 of guide vane 24.
- the sealing disks 48 are arranged in recesses 56 in the first delimiting plate 20, the recess similar to the sealing disk also locally having a larger radius than the continuous radius.
- the circular segment of the recess 56 with the larger radius is dimensioned in such a way that no collision between the sealing disk and the recess occurs over the permissible angle of rotation ⁇ .
- the sealing disk radius r can depend on a rotation angle ⁇ , but this is not necessary.
- Figure 4a 12 shows the position of the vanes with the blade trailing edges 62 positioned just prior to an overlap with the sealing washer 48.
- FIG. If the angle of rotation ⁇ changes in the closing direction, the trailing edge 62.i of the wing begins to sweep over the adjacent sealing disk 48.i-1.
- the sealing disk 48 locally has a recess 64 which is designed with a continuous transition as a type of wing support surface 66 .
- Figure 4a shows that the sealing disk 48 has a substantially circular outer contour.
- the recess 56 in the first delimiting plate 20 also has an essentially circular inner contour.
- Figure 4b shows an example of a way to connect the sealing disk 48 in a rotationally fixed manner to the wing, which is favorable for the under Figure 4a described advantageous functionality of the sealing disk in interaction with the wing, ie that the wing trailing edge 62 always comes into contact with the adjacent sealing disk at the same point.
- the sealing disk 48 has a pin on the side facing the wing, which engages in a pin bore 70 of the wing 28 .
- the reverse design with a pin on the wing side or the use of a separate component in the form of a pin is also conceivable, which then engages in bores in the wing and the sealing disk.
- Figure 4c Figure 12 shows the position of the vanes where all vanes 28 and washers 48 are engaged and collectively aligned, which is particularly beneficial for uniform and narrow gaps. It can also be seen that this favorable position is half-open to closed, which is particularly advantageous for efficiency.
- Figure 5a shows that the adjustment device 26 has a lever 76.i for each guide vane 24.i, by means of which the guide vane 24.i can be rotated about the respective adjustment axis 44.i.
- the levers 76.i are connected to one another without play by means of a connecting ring 78.
- Each lever 76.i is clamped resiliently without play between two spring sections 80a.i, 80b.i.
- All spring sections 80a.i, 80b.i are integrally formed on a connecting web 82, preferably on two connecting webs. It is possible, but not necessary, for the spring sections to be formed in one piece on the connecting ring; other fastening options, for example insertion, are also possible.
- Figure 5a also shows an actuating element 84, by means of which, when rotated about its actuating axis, the movement via the connecting ring 78 in the circumferential direction is transmitted simultaneously to all levers 76.i and all levers can thus be actuated simultaneously.
- the actuating axis which in the present case belongs to the scope of parts of the actuator (not shown), engages in an axis bore 85 of the actuating element 84 and is connected here in a rotationally fixed manner, for example by welding. It is also conceivable that the actuation axis is part of the actuation element 84 . It can also be seen that the actuating element 84 engages in the ends of the connecting ring 78, which are designed as loops 92 for this purpose. As can be seen, the connecting ring 78 is not firmly connected at the ends, which can be advantageous in terms of manufacturing technology. However, a fixed connection of the ends of the connecting ring is also possible, which results in greater rigidity.
- Figure 5b shows the actuating element 84, which preferably has a holder 86 with two pin-shaped elements 90 and an axle bore 85 for receiving the actuating axle. It is particularly favorable to design the two pin-shaped elements in one piece as a U-part 88 on which a first section 90.1 and a second section 90.2 are formed.
- the U-part 88 is accommodated in a slot 87 of the holder 86, preferably in a form-fitting manner, for example by means of a press fit.
- Sections 90.1, 90.2 engage in loops 92.1, 92.2 and thus cause the connecting ring 82 to close with a positive fit.
- Figure 5c shows a particularly advantageous design of the connecting ring 78, in which the spring sections 80 have the desired different spring constants in the circumferential direction and in the radial direction, such that the spring sections 80 have a higher spring constant in the circumferential direction than in the radial direction.
- Figure 1b 12 shows that the first constraint plate 20 has a first constraint plate thickness d 20 .
- the second constraint plate 22 has a second constraint plate thickness d 22 . If the boundary plates 20, 22 are not disc-shaped, as in the present case, then a compensating cylinder is used to determine the thicknesses d 20 , d 22 used, in which 90% of the mass of the respective boundary plate 20 or 22 is added.
- the plate thicknesses d 20 , d 22 preferably deviate from one another by at most 30%.
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Abstract
Die Erfindung betrifft eine Radialgasturbine (10) mit einem Turbinenrad (12) und einer Gaszuleitvorrichtung (14) zum Zuleiten eines Gases (16) zum Turbinenrad (12), die eine erste Begrenzungsplatte (20), eine zweite Begrenzungsplatte (22), verstellbare Leitschaufeln (24), die zwischen der ersten Begrenzungsplatte (20) und der zweiten Begrenzungsplatte (22) angeordnet sind, und eine Verstellvorrichtung (26) zum kollektiven Drehen der Leitschaufeln (24) aufweist, wobei die Leitschaufeln (24) jeweils einen Flügel (28) zum Leiten des Gases (16) und eine Verstellachse (44) zum Drehen des Flügels (28) aufweisen und in einem Hauptlager (30) an der ersten Begrenzungsplatte (20) gelagert sind. Erfindungsgemäß ist vorgesehen, dass zumindest eine Leitschaufel (24) in einem Stützlager an der zweiten Begrenzungsplatte (22) gelagert ist und mittels einer Axialfeder (36) gegen die zweite Begrenzungsplatte (22) vorgespannt ist.The invention relates to a radial gas turbine (10) with a turbine wheel (12) and a gas supply device (14) for supplying a gas (16) to the turbine wheel (12), which has a first boundary plate (20), a second boundary plate (22), adjustable guide vanes (24) arranged between the first restriction plate (20) and the second restriction plate (22), and an adjusting device (26) for rotating the guide vanes (24) collectively, the guide vanes (24) each having a vane (28) for directing the gas (16) and an adjustment axis (44) for rotating the vane (28) and are mounted in a main bearing (30) on the first restriction plate (20). According to the invention, at least one guide vane (24) is mounted in a support bearing on the second delimiting plate (22) and is prestressed against the second delimiting plate (22) by means of an axial spring (36).
Description
Die Erfindung betrifft eine Radialgasturbine mit (a) einem Turbinenrad und (b) einer Gaszuleitvorrichtung zum Zuleiten eines Gases zum Turbinenrad, die (i) eine erste Begrenzungsplatte, (ii) eine zweite Begrenzungsplatte, (iii) verstellbare Leitschaufeln, die zwischen der ersten Begrenzungsplatte und der zweiten Begrenzungsplatte angeordnet sind, und (iv) eine Verstellvorrichtung zum kollektiven Drehen der Leitschaufeln aufweist, (c) wobei die Leitschaufeln jeweils (i) einen Flügel zum Leiten des Gases und (ii) eine Verstellachse zum Drehen des Flügels aufweisen und (iii) in einem Hauptlager an der ersten Begrenzungsplatte gelagert sind.The invention relates to a radial gas turbine with (a) a turbine wheel and (b) a gas supply device for supplying a gas to the turbine wheel, which has (i) a first boundary plate, (ii) a second boundary plate, (iii) adjustable guide vanes between the first boundary plate and the second restriction plate, and (iv) a pitch mechanism for collectively rotating the guide vanes, (c) the guide vanes each having (i) a vane for directing the gas and (ii) a pitch axis for rotating the vane, and (iii ) are stored in a main bearing on the first boundary plate.
Derartige Radialgasturbinen sind häufig Bestandteile von Abgasturboladern. Abgasturbolader wiederum werden in Zylindermotoren eingesetzt, beispielsweise in Diesel oder Benzinmotoren, in der Regel in Fahrzeugen. Die Aufgabe der Radialgasturbinen ist es, dem einströmenden Gasstrom, in der Regel dem Abgasstrom, Energie zu entziehen. Oft wird diese Energie zum Verdichten von Ladeluft verwendet. Um die Leistungsabgabe des Turbinenrads steuern oder regeln zu können, sind Gaszuleitvorrichtungen bekannt. Die Leitschaufeln sind mittels der Verstellvorrichtung kollektiv so verstellbar, dass die Anströmung des Turbinenrades variiert werden kann.Such radial gas turbines are often components of exhaust gas turbochargers. In turn, exhaust gas turbochargers are used in cylinder engines, for example in diesel or gasoline engines, usually in vehicles. The task of radial gas turbines is to extract energy from the inflowing gas flow, usually the exhaust gas flow. This energy is often used to compress charge air. In order to be able to control or regulate the power output of the turbine wheel, gas supply devices are known. The guide vanes can be adjusted collectively by means of the adjusting device in such a way that the inflow onto the turbine wheel can be varied.
Nachteilig an bekannten Radialgasturbinen ist, dass sie im Vergleich zum maximal möglichen Wirkungsgrad einen suboptimalen Wirkungsgrad haben. Einer der Gründe dafür ist, dass zwischen den Flügeln und den Begrenzungsplatten vergleichsweise große Spalte vorgesehen werden müssen. Der Grund dafür wiederum ist, dass beim Betrieb der Radialgasturbine auftretende Schwingungen und Querkräfte sowie Temperaturschwankungen mit entsprechenden Bauteilverzügen andernfalls dazu führen könnten, dass die Flügel schwergängig werden und/oder sich verklemmen. Das kann zu erheblichem Verschleiß bis zur Zerstörung der Radialgasturbinen führen.A disadvantage of known radial gas turbines is that they have suboptimal efficiency compared to the maximum possible efficiency. One of the reasons for this is that comparatively large gaps have to be provided between the vanes and the boundary plates. The reason for this, in turn, is that vibrations and transverse forces that occur during operation of the radial gas turbine, as well as temperature fluctuations with corresponding component distortions, could otherwise lead to the blades becoming stiff and/or jamming. This can lead to significant wear and even destruction of the radial gas turbines.
Es ist ein weiterer Nachteil, dass die maximale Temperatur, die das Gas haben kann, bei Dieselmotoren in der Regel bei ca. 800°C liegt. Bei deutlich höheren Temperaturen, die insbesondere bei Benzinmotoren auftreten, verlieren selbst hochfeste Stähle deutlich an Festigkeit. Dazu kommt, dass Bauteile aus Stahl, die relativ zu einem anderen Bauteil bewegbar sein müssen, hohe Reibkoeffizienten zu diesen aufweisen und zum "Verkleben" mit diesen neigen. Beides führt zu hohem Verschleiß oder zur direkten Zerstörung der Radialgasturbine.Another disadvantage is that the maximum temperature that the gas can have is usually around 800°C in diesel engines. At significantly higher temperatures, which occur in particular in petrol engines, even high-strength steels lose significantly in strength. In addition, components made of steel, which must be able to move relative to another component, have high coefficients of friction with them and tend to "stick" to them. Both lead to high wear or direct destruction of the radial gas turbine.
Der Erfindung liegt die Aufgabe zugrunde, Nachteile im Stand der Technik zu vermindern.The object of the invention is to reduce the disadvantages of the prior art.
Die Erfindung löst das Problem durch eine gattungsgemäße Radialgasturbine, bei der zumindest eine Leitschaufel in einem Stützlager an der zweiten Begrenzungsplatte gelagert ist und mittels einer Axialfeder gegen die zweite Begrenzungsplatte vorgespannt ist.The invention solves the problem by means of a generic radial gas turbine in which at least one guide vane is mounted in a support bearing on the second boundary plate and is prestressed against the second boundary plate by means of an axial spring.
Vorteilhaft an dieser Radialgasturbine ist, dass die zumindest eine Leitschaufel zweiseitig gelagert ist. Das begrenzt die Kippneigung der Flügel und minimiert die Toleranzketten, sodass kleinere Spalte zwischen den Flügeln und den Begrenzungsplatten eingestellt werden können. Dieses wiederum erhöht den Wirkungsgrad der Radialgasturbine.What is advantageous about this radial gas turbine is that the at least one guide vane is mounted on two sides. This limits the tendency of the wings to tilt and minimizes the tolerance chains, so that smaller gaps between the wings and the limiter plates can be set. This in turn increases the efficiency of the radial gas turbine.
Vorteilhaft ist zudem, dass die zweite Lagerung meist vergleichsweise wenig aufwändig ist. Insbesondere handelt es sich bei dem Stützlager nicht um ein Wälzlager, das heißt, ein Lager mit Wälzlagerkörpern. Insbesondere ist das Lagersystem, bestehend aus Hauptlager und Stützlager, so ausgebildet, dass eine in axialer Richtung auf das Stützlager wirkende Kraft gleichzeitig eine radial einwärts wirkenden Kraftkomponente aufweist, die auf die Verstellachse im Bereich des Hauptlagers wirkt.It is also advantageous that the second bearing is usually comparatively less complex. In particular, the support bearing is not a roller bearing, that is, a bearing with roller bearing bodies. In particular, the bearing system, consisting of a main bearing and a support bearing, is designed such that a force acting on the support bearing in the axial direction simultaneously has a force component acting radially inward, which acts on the adjustment axis in the area of the main bearing.
In anderen Worten kann die Verstellachse im Stützlager begrenzt taumeln. Ein derartiges Stützlager kann in der Regel vergleichsweise einfach gefertigt werden. Zudem ist ein derartiges Stützlager häufig robust und gegen Bauteilverzüge bei Temperaturschwankungen relativ unempfindlich.In other words, the adjustment axis can wobble to a limited extent in the support bearing. Such a support bearing can usually be manufactured comparatively easily. In addition, such a support bearing is often robust and relatively insensitive to component distortions in the event of temperature fluctuations.
Im Rahmen der vorliegenden Beschreibung werden unter den Begrenzungsplatten diejenigen Elemente verstanden, zwischen denen die Leitschaufeln angeordnet sind. In der Regel sind die Begrenzungsplatten scheibenförmig, das heißt, dass sie in zwei Flächenausdehnungen eine größere Abmessung besitzen, als in einer Ausdehnung senkrecht dazu. Es ist aber beispielsweise möglich, dass die Begrenzungsplatte Vorsprünge aufweist, die größer sein können als die Ausdehnung der Flächenerstreckung.Within the scope of the present description, the boundary plates are understood to mean those elements between which the guide vanes are arranged. As a rule, the boundary plates are disc-shaped, which means that they have a larger dimension in two surface areas than in one area perpendicular to them. However, it is possible, for example, for the delimiting plate to have projections which can be larger than the extension of the surface area.
Unter den Leitschaufeln werden Vorrichtungen verstanden, die einen Flügel aufweisen, der zum Leiten des Gases ausgebildet ist. Die Flügel weisen vorzugsweise eine Tragflächengeometrie auf. Das heißt insbesondere, dass sie ausgebildet sind zum Umleiten des Gases. Insbesondere sind die Flügel zum Variieren einer Anströmrichtung gestaltet, unter der das Gas auf das Turbinenrad strömt.Guide vanes are devices that have a vane that is designed to conduct the gas. The wings preferably have an airfoil geometry. This means in particular that they are designed to divert the gas. In particular, the vanes are designed to vary an inflow direction under which the gas flows onto the turbine wheel.
Die Begrenzungsplatten werden vorzugsweise von Verbindungselementen zusammengehalten und/oder zueinander positioniert. Alternativ ist eine Positionierung der zweiten Begrenzungsplatte über die gelagerten Leitschaufeln und/oder ein indirektes Zusammenhalten der Begrenzungsplatten über an die Gaszuleitvorrichtung angrenzende Bauteile möglich. In diesem Fall ist die Gaszuleitungsvorrichtung zwischen angrenzenden Bauteilen eingespannt.The boundary plates are preferably held together and/or positioned relative to one another by connecting elements. Alternatively, it is possible to position the second delimiting plate via the mounted guide vanes and/or hold the delimiting plates together indirectly via components adjoining the gas supply device. In this case, the gas supply device is clamped between adjacent components.
Gemäß einer bevorzugten Ausführungsform weist das Stützlager eine konkave Lagerschale und eine Lagerkalotte auf, die in der Lagerschale aufgenommen ist. Bei der Lagerkalotte handelt es sich insbesondere um ein kugelförmiges Gebilde. Unter einer Kalotte wird ein konvex gekrümmter Abschnitt eines Bauteils verstanden. Insbesondere handelt es sich bei der Lagerkalotte um einen kreisförmig berandeten Teil eines Objekts. Die Lagerschale kann an der zweiten Begrenzungsplatte und die Lagerkalotte an der Verstellachse des Flügels oder umgekehrt angeordnet sein.According to a preferred embodiment, the support bearing has a concave bearing shell and a spherical cap that is accommodated in the bearing shell. The spherical cap is in particular a spherical structure. A cap is understood to mean a convexly curved section of a component. In particular, the spherical cap is a part of an object with a circular border. The bearing shell can be arranged on the second delimiting plate and the spherical cap on the adjustment axis of the wing or vice versa.
Besitzt das Stützlager - wie gemäß einer bevorzugten Ausführungsform vorgesehen ― ein separates kugelförmiges Element, nämlich eine sogenannte Lagerkugel, so weisen die zweite Begrenzungsplatte sowie die Verstellachse des Flügels jeweils eine Lagerschale auf. Ist eine Lagerkugel vorhanden, ist diese vorzugsweise aus Stahl oder Keramik gefertigt.Does the support bearing - as provided for in a preferred embodiment - a separate spherical element, namely a so-called Bearing ball, the second delimiting plate and the adjustment axis of the wing each have a bearing shell. If there is a bearing ball, it is preferably made of steel or ceramic.
Der Krümmungsradius der Lagerschale ist zumindest so groß wie der Krümmungsradius der Lagerkalotte in dem Punkt, in dem die Lagerschale und die Lagerkalotte in Kontakt miteinander stehen.The radius of curvature of the bearing shell is at least as large as the radius of curvature of the bearing shell at the point at which the bearing shell and the bearing shell are in contact with one another.
Die Lagerkalotte kann vorzugsweise in der Lagerschale taumeln. Besonders bevorzugt bewirkt eine Auslenkung der Verstellachse aus ihrer Soll-Lage eine Rückstellkraft, die beispielsweise über parabelförmige Geometrien bei Lagerschale und Lagerkalotte erreicht werden kann.The spherical cap can preferably wobble in the bearing shell. Particularly preferably, a deflection of the adjustment axis from its desired position causes a restoring force, which can be achieved, for example, via parabolic geometries in the bearing shell and spherical cap.
Günstig ist es, wenn die Axialfeder wellenförmig gebogen ist. Diese Wellenform bezieht sich auf die Radialkomponente. In anderen Worten ist die Axialfeder im Querschnitt wellenförmig gebogen. Die Axialfeder kann beispielsweise eine Tellerfeder sein, die Ausnehmungen aufweisen kann. gemäß einer bevorzugten Ausführungsform besitzt die Axialfeder einen Außenring, an dem die einzelnen Wellenelemente angebunden sind und eine rechteckige bzw. trapezförmige Geometrie aufweisen. Dies ermöglicht auch, die Axialfeder in die Bohrung der ersten Begrenzungsplatte einzupressen. Alternativ ist die Anbindung der Wellenelemente auch über einen Innenring möglich, der im Bereich der Verstellachse der Leitschaufel fixiert werden kann.It is favorable if the axial spring is bent in a wave shape. This waveform is related to the radial component. In other words, the axial spring is curved in a wavy shape in cross section. The axial spring can be a plate spring, for example, which can have recesses. according to a preferred embodiment, the axial spring has an outer ring to which the individual shaft elements are connected and have a rectangular or trapezoidal geometry. This also makes it possible to press the axial spring into the bore of the first delimiting plate. Alternatively, the shaft elements can also be connected via an inner ring, which can be fixed in the area of the adjustment axis of the guide vane.
Günstig ist es, wenn die Axialfeder aus Stahl gefertigt ist. Besonders vorteilhaft ist es, wenn die vorgespannte Axialfeder bei hohen Temperaturen über 800 °C ein begrenztes Setzverhalten aufweist und sich der Gegenkontur anpasst unter Beibehaltung einer restlichen Vorspannkraft, was mit geeigneten Stahlsorten machbar ist. Dadurch wird der Flächenkontakt erhöht und die Flächenpressung verringert, was sich auf den Verschleiß günstig auswirkt. Es ist aber auch möglich, die Axialfeder aus einem anderen Material herzustellen.It is favorable if the axial spring is made of steel. It is particularly advantageous if the prestressed axial spring has a limited setting behavior at high temperatures above 800 °C and adapts to the counter-contour while maintaining a residual prestressing force, which can be done with suitable types of steel. This increases the surface contact and reduces the surface pressure, which has a favorable effect on wear. However, it is also possible to produce the axial spring from a different material.
Günstig ist es, wenn das Hauptlager eine Lagerbuchse aufweist. Bei hohen Temperaturen kann es bei ungünstigen Materialpaarungen leicht zu Lagerschäden kommen. Von daher ist eine Lagerung in einer Lagerbuchse besonders günstig. Diese Lagerbuchse ist vorzugsweise aus Stahl und/oder aus Keramik gefertigt. Das ermöglicht eine Optimierung der Reibpaarung. Bei der Keramik handelt es sich vorzugsweise um Zirkonoxid, da dieses einen ähnlichen Ausdehnungskoeffizienten wie Stahl hat.It is favorable if the main bearing has a bearing bush. At high temperatures, unfavorable material pairings can easily lead to bearing damage come. Therefore, storage in a bearing bush is particularly favorable. This bearing bush is preferably made of steel and/or ceramic. This enables optimization of the friction pairing. The ceramic is preferably zirconium oxide, since this has a similar coefficient of expansion as steel.
Vorzugsweise weißt das Hauptlager ein Scheibenelement auf. Dieses Scheibenelement stützt den Flügel und verhindert ein zu starkes Kippen des Flügels. Vorzugsweise liegt eine Stirnfläche des Scheibenelements - verbunden oder unverbunden - am Flügel an. Es ist möglich, dass die Stirnfläche verbunden oder unverbunden am Flügel anliegt.The main bearing preferably has a disc element. This disk element supports the wing and prevents the wing from tilting too much. Preferably, an end face of the disc element - connected or unconnected - on the wing. It is possible that the end face is connected or not connected to the wing.
Günstig ist es, wenn die Axialfeder zum Drücken des Scheibenelements in Richtung auf den Flügel zu angeordnet ist. Insbesondere ist es möglich, nicht aber notwendig, dass das Scheibenelement relativ zum Flügel bewegbar ist.It is favorable if the axial spring is arranged to press the disc element in the direction of the wing. In particular, it is possible, but not necessary, for the disc element to be movable relative to the wing.
Günstig ist es, wenn die Axialfeder angeordnet ist zum Ausüben einer Federkraft zwischen der ersten Begrenzungsplatte und dem Stützlager.It is favorable if the axial spring is arranged to exert a spring force between the first delimiting plate and the support bearing.
Besonders günstig ist es, wenn die Axialfeder so ausgebildet ist, dass eine Federkurve, die die Abhängigkeit einer Federkraft von einer Auslenkung der Axialfeder aus einer Nullstellung beschreibt, einen ersten Abschnitt mit einer ersten Federkonstanten und einen zweiten Abschnitt mit einer zweiten Federkonstanten hat, wobei die erste Federkonstante kleiner ist als die zweite Federkonstante. Das führt dazu, dass die axialen Toleranzen der Bauteile mittels kleiner Kräfte ausgeglichen werden und die Federkraft im zweiten Abschnitt die gewünschten höheren Kräfte aufweist, sodass eine geeignete Rückstellkraft auf den Flügel entsteht, die den Flügel in Richtung auf die Soll-Lage zurückdrückt. Das wirkt einem Verklemmen der Flügel entgegen.It is particularly favorable if the axial spring is designed in such a way that a spring curve, which describes the dependency of a spring force on a deflection of the axial spring from a zero position, has a first section with a first spring constant and a second section with a second spring constant, with the first spring constant is less than the second spring constant. As a result, the axial tolerances of the components are compensated for by means of small forces and the spring force in the second section has the desired higher forces, so that a suitable restoring force is generated on the wing, which pushes the wing back towards the target position. This counteracts jamming of the wings.
Der erste Abschnitt verläuft insbesondere vom Anfang der Federkurve bis zu dem Punkt, an dem die erste Ableitung der Federkurve nach der Auslenkung einen Wendepunkt hat. Günstig ist es, wenn die Axialfeder so montiert ist, dass sie bei geringer Auslenkung, also dann, wenn die Federkurve im ersten Abschnitt ist, an einer vorgegebenen Anzahl an Stützstellen an einer Axialfederlagerstruktur anliegt. Wird die Auslenkung größer, so liegt die Axialfeder an zumindest einer weiteren Stützstelle an der Axiallagerfederstruktur an, was dazu führt, dass die Federkonstante zunimmt. Die Axialfeder wird in anderen Worten härter.In particular, the first section runs from the beginning of the spring curve to the point at which the first derivative of the spring curve after the deflection has an inflection point. It is favorable if the axial spring is mounted in such a way that it is activated at low deflection, ie when the spring curve is in the first section a predetermined number of support points on an axial spring bearing structure. If the deflection becomes greater, then the axial spring rests against at least one further support point on the axial bearing spring structure, which means that the spring constant increases. In other words, the axial spring becomes harder.
Die erste Federkonstante kann beispielsweise aus der Ausgleichsgeraden im ersten Abschnitt berechnet werden, die zweite Federkonstante aus einer zweiten Ausgleichsgeraden durch den zweiten Abschnitt.The first spring constant can be calculated, for example, from the straight line in the first section, the second spring constant from a second straight line through the second section.
Vorzugsweise weist die Axialfeder einen Außen- oder Innen-Axialfeder-Ring auf und zwei oder mehr Axialfeder-Elemente sind an dem Axialfeder-Ring angeordnet.The axial spring preferably has an outer or inner axial spring ring and two or more axial spring elements are arranged on the axial spring ring.
Vorzugsweise ist das Scheibenelement als Dichtscheibe ausgebildet, die am Flügel anliegt. Diese Dichtscheibe ist insbesondere so ausgebildet, dass sie einen Gasfluss seitlich am Flügel vorbei vermindert.The disk element is preferably designed as a sealing disk which rests against the wing. This sealing washer is designed in particular in such a way that it reduces a gas flow past the side of the wing.
Günstig ist es, wenn das Scheibenelement einen Dichtabschnitt aufweist, der sich in Axial- und in Umfangs-Richtung erstreckt und ein Strömungspfad vom Gas am Flügel vorbei verlängert. In anderen Worten wirkt der Dichtabschnitt des Scheibenelements wie eine Labyrinth-Dichtung. Der Dichtabschnitt verläuft zumindest abschnittsweise und zumindest teilweise in axialer Richtung. Unter dem Merkmal, dass der Dichtabschnitt sich in Umfangs-Richtung erstreckt, wird insbesondere verstanden, dass er in Umfangs-Richtung zumindest überwiegend durchgängig ausgebildet ist. Grundsätzlich ist es möglich, dass der Dichtabschnitt Lücken aufweist, das aber führt in der Regel zu einer geringeren Dichtwirkung, weshalb es günstig ist, wenn das Scheibenelement in Umfangs-Richtung weitgehend durchgängig, insbesondere komplett durchgängig, ist.It is favorable if the disk element has a sealing section which extends in the axial and circumferential direction and lengthens a gas flow path past the wing. In other words, the sealing section of the disk element acts like a labyrinth seal. The sealing section runs at least in sections and at least partially in the axial direction. The feature that the sealing section extends in the circumferential direction means in particular that it is at least predominantly designed to be continuous in the circumferential direction. In principle, it is possible for the sealing section to have gaps, but this generally leads to a lower sealing effect, which is why it is favorable if the disk element is largely continuous, in particular completely continuous, in the circumferential direction.
Das Scheibenelement greift vorzugsweise in eine, insbesondere kreisförmige, Ausnehmung in der ersten Begrenzungsplatte ein. Vorzugsweise hat die Ausnehmung eine Außenkontur, die einer Außenkontur des Scheibenelements im Wesentlichen entspricht. Insbesondere ist die Außenkontur der Dichtscheibe um einen kleinen Betrag kleiner als die Außenkontur der Ausnehmung. Je geringer der Unterschied zwischen der Außenkontur der Ausnehmungen und der Außenkontur der Dichtscheibe, umso größer ist der Strömungswiderstand für Gas, das am Flügel vorbei strömt.The disc element preferably engages in a recess, in particular a circular one, in the first delimiting plate. The recess preferably has an outer contour which essentially corresponds to an outer contour of the disk element. In particular, the outer contour of the sealing disk is smaller by a small amount than the outer contour of the recess. The smaller the difference between the outer contour of the recesses and the outer contour of the sealing disc, the greater the flow resistance for gas that flows past the wing.
Ist die Dichtscheibe zylinderförmig berandet, so ist die Ausnehmung vorzugsweise ebenfalls zylinderförmig berandet. Der Unterschied in den Radien ist vorzugsweise kleiner als 10%, insbesondere kleiner als 5%.If the sealing disc has a cylindrical border, the recess preferably also has a cylindrical border. The difference in the radii is preferably less than 10%, in particular less than 5%.
Vorzugsweise hat die Dichtscheibe einen Dichtscheiben-Außendurchmesser, der zumindest 50% größer ist als der Durchmesser der Verstellachse der Leitschaufel. So wird bei vergleichsweise kleinem Durchmesser der Verstellachse eine gute Abdichtwirkung erreicht.The sealing washer preferably has an outer diameter of the sealing washer which is at least 50% larger than the diameter of the adjustment axis of the guide vane. A good sealing effect is thus achieved with a comparatively small diameter of the adjustment axis.
Günstig ist es, wenn der Dichtscheiben-Außendurchmesser höchstens 20% kleiner ist als ein Ausnehmungs-Innendurchmesser der Ausnehmung. Der Ausnehmungs-Innendurchmesser ist der Durchmesser des Ausgleichskreises durch den Rand der Ausnehmung. Wie oben beschrieben, führt das zu einer guten Dichtwirkung.It is favorable if the outer diameter of the sealing disk is at most 20% smaller than the inner diameter of the recess. The recess inner diameter is the diameter of the compensating circle through the edge of the recess. As described above, this leads to a good sealing effect.
Günstig ist es, wenn ein Drehachsen-Abstand zwischen zwei benachbarten Verstellachsen-Drehachsen höchstens das 1,5-fache, bevorzugt das 1,2-fache oder weniger, des Dichtscheiben-Außendurchmessers beträgt. Das trägt zu einer erhöhten Dichtwirkung bei.It is favorable if a rotation axis distance between two adjacent adjustment axis rotation axes is at most 1.5 times, preferably 1.2 times or less, the outer diameter of the sealing disk. This contributes to an increased sealing effect.
Es sei darauf hingewiesen, dass der Dichtscheiben-Außendurchmesser auch dann existiert, wenn die Dichtscheibe nicht im streng mathematischen Sinne zylinderförmig berandet ist. In diesem Fall handelt es sich um den Außendurchmesser eines Umkreises. Der Umkreis ist derjenige Kreis minimalen Durchmessers, der um den Querschnitt der Ausnehmungen gelegt werden kann.It should be noted that the outer diameter of the sealing disk also exists if the sealing disk is not cylindrical in the strict mathematical sense. In this case it is the outside diameter of a perimeter. The circumcircle is the minimum diameter circle that can be placed around the cross section of the recesses.
Vorzugsweise weist das Scheibenelement zur Verstellachse des Flügels hin einen Kragen auf, der dem Kippen des Flügels entgegenwirkt. Vorteilhaft ist, wenn der Kragen eine größere axiale Höhe aufweist und so gleichzeitig eine Lagerbuchse bildet. Eine gleichwertige Beschreibung ist, dass die Lagerbuchse einen Lagerbuchsenkragen mit größerer radialer Ausdehnung in Richtung Flügel aufweist, der innerhalb der kreisförmigen Ausnehmung der ersten Begrenzungsplatte angeordnet ist. Mit anderen Worten bildet der Kragen der Lagerbuchse das Scheibenelement bzw. die Dichtscheibe.The disc element preferably has a collar towards the adjustment axis of the wing, which collar counteracts the tilting of the wing. It is advantageous if the collar has a greater axial height and thus forms a bearing bush at the same time. An equivalent description is that the bushing has a bushing collar of greater radial extent towards the vane, located within the circular recess of the first restriction plate is arranged. In other words, the collar of the bearing bush forms the disc element or the sealing disc.
Vorzugsweise ist der Lagerbuchsenkragen der Lagerbuchse innerhalb der kreisförmigen Ausnehmung angeordnet ist.The bearing bushing collar of the bearing bushing is preferably arranged within the circular recess.
Vorzugsweise gilt für zumindest eine Mehrzahl der Leitschaufeln, insbesondere für alle Leitschaufeln, dass der Abstand zwischen Verstellachse der Leitschaufel und Flügel-Abströmkante des Flügels zumindest so groß ist wie der Dichtscheibenradius. In anderen Worten steht die Flügel-Abströmkante über die Dichtscheibe über oder schließt mit dieser ab.It is preferably the case for at least a majority of the guide vanes, in particular for all guide vanes, that the distance between the adjustment axis of the guide vane and the wing trailing edge of the wing is at least as large as the sealing disk radius. In other words, the trailing edge of the wing protrudes beyond the sealing disk or closes with it.
Günstig ist es, wenn das Scheibenelement, insbesondere die Dichtscheibe, eine dem Flügel zugewandte Flügelträgerfläche hat und mit dem Flügel drehfest verbunden ist, wobei die Flügelträgerfläche eine örtliche axiale Vertiefung zum Verhindern einer Kollision mit der Flügel-Abströmkante des benachbarten Flügels aufweist. Der Hintergrund zu diesem bevorzugten Merkmal ist, dass die Flügel-Abströmkante beim Zurückdrehen (Schließdrehung) aus der maximalen Öffnungslage die Dichtscheibe der benachbarten Leitschaufel immer an der gleichen Stelle trifft. An dieser Stelle hat die Dichtscheibe vorzugsweise die Vertiefung und eine Rampe, die in Richtung Schließdrehung ansteigt. Damit wird verhindert, dass, im Falle von Schiefstellungen benachbarter Leitschaufeln und trotz sehr kleiner Spalte kein Aufeinandertreffen von Kanten sondern ein Einfädeln der Flügel-Abströmkante in die benachbarte Dichtscheibe und ein kollisionsfreies gleichmäßiges Ausrichten der benachbarten Leitschaufeln über Rampen erfolgt. Besonders vorteilhaft ist, dass schon bei einem kleinen Schließwinkel nach dem Einfädeln ein perfekt ausgerichtetes System von Leitschaufeln entsteht, das minimale und gleichmäßige Spalte zwischen den Begrenzungsplatten aufweist.It is favorable if the disk element, in particular the sealing disk, has a wing support surface facing the wing and is connected to the wing in a rotationally fixed manner, the wing support surface having a local axial depression to prevent a collision with the wing trailing edge of the adjacent wing. The background to this preferred feature is that the trailing edge of the wing always hits the sealing washer of the adjacent guide vane at the same point when rotating back (closing rotation) from the maximum open position. At this point, the sealing disk preferably has the indentation and a ramp which rises in the direction of the closing rotation. This prevents, in the event of misalignment of adjacent guide vanes and despite a very small gap, that the edges do not meet, but that the trailing edge of the wing threads into the adjacent sealing disk and a collision-free, even alignment of the adjacent guide vanes via ramps takes place. It is particularly advantageous that even with a small closing angle after threading, a perfectly aligned system of guide vanes is created, which has minimal and even gaps between the limiting plates.
Besonders günstig ist, dass ein perfekt ausgerichtetes System von Leitschaufeln mit minimalen Spalten bei geringen, bis mittleren Öffnungswinkeln vorliegt, da diesen Bereichen für den Wirkungsgrad besondere Bedeutung zukommt.It is particularly favorable that there is a perfectly aligned system of guide vanes with minimal gaps at low to medium opening angles, since these areas are of particular importance for efficiency.
Vorzugsweise hat die Dichtscheibe eine im Wesentlichen kreisförmige Außenkontur. Herunter ist insbesondere zu verstehen, dass eine Abweichung von einer idealen kreisförmigen Außenkontur vorzugsweise im Mittel höchstens 10%, insbesondere höchstens 5% beträgt.The sealing washer preferably has an essentially circular outer contour. Under is to be understood in particular that a deviation from an ideal circular outer contour is preferably on average at most 10%, in particular at most 5%.
Um einen guten Wirkungsgrad zu erzielen, ist die Summe der Flügellängen aller Leitschaufeln vorzugsweise größer als der Kreisumfang auf dem die Verstellachsen angeordnet sind. Das hat zur Folge, dass, auch wenn die Dichtscheiben einen maximalen Durchmesser ausweisen und sich ohne Spalte aneinanderreihen, die Enden der Flügel über die Dichtscheiben hinausragen. Dies ist insbesondere im Bereich der Flügel-Anströmkante ungünstig, da Spalte an dieser Stelle für den Wirkungsgrad besonders nachteilig sind.In order to achieve good efficiency, the sum of the wing lengths of all guide vanes is preferably greater than the circumference on which the adjustment axes are arranged. As a result, even if the sealing disks have a maximum diameter and line up without gaps, the ends of the wings protrude beyond the sealing disks. This is particularly unfavorable in the area of the leading edge of the wing, since gaps at this point are particularly disadvantageous for the efficiency.
Vorzugsweise sind (a) die Flügel so ausgebildet, dass die Flügel-Abströmkanten der Flügel beim Schließen der Gaszuleitvorrichtung die benachbarten Dichtscheiben überstreichen und/oder (b) beim Übergang, wenn sich die Flügel-Abströmkanten von der axialen Vertiefung zur ebenen Flügelträgerfläche bewegen, die Leitschaufeln und die Dichtscheiben kollektiv eben ausgerichtet werden.Preferably, (a) the vanes are designed in such a way that the trailing edges of the vanes sweep over the adjacent sealing discs when the gas supply device is closed and/or (b) during the transition, when the trailing edges of the vanes move from the axial depression to the planar vane support surface, the Guide vanes and the sealing washers are collectively leveled.
Gemäß einer bevorzugten Ausführungsform ist (a) eine Erstbegrenzungsplattendicke der ersten Begrenzungsplatte höchstens 30%, insbesondere höchstens 20%, größer als eine Zweitbegrenzungsplattendicke der zweiten Begrenzungsplatte und/oder (b) eine Erstbegrenzungsplattenmasse der ersten Begrenzungsplatte höchstens 50%, insbesondere höchstens 20%, größer als eine Zweitbegrenzungsplattenmasse der zweiten Begrenzungsplatte.According to a preferred embodiment, (a) a first limiting plate thickness of the first limiting plate is at most 30%, in particular at most 20%, larger than a second limiting plate thickness of the second limiting plate and/or (b) a first limiting plate mass of the first limiting plate is at most 50%, in particular at most 20% larger as a second constraint plate mass of the second constraint plate.
Günstig ist es, wenn ein Dichtscheiben-Radius der Dichtscheibe im Bereich einer Flügel-Anströmkante des Flügels größer ist als der durchschnittliche Radius der Dichtscheibe. Wenn in diesem Fall von einem Radius gesprochen wird, so ist damit der Strahl gemeint, der von der Drehachse der Drehscheibe nach radial auswärts verläuft. Insbesondere wird auch dann von einem Radius gesprochen, wenn die Dichtscheibe nicht im strengen Sinne kreisförmig ist. Dadurch, dass der Dichtscheiben-Radius im Bereich der Flügel-Anströmkante des Flügels größer ist als der durchschnittliche Radius, kann die axiale Lücke zwischen dem Flügel und der ersten Begrenzungsplatte minimiert und werden. Insbesondere ist es möglich und bevorzugt, dass der Dichtscheiben-Radius im Bereich der Flügel-Anströmkante zumindest im Wesentlichen einen Abstand der Flügel-Anströmkante von der Dichtscheibe entspricht. In anderen Worten ist die relative Abweichung zwischen beiden höchstens 10%, insbesondere höchstens 5%. Ideale wäre eine Abweichung von 0%, was aber technisch quasi nicht erreichbar ist. Bei 0% Abweichung entspricht der Dichtscheiben-Radius dem Abstand der Flügel-Anströmkante des Flügels von der Drehachse der Dichtscheibe, und es existiert keine Lücke zwischen dem Flügel und der Dichtscheibe, durch die ein Gas-Leckstrom treten könnte. Dies ist besonders günstig.It is favorable if a sealing disk radius of the sealing disk in the area of a wing leading edge of the wing is larger than the average radius of the sealing disk. When speaking of a radius in this case, it means the ray that runs radially outwards from the axis of rotation of the turntable. In particular, a radius is also spoken of when the sealing washer is not strictly circular. Because the sealing washer radius in the area of the wing leading edge of the wing is larger than the average radius, the axial gap between the wing and the first boundary plate minimized and become. In particular, it is possible and preferred that the sealing disk radius in the region of the leading edge of the wing corresponds at least essentially to a distance between the leading edge of the wing and the sealing disk. In other words, the relative deviation between the two is at most 10%, in particular at most 5%. A deviation of 0% would be ideal, but this is practically unattainable from a technical point of view. At 0% deviation, the seal radius equals the distance of the wing leading edge of the wing from the axis of rotation of the seal, and there is no gap between the wing and the seal for gas leakage to occur. This is particularly cheap.
Unter dem Merkmal, dass der Dichtscheiben-Radius der Dichtscheibe im Bereich der Flügel-Anströmkante größer ist als der durchschnittliche Radius der Dichtscheibe wird insbesondere verstanden, dass dies über einen Winkelbereich von bis zu 25° vorliegt.The feature that the sealing disk radius of the sealing disk in the area of the leading edge of the wing is greater than the average radius of the sealing disk means in particular that this is present over an angular range of up to 25°.
Günstig ist es, wenn der Flügel eine stärker gekrümmte Tragflächenoberseite und eine weniger gekrümmte Tragflächenunterseite aufweist. Die Tragflächenoberseite und die Tragflächenunterseite sind durch die Sehne des Flügels voneinander getrennt. Der Winkelbereich, in den der Dichtscheiben-Radius größer ist als im Durchschnitt, liegt vorzugsweise auf der Seite der Tragflächenoberseite.It is favorable if the wing has a more strongly curved upper side of the wing and a less curved lower side of the wing. The upper surface of the wing and the lower surface of the wing are separated by the chord of the wing. The angular range in which the sealing washer radius is greater than average is preferably on the wing top side.
Vorzugsweise besitzt die Verstellvorrichtung Hebel zum Drehen der Leitschaufeln um ihre jeweilige Verstellachse und besitzt zudem einen Verbindungsring, mittels dem die Hebel spielfrei miteinander verbunden sind. Bei bisherigen Radialgasturbinen, insbesondere bei bestehenden Abgasturboladern, sind die Hebel mit Spiel mit dem Verbindungsring verbunden. Das hat den Nachteil, dass die beim Betrieb der Radialgasturbine auftretenden Schwingungen durch die pulsierenden Gaskräfte zu einem Verschleiß zwischen Verbindungsring und Hebeln führen. Je größer aber das Spiel ist, desto stärker ist der Verschleiß. Es kommt damit mit zunehmenden Einsatzdauer der Radialgasturbine nicht nur zu fortschreitendem Verschleiß, sondern auch zu einer zunehmenden Verschleißgeschwindigkeit, was unerwünscht ist. Dadurch, dass der Verbindungsring spielfrei mit den Hebeln verbunden ist, können Schwingungen der Flügel stark gedämpft oder sogar unterdrückt werden. Das vermindert den Verschleiß.The adjustment device preferably has levers for rotating the guide vanes about their respective adjustment axis and also has a connecting ring, by means of which the levers are connected to one another without play. In previous radial gas turbines, in particular in existing exhaust gas turbochargers, the levers are connected to the connecting ring with play. This has the disadvantage that the vibrations that occur during operation of the radial gas turbine due to the pulsating gas forces lead to wear between the connecting ring and the levers. However, the greater the play, the greater the wear. With increasing service life of the radial gas turbine, there is not only progressive wear, but also an increasing rate of wear, which is undesirable. Because the connecting ring is connected to the levers without play, Vibrations of the wings are greatly dampened or even suppressed. This reduces wear.
Erfindungsgemäß ist zudem eine gattungsgemäße Radialgasturbine, die (a) Hebel zum Drehen der Leitschaufeln um die Verstellachse und (b) einen Verbindungsring, mittels dem die Hebel spielfrei miteinander verbunden sind, aufweist. Die oben und im Folgenden genannten bevorzugten Ausführungsformen gelten für diesen und den weiter oben genannten Aspekt der Erfindung.According to the invention is also a radial gas turbine of the generic type, which has (a) levers for rotating the guide vanes about the adjustment axis and (b) a connecting ring, by means of which the levers are connected to one another without play. The preferred embodiments mentioned above and below apply to this and the above-mentioned aspect of the invention.
Günstig ist es, wenn der Verbindungsring Federabschnitte aufweist, zwischen denen die Hebel spielfrei geklemmt sind. Das erlaubt es, den Verbindungsring trotz fertigungsbedingter Toleranzen spielfrei mit den Hebeln zu verbinden.It is favorable if the connecting ring has spring sections between which the levers are clamped without play. This allows the connection ring to be connected to the levers without play, despite production-related tolerances.
Günstig ist es, wenn die Federabschnitte mit einem Verbindungssteg und/oder einem Ringkörper des Verbindungsrings verbunden sind, insbesondere einstückig verbunden sind. Ein derartiger Verbindungsring ist kostengünstig herstellbar. Eine bevorzugte Bauform weist Federelemente auf, die in Umfangsrichtung, d.h. in Betätigungsrichtung, eine größere Steifigkeit als in radialer Richtung haben. Die höhere Federkonstante in Umfangsrichtung als in radialer Richtung eliminiert die auftretenden Schwingungen und die kleinere Federkonstante der Federelemente in radialer Richtung liefert die gewünschte Nachgiebigkeit, wenn der Angriffspunkt zwischen Hebel und Federelement bei Betätigung ausgehend von der zentralen Position nach unten bzw. nach oben wandert.It is favorable if the spring sections are connected to a connecting web and/or an annular body of the connecting ring, in particular are connected in one piece. Such a connecting ring can be produced inexpensively. A preferred design has spring elements that are more rigid in the circumferential direction, i.e. in the direction of actuation, than in the radial direction. The higher spring constant in the circumferential direction than in the radial direction eliminates the vibrations that occur and the lower spring constant of the spring elements in the radial direction provides the desired flexibility when the point of application between the lever and spring element moves downwards or upwards from the central position when actuated.
Gemäß einer bevorzugten Ausführungsform ist der Verbindungsring an den Enden offen und dort schlaufenförmig ausgebildet. Das erleichtert die Montage. Günstig ist es dann nämlich, wenn die Gaszuleitvorrichtung ein Betätigungselement aufweist, das zwei stiftförmige Elemente hat und mit diesen formschlüssig in die Schlaufen eingreift. Es ist dann zur Montage lediglich notwendig, die stiftförmigen Elemente formschlüssig in die Schlaufen einzubringen.According to a preferred embodiment, the connecting ring is open at the ends and is designed in the form of a loop there. This makes assembly easier. It is advantageous if the gas supply device has an actuating element that has two pin-shaped elements and engages with them in a form-fitting manner in the loops. It is then only necessary for assembly to introduce the pin-shaped elements into the loops in a form-fitting manner.
Besonders günstig ist es, wenn das Betätigungselement mehrteilig, insbesondere zweiteilig, ausgebildet ist. Das Betätigungselement kann einen Halter und stiftförmige Abschnitte aufweisen. Die stiftförmigen Abschnitte sind vorzugsweise mit dem Halter form- und/oder kraftschlüssig verbunden. Die stiftförmigen Abschnitte können einstückig als U-Teil ausgebildet sein. Der Halter kann ein Halter-Langloch aufweisen, in den das U-Teil form-/ und/oder kraftschlüssig eingreift.It is particularly favorable if the actuating element is designed in several parts, in particular in two parts. The actuating element can have a holder and pin-shaped sections. The pin-shaped sections are preferably with the holder positively and/or non-positively connected. The pin-shaped sections can be designed in one piece as a U-part. The holder can have a holder slot into which the U-part engages in a positive and/or non-positive manner.
Das Betätigungselement kann einen Halter und ein U-Teil aufweisen, an dem die stiftförmigen Abschnitte ausgebildet sind und das formschlüssig mit dem Halter verbunden ist. Ein derartiges Betätigungselement ist besonders leicht zu fertigen und zu montieren.The actuating element can have a holder and a U-part on which the pin-shaped sections are formed and which is positively connected to the holder. Such an actuator is particularly easy to manufacture and assemble.
Günstig ist es, wenn die Abmaße bzw. Dicke und insbesondere die Masse der ersten Begrenzungsplatte höchstens 30%, insbesondere höchstens 20%, größer ist als die der zweiten Begrenzungsplatte. Bei bekannten Radialgasturbinen ist die erste Begrenzungsplatte deutlich stärker ausgebildet als die zweite Begrenzungsplatte, da in der ersten Begrenzungsplatte das einseitige Lager der Leitschaufeln angeordnet ist, das technisch bedingt eine größere axiale Länge aufweist. Das aber hat den Nachteil, dass es zu unterschiedlichen thermischen Ausdehnungen zwischen den Begrenzungsplatten beim Aufheizen und Abkühlen kommt, was zu einem Versatz der Begrenzungsplatten führt und ein Verklemmen der Leitschaufeln befördert. Bei der erfindungsgemäßen Radialgasturbine wird das durch das Stützlager vermieden, die es ermöglicht, das Hauptlager in axialer Richtung kompakt auszuführen.It is favorable if the dimensions or thickness and in particular the mass of the first delimiting plate is at most 30%, in particular at most 20%, greater than that of the second delimiting plate. In known radial gas turbines, the first delimiting plate is designed to be significantly stronger than the second delimiting plate, since the one-sided bearing of the guide vanes is arranged in the first delimiting plate and, for technical reasons, has a greater axial length. However, this has the disadvantage that different thermal expansions occur between the delimiting plates during heating and cooling, which leads to an offset of the delimiting plates and promotes jamming of the guide vanes. In the radial gas turbine according to the invention, this is avoided by the support bearing, which makes it possible to design the main bearing to be compact in the axial direction.
Erfindungsgemäß ist zudem ein Abgasturbolader mit einer erfindungsgemäßen Abgasturbine. Ebenfalls erfindungsgemäß ist ein Landfahrzeug, insbesondere ein Personenkraftwagen oder ein Lastkraftwagen, mit einem erfindungsgemäßen Abgasturbolader.Also according to the invention is an exhaust gas turbocharger with an exhaust gas turbine according to the invention. Also according to the invention is a land vehicle, in particular a passenger car or a truck, with an exhaust gas turbocharger according to the invention.
Im Folgenden wird die Erfindung anhand der beigefügten Zeichnungen näher erläutert. Dabei zeigt
- Figur 1a
- eine erfindungsgemäße Radialgasturbine als Teil eines erfindungsgemäßen Abgasturboladers,
- Figur 1b
- eine Explosionsansicht der Gaszuleitvorrichtung der Radialgasturbine gemäß
Figur 1a , - Figur 2a
- einen schematischen Querschnitt durch eine Leitschaufel mit einem Stützlager und einer Axialfeder,
- Figur 2b
- eine detailliertere Querschnittsansicht durch eine Leitschaufel einer erfindungsgemäßen Radialgasturbine, in der eine Axialfeder, ein Scheibenelement und eine Lagerkugel zu sehen ist,
- Figur 2c
- eine Ausführungsform der erfindungsgemäßen Axialfeder mit Außenring und rechteckförmigen Federelementen in zwei Ansichten und
- Figur 2d
- eine Ausführungsform der erfindungsgemäßen Axialfeder mit Außenring und trapezförmigen Federelementen in der Draufsicht und
- Figur 3a
- einen Querschnitt durch eine weitere Ausführungsform einer Gaszuleitvorrichtung einer erfindungsgemäßen Radialgasturbine,
- Figur 3b
- eine weitere Ausführungsform einer erfindungsgemäßen Gaszuleitvorrichtung einer erfindungsgemäßen Radialgasturbine,
Figur 3c- eine weitere Ausführungsform einer erfindungsgemäßen Gaszuleitvorrichtung einer erfindungsgemäßen Radialgasturbine,
- Figur 3d
- Leitschaufel mit integrierter Dichtscheibe,
- Figur 4a
- eine schematische Querschnittsansicht auf eine Ebene senkrecht zur Verstellachse mit einer ersten Verdrehposition der Flügel,
- Figur 4b
- eine Leitschaufel und eine Dichtscheibe mit Verdrehsicherung,
- Figur 4c
- eine schematische Querschnittsansicht auf eine Ebene senkrecht zur Verstellachse mit einer zweiten Verdrehposition der Flügel
- Figur 5a
- einen Verbindungsring einer erfindungsgemäßen Radialgasturbine und
- Figur 5b
- eine dreidimensionale Ansicht eines Betätigungselements einer Gaszuleitvorrichtung einer erfindungsgemäßen Radialgasturbine und
- Figur 5c
- eine weitere Bauform eines Verbindungsringes.
- Figure 1a
- a radial gas turbine according to the invention as part of an exhaust gas turbocharger according to the invention,
- Figure 1b
- an exploded view of the gas supply device of the radial gas turbine according to FIG
Figure 1a , - Figure 2a
- a schematic cross section through a vane with a support bearing and an axial spring,
- Figure 2b
- a more detailed cross-sectional view through a vane of a radial gas turbine according to the invention, in which an axial spring, a disk element and a bearing ball can be seen,
- Figure 2c
- an embodiment of the axial spring according to the invention with an outer ring and rectangular spring elements in two views and
- Figure 2d
- an embodiment of the axial spring according to the invention with an outer ring and trapezoidal spring elements in plan view and
- Figure 3a
- a cross section through a further embodiment of a gas supply device of a radial gas turbine according to the invention,
- Figure 3b
- a further embodiment of a gas supply device according to the invention of a radial gas turbine according to the invention,
- Figure 3c
- a further embodiment of a gas supply device according to the invention of a radial gas turbine according to the invention,
- Figure 3d
- guide vane with integrated sealing washer,
- Figure 4a
- a schematic cross-sectional view on a plane perpendicular to Adjustment axis with a first twisting position of the wings,
- Figure 4b
- a guide vane and a sealing washer with anti-twist device,
- Figure 4c
- a schematic cross-sectional view on a plane perpendicular to the adjustment axis with a second twisted position of the wings
- Figure 5a
- a connecting ring of a radial gas turbine according to the invention and
- Figure 5b
- a three-dimensional view of an actuating element of a gas supply device of a radial gas turbine according to the invention and
- Figure 5c
- another type of connecting ring.
Jede Leitschaufel 24.i besitzt einen Flügel 28.i (vgl.
Die Leitschaufeln 24.i sind in einem jeweiligen Hauptlager 30.i an der ersten Begrenzungsplatte 20 gelagert. Die erste Begrenzungsplatte 20 ist auf einer turbinenwelligen Seite bezüglich einer Turbinenwelle 32 angeordnet, wohingegen die zweite Begrenzungsplatte 22 einen größeren Abstand von der Turbinenwelle 32 hat.The guide vanes 24.i are mounted on the first delimiting
Im Detailbild links ist zu erkennen, dass die Leitschaufeln 24.i, im vorliegenden Fall die Leitschaufel 24.4, in einem jeweiligen Stützlager 34.i gelagert ist.In the detailed image on the left it can be seen that the guide vanes 24.i, in the present case the guide vane 24.4, is mounted in a respective support bearing 34.i.
Sind die Begrenzungsplatten 20, 22 nicht wie im vorliegenden Fall scheibenförmig, so werden die Massen der Begrenzungsplatten zur Größenoptimierung herangezogen, wobei analog gilt, dass die Massenabweichung vorzugsweise nicht mehr als 30% beträgt.If the delimiting
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Citations (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3910716A (en) * | 1974-05-23 | 1975-10-07 | Westinghouse Electric Corp | Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement |
US4050844A (en) * | 1976-06-01 | 1977-09-27 | United Technologies Corporation | Connection between vane arm and unison ring in variable area stator ring |
JPS6314843U (en) * | 1986-07-14 | 1988-01-30 | ||
JPS6361545U (en) * | 1986-10-09 | 1988-04-23 | ||
JPS6415704U (en) * | 1987-07-17 | 1989-01-26 | ||
DE19523287A1 (en) * | 1994-06-28 | 1996-01-04 | Usui Kokusai Sangyo K Ltd | Connection arrangement for connecting a branch element to a high-pressure fuel rail |
DE19959017C1 (en) * | 1999-12-08 | 2000-12-21 | Daimler Chrysler Ag | Exhaust gas turbocharger for i.c. engine has guide grid ring with adjustable guide vanes and cooperating sealing discs used for providing variable radial turbine geometry |
DE10311205B3 (en) * | 2003-03-14 | 2004-09-16 | Man B & W Diesel Ag | Guiding device for a radial turbine of a turbocharger of a lifting piston I.C. engine operating with heavy oil has blades with shafts positioned in a housing part of the device facing a compressor of the turbocharger |
WO2004099573A1 (en) * | 2003-05-08 | 2004-11-18 | Honeywell International Inc. | Turbocharger with a variable nozzle device |
EP1561007A1 (en) * | 2002-11-15 | 2005-08-10 | Honeywell International, Inc. | Variable nozzle for turbocharger |
EP1895106A1 (en) * | 2006-08-28 | 2008-03-05 | ABB Turbo Systems AG | Sealing of variable guide vanes |
DE102008005658A1 (en) * | 2008-01-23 | 2009-07-30 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | loader |
DE102008020932A1 (en) * | 2008-04-25 | 2009-10-29 | Continental Automotive Gmbh | Turbocharger, particularly for motor vehicle, has variable turbine geometry unit and one or multiple fastening elements for fastening variable turbine geometry unit in housing of turbocharger |
EP2199570A2 (en) * | 2008-12-20 | 2010-06-23 | Bosch Mahle Turbo Systems GmbH & Co. KG | Charging device |
EP2215340A1 (en) * | 2007-11-28 | 2010-08-11 | Continental Automotive GmbH | Heat shield and turbocharger having a heat shield |
DE102009012065A1 (en) * | 2009-03-06 | 2010-09-09 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device, in particular for a motor vehicle, with a variable turbine geometry |
EP2236773A2 (en) * | 2009-03-11 | 2010-10-06 | General Electric Company | Variable stator vane contoured button |
JP2012167640A (en) * | 2011-02-16 | 2012-09-06 | Ihi Corp | Turbocharger |
DE102011085703A1 (en) * | 2011-11-03 | 2013-05-08 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Variable turbine or compressor geometry for output control of charging device, particularly exhaust gas turbocharger, comprises spring assembly, which causes permanent, backlash free contact between adjusting lever and adjusting ring |
US20130216361A1 (en) * | 2012-02-22 | 2013-08-22 | Propheter-Hinckley Tracy A | Vane assembly for a gas turbine engine |
EP2960461A1 (en) * | 2013-02-21 | 2015-12-30 | Mitsubishi Heavy Industries, Ltd. | Variable capacity exhaust turbine |
DE102015222598A1 (en) * | 2014-11-21 | 2016-05-25 | Borgwarner Inc. | VARIABLE TURBINE GEOMETRY SHOVEL WITH SINGLE-AXIS, SELF-CENTERING SWIVEL FEATURE |
JP2017067033A (en) * | 2015-10-01 | 2017-04-06 | 株式会社豊田自動織機 | Turbocharger |
EP3315729A1 (en) * | 2016-10-26 | 2018-05-02 | MTU Aero Engines GmbH | Ellipsoidal internal guide vane bearing |
DE112016004635T5 (en) * | 2015-10-07 | 2018-08-16 | Ihi Corporation | VALVE MECHANISM WITH VARIABLE FLOW RATE AND TURBOCHARGER |
WO2019049873A1 (en) * | 2017-09-11 | 2019-03-14 | いすゞ自動車株式会社 | Variable nozzle turbocharger |
CN108730025B (en) * | 2018-03-26 | 2019-08-06 | 北京理工大学 | A kind of turbocharger with end-clearance-free adjustable nozzle ring blade assembly |
-
2021
- 2021-10-18 EP EP21203258.5A patent/EP3988767A1/en not_active Withdrawn
- 2021-10-18 DE DE202021004007.2U patent/DE202021004007U1/en active Active
Patent Citations (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3910716A (en) * | 1974-05-23 | 1975-10-07 | Westinghouse Electric Corp | Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement |
US4050844A (en) * | 1976-06-01 | 1977-09-27 | United Technologies Corporation | Connection between vane arm and unison ring in variable area stator ring |
JPS6314843U (en) * | 1986-07-14 | 1988-01-30 | ||
JPS6361545U (en) * | 1986-10-09 | 1988-04-23 | ||
JPS6415704U (en) * | 1987-07-17 | 1989-01-26 | ||
DE19523287A1 (en) * | 1994-06-28 | 1996-01-04 | Usui Kokusai Sangyo K Ltd | Connection arrangement for connecting a branch element to a high-pressure fuel rail |
DE19959017C1 (en) * | 1999-12-08 | 2000-12-21 | Daimler Chrysler Ag | Exhaust gas turbocharger for i.c. engine has guide grid ring with adjustable guide vanes and cooperating sealing discs used for providing variable radial turbine geometry |
EP1561007A1 (en) * | 2002-11-15 | 2005-08-10 | Honeywell International, Inc. | Variable nozzle for turbocharger |
DE10311205B3 (en) * | 2003-03-14 | 2004-09-16 | Man B & W Diesel Ag | Guiding device for a radial turbine of a turbocharger of a lifting piston I.C. engine operating with heavy oil has blades with shafts positioned in a housing part of the device facing a compressor of the turbocharger |
WO2004099573A1 (en) * | 2003-05-08 | 2004-11-18 | Honeywell International Inc. | Turbocharger with a variable nozzle device |
EP1895106A1 (en) * | 2006-08-28 | 2008-03-05 | ABB Turbo Systems AG | Sealing of variable guide vanes |
EP2215340A1 (en) * | 2007-11-28 | 2010-08-11 | Continental Automotive GmbH | Heat shield and turbocharger having a heat shield |
DE102008005658A1 (en) * | 2008-01-23 | 2009-07-30 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | loader |
DE102008020932A1 (en) * | 2008-04-25 | 2009-10-29 | Continental Automotive Gmbh | Turbocharger, particularly for motor vehicle, has variable turbine geometry unit and one or multiple fastening elements for fastening variable turbine geometry unit in housing of turbocharger |
EP2199570A2 (en) * | 2008-12-20 | 2010-06-23 | Bosch Mahle Turbo Systems GmbH & Co. KG | Charging device |
DE102009012065A1 (en) * | 2009-03-06 | 2010-09-09 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device, in particular for a motor vehicle, with a variable turbine geometry |
EP2236773A2 (en) * | 2009-03-11 | 2010-10-06 | General Electric Company | Variable stator vane contoured button |
JP2012167640A (en) * | 2011-02-16 | 2012-09-06 | Ihi Corp | Turbocharger |
DE102011085703A1 (en) * | 2011-11-03 | 2013-05-08 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Variable turbine or compressor geometry for output control of charging device, particularly exhaust gas turbocharger, comprises spring assembly, which causes permanent, backlash free contact between adjusting lever and adjusting ring |
US20130216361A1 (en) * | 2012-02-22 | 2013-08-22 | Propheter-Hinckley Tracy A | Vane assembly for a gas turbine engine |
EP2960461A1 (en) * | 2013-02-21 | 2015-12-30 | Mitsubishi Heavy Industries, Ltd. | Variable capacity exhaust turbine |
DE102015222598A1 (en) * | 2014-11-21 | 2016-05-25 | Borgwarner Inc. | VARIABLE TURBINE GEOMETRY SHOVEL WITH SINGLE-AXIS, SELF-CENTERING SWIVEL FEATURE |
JP2017067033A (en) * | 2015-10-01 | 2017-04-06 | 株式会社豊田自動織機 | Turbocharger |
DE112016004635T5 (en) * | 2015-10-07 | 2018-08-16 | Ihi Corporation | VALVE MECHANISM WITH VARIABLE FLOW RATE AND TURBOCHARGER |
EP3315729A1 (en) * | 2016-10-26 | 2018-05-02 | MTU Aero Engines GmbH | Ellipsoidal internal guide vane bearing |
WO2019049873A1 (en) * | 2017-09-11 | 2019-03-14 | いすゞ自動車株式会社 | Variable nozzle turbocharger |
CN108730025B (en) * | 2018-03-26 | 2019-08-06 | 北京理工大学 | A kind of turbocharger with end-clearance-free adjustable nozzle ring blade assembly |
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