EP2071134A2 - Turbine with variable geometry - Google Patents
Turbine with variable geometry Download PDFInfo
- Publication number
- EP2071134A2 EP2071134A2 EP08170220A EP08170220A EP2071134A2 EP 2071134 A2 EP2071134 A2 EP 2071134A2 EP 08170220 A EP08170220 A EP 08170220A EP 08170220 A EP08170220 A EP 08170220A EP 2071134 A2 EP2071134 A2 EP 2071134A2
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- EP
- European Patent Office
- Prior art keywords
- vanes
- turbine
- guide
- guide vane
- rotation
- 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
-
- 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
- F05D2250/30—Arrangement of components
- F05D2250/34—Arrangement of components translated
Definitions
- a Ablasseklappe Waaste gate
- This can be done the control of the boost pressure, especially in turbochargers for internal combustion engines.
- An alternative to the waste gate is the adjustment of the inflow to the turbine impeller of the turbine part of the exhaust gas turbocharger by means of rotatable or displaceable guide vanes.
- exhaust gas turbochargers which are used in the automotive sector, to loader pressure increase of internal combustion engines, rotatable vanes have prevailed.
- Rotatable vanes are also referred to as VTG (Variable Turbine Geometry). If the rotatable vanes are to be closed, ie the vanes are rotated so that the flow is directed almost radially, and only a small flow area remains between the vanes, the blade ends move away from the turbine inlet.
- VTG Very Turbine Geometry
- a variant for rotatable vanes is made US 3,033,519 known. It has been found that it is beneficial for the efficiency of variable turbine blade geometry, ie, variably arranged vanes, to enter a turbine wheel when the blade end of the rotatable vanes - and only these are considered below - especially at closed VTG position Radial is located very close to the turbine inlet and the distance between the blade end and the turbine inlet is minimal.
- variable turbine geometry Upon normal positioning of the vane on an axis of rotation by which it is actuated, the vane end moves away from the periphery of the turbine wheel as the variable turbine geometry is closed as the vanes move.
- the minimum blade length of the rotatably arranged vanes of the variable turbine geometry is determined by the circumference of the blade chain in closed Position of the vanes and the overlap of two vanes. When arranged relatively far outside arranged vanes, the disadvantage of larger size results. Leakage flows that run past the sides of the blade lead to disadvantages in the thermodynamic efficiency.
- the gap surface extends between the turbine housing and the vanes of the Variable Turbine Geometry.
- the portion of the flow passing between the vanes has a defined direction dictated by the vanes.
- the part of the flow that flows through the sides, between the vanes and the housing of the turbine part disturbs this directed flow and leads to a false flow of the turbine wheel, which adversely affects the efficiency.
- This can be remedied.
- variable turbine geometry in particular a number of stator blades, which are arranged in a circle around a turbine wheel of a turbine part of a charging device, in particular an exhaust gas turbocharger, such that one blade end of the respective stator blades, in particular with closed variable turbine geometry (ie closed VTG ), radially possible close to the turbine inlet, that is as close as possible to the circumference of the turbine runner.
- closed VTG closed variable turbine geometry
- the individual blades which are arranged distributed on a blade ring around the entrance of the turbine runner wheel, are arranged eccentrically to their respective axes of rotation.
- the eccentricity in which the wing-shaped profiled vanes are arranged in their axes of rotation along the blade ring, is selected so that the blade end of the respective vanes in the salaried state, ie in the position in which the guide vane is set in the direction of the circumference of the turbine runner , becomes minimal.
- the blade end can be positioned radially closer to the periphery of the turbine runner in the closed position, which can achieve an increase in the efficiency of the turbine part.
- variable turbine geometry proposed according to the invention
- a reduction in the gap area between the turbine housing and the guide vanes of the variable turbine geometry proposed according to the invention can be achieved.
- the part of the exhaust gas flow passing through between the vanes of the VTG and the housing of the turbine part and the directional flow generated by the vanes can be negatively influenced to a false flow of the turbine wheel can be significantly reduced, which increases the achievable efficiency of the turbine part.
- variable turbine geometry with the inventively proposed eccentrically arranged vanes
- the open position in which a large flow cross-section is opened. If the vanes of the variable turbine geometry are nearly circumferentially, only a small area for flow in the radial direction with respect to the circumference of the turbine runner is available to the flow. This position is accordingly referred to as a closed position.
- the blade chain ie the circumference of the guide vanes driven along in the closed position along the blade ring, is moved closer to the circumference of the turbine runner overall. Due to this measure can be achieved that the length of the individual wing-like profiled vanes and their number can be reduced or optimized. Shorter vanes reduce the adjusting aerodynamic forces on the vanes, thereby reducing the actuator force necessary for adjustment. A smaller number of blades results in cost advantages in terms of the number of parts and assembly.
- an auxiliary blade or an auxiliary blade can be arranged on an axis of rotation, on which a guide blade is accommodated eccentrically to the axis of rotation, which favorably influences the moment required for actuating the respective axis of rotation, d , H. in the present case.
- a reduction in the moment required to operate the vane ring of the Variable Turbine Geometry (VTG) allows the use of a smaller actuator.
- the auxiliary blade or the auxiliary wing which is received at an angle to the guide vane on the axis of rotation, form with the guide vane a funnel-shaped channel whose inlet cross-section is larger on the upstream side than on the outflow side.
- FIG. 1 shows a known from the prior art, a turbine wheel associated variable turbine geometry (VTG).
- VFG turbine wheel associated variable turbine geometry
- a turbine runner 10 which is in particular a turbine runner of a turbine part of a supercharger designed as a turbocharger, comprises a number of airfoils 18.
- An exhaust gas flow 12 flows to an inflow side 14 of a circumference 32 of the turbine runner 10 and flows over an outflow side 16 from individual channels 20, which are bounded in each case by two blade leaves 18, at an outflow side 16 again.
- the channels 20, which extend on the turbine runner 10 from the inflow side 14 to the outflow side 16, have a continuous cross-sectional widening 22 in the direction of the center of the turbine runner 10.
- a blade ring 24 Concentric with the circumference 32 of the turbine runner 10, a blade ring 24 is arranged. On the blade ring 24 is a number of blades 28 of a variable turbine geometry (VTG).
- VGT variable turbine geometry
- the axis of the turbine runner 10, which coincides with the axis of the blade ring 24, is identified by reference numeral 26.
- Figure 1.1 shows a vane according to the VTG in FIG. 1 in the closed state.
- FIG. 2 shows that analogous to the turbine runner 10 according to FIG. 1
- On the turbine runner 10 a number of blades 18 are formed, which extend from the inflow side 14 to the outflow side 16 to form channels 20.
- the channels 20 have, starting from the inflow side 14 to the outflow side 16, a cross-sectional widening 22 extending continuously to the axis 26 of the turbine runner 10.
- the periphery 32 of the turbine runner 10 as shown in FIG. 2 is analogous to the representation according to FIG. 1 surrounded by a blade ring 24, which has a number of axes of rotation 36, on which arranged in an eccentricity 42 vanes 40 of the variable turbine geometry (VTG) are arranged. From the illustration according to FIG. 2 It can be seen that the vane ends 38 of the variable geometry turbine vanes (VTG) have a second, minimized change in distance 48 that is less than the first change in distance 30 upon actuation of the vanes 40 from closed to open position, as shown in FIGS Figures 2.1 and 2.2 ,
- Figure 2.1 shows that the wing-like profiled vane 40 of the variable turbine geometry (VTG) with respect to the center of the axis of rotation 36 is received in an eccentricity 42.
- the arrow provided with reference numeral 34 indicates the pivoting movement about which the rotation axis 36 is actuated by a not shown, preferably electrically formed actuator.
- the individual along the blade ring 24 at axes of rotation 36 recorded guide vanes 40 are flown on its inflow side 44 of the exhaust gas flow 12. In the in FIG. 2 illustrated closed position 50, the guide vanes 40 are almost in the circumferential direction, so that the exhaust gas flow is only a small area for flow available.
- a comparison of the displacement movements of the blade 28 of the variable turbine geometry (VTG) according to the Figures 1.1 and 1.2 for adjusting the arranged in the eccentricity 42 vanes 40 according to FIGS. 2.1 and 2.2 shows that in the proposed inventive eccentric positioning of the vanes 40 of the variable turbine geometry (VTG) to the rotation axis 36, a smaller change in the position of the respective blade end 38 to the periphery 32 of the turbine runner 10 results.
- a further advantage of the variable turbine geometry solution proposed according to the invention is the fact that the axis of rotation 36 can be arranged radially further away from the axis 26 of the turbine runner 10, but the guide vanes 40 are not displaced. This results from the inventive eccentric mounting of the guide vanes 40, at the axes of rotation 36.
- the adjustment mechanism for adjusting the vanes 40 of the variable turbine geometry is located on the bearing housing side of the bearing of the turbine runner 10. The size of this bearing housing in not to the same extent to reduce the circumference of the turbine runner 10. Thus, it is difficult for small turbine runners 10, the axes of rotation 36 of the vanes 40 to be placed close to the periphery of the turbine wheel 10, without resulting in overlaps between the adjustment mechanism and the bearing housing.
- the solution proposed according to the invention makes it possible to remove the axes of rotation 86 of the guide vanes 40 radially further from the turbine wheel 10, but not to displace the guide vanes 40 themselves.
- Reference numeral 50 denotes the closed position of the vane 40.
- reference numeral 50 denotes the closed position of the vane 40.
- FIG. 3 shows that on the axis of rotation 36, which is actuated by a not shown, preferably electrically formed actuator, the guide vane 40 is arranged in the eccentric 42 with respect to the axis of symmetry of the axis of rotation 36.
- the vane 40 has a wing-shaped profile 46 and has the already mentioned upstream side 44 and the blade end 38.
- an auxiliary blade 54 is also located on the axis of rotation 36 in an eccentricity 42 with respect to its axis of symmetry.
- the auxiliary blade 54 is arranged at an angle of attack 58 with respect to the guide blade 40.
- the auxiliary blade 54 like the vane 40 mounted in the eccentric 42, includes an upstream side 56 and a blade end.
- the upstream sides 44, 56 and the blade ends of the guide vanes 40 and the auxiliary blade 54 each extend in the same directions.
- Between the auxiliary blade 54 and the assigning this wing side of the vane 40 has a shape of a funnel 60 having channel is formed. Its inlet cross section is dimensioned to be larger than the outflow cross section defined by the blade end 38 of the guide vane 40 and the auxiliary vane 54.
- the exhaust gas flow 12 around the vanes 40 see illustration according to FIG. 2 , generates an aerodynamic moment which acts on the vane 40 arranged in the eccentricity 42 relative to the axis of rotation 36.
- this moment must not change its direction of rotation over the entire adjustment range of the variable turbine geometry (VTG) and thus over the entire adjustment range of the individual guide vanes 40.
- this moment must not be too great in any position of the guide vane 40, since otherwise the actuator required for actuation for the adjustment of the axis of rotation 36 must be made larger. This would require, in particular when using an electric actuator, a significantly larger actuator, a larger torque applying actuator.
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
Description
Zur Regelung der Leistung, insbesondere der Turbinenleistung einer Aufladeeinrichtung, die als Abgasturbolader beschaffen ist, kommt üblicherweise eine Abblaseklappe (Waste Gate) zum Einsatz. Damit kann die Regelung des Ladedrucks, insbesondere bei Turboladern für Verbrennungskraftmaschinen erfolgen. Eine Alternative zum Waste Gate ist die Verstellung der Zuströmung zum Turbinenlaufrad des Turbinenteiles des Abgasturboladers mittels verdrehbarer oder verschiebbarer Leitschaufeln. Bei Abgasturboladern, die im Kfz-Bereich, zur Laderdruckerhöhung von Verbrennungskraftmaschinen eingesetzt werden, haben sich verdrehbare Leitschaufeln durchgesetzt.To control the power, in particular the turbine power of a supercharger, which is designed as an exhaust gas turbocharger, usually a Ablasseklappe (waste gate) is used. This can be done the control of the boost pressure, especially in turbochargers for internal combustion engines. An alternative to the waste gate is the adjustment of the inflow to the turbine impeller of the turbine part of the exhaust gas turbocharger by means of rotatable or displaceable guide vanes. In exhaust gas turbochargers, which are used in the automotive sector, to loader pressure increase of internal combustion engines, rotatable vanes have prevailed.
Verdrehbare Leitschaufeln werden auch als VTG (Variable Turbinen Geometrie) bezeichnet. Sollen die verdrehbaren Leitschaufeln geschlossen werden, d. h. die Leitschaufeln so verdreht werden, dass die Strömung nahezu radial gerichtet ist, und nur noch eine kleine Strömungsfläche zwischen den Schaufeln verbleibt, bewegen sich die Schaufelenden vom Turbineneintritt weg. Eine Ausführungsvariante für verdrehbare Leitschaufeln ist aus
Erfindungsgemäß wird vorgeschlagen, die Variable Turbinengeometrie, insbesondere eine Anzahl von Leitschaufeln, die kreisförmig um ein Turbinenlaufrad eines Turbinenteils einer Aufladeeinrichtung, insbesondere eines Abgasturboladers, angeordnet sind, derart anzuordnen, dass ein Schaufelende der jeweiligen Leitschaufeln, insbesondere bei geschlossener Variabler Turbinengeometrie (d. h. geschlossener VTG), sich radial möglich nahe am Turbineneintritt, d. h. möglichst nahe an dem Umfang des Turbinenlaufrades befindet. Je kürzer die einzelnen Leitschaufeln, die zum Beispiel entlang eines Schaufelkranzes angeordnet werden und über einen Elektroantrieb verstellt werden, gestaltet werden können, desto kleiner baut die Variable Turbinengeometrie in radiale Richtung. Dies beeinflusst die Baugröße der Aufladeeinrichtung, insbesondere eines Abgasturboladers, günstig. Der erfindungsgemäß vorgeschlagenen Lösung folgend, werden die einzelnen Schaufeln, die an einem Schaufelkranz verteilt um den Eintritt des Turbinenlaufrades angeordnet sind, an ihren jeweiligen Drehachsen exzentrisch zu diesen angeordnet. Die Exzentrizität, in der die flügelförmig profilierten Leitschaufeln in ihren Drehachsen entlang des Schaufelringes angeordnet sind, ist so gewählt, dass das Schaufelende der jeweiligen Leitschaufeln im angestellten Zustand, d. h. in der Position, in der die Leitschaufel in Richtung auf den Umfang des Turbinenlaufrades gestellt ist, minimal wird. Die Minimierung des Abstandes des Schaufelendes in Bezug auf den Umfang des Turbinenlaufrades hat zur Folge, dass der Spalt bzw. die Spaltfläche, über welche gasförmiges Medium - im vorliegenden Fall Abgas - abströmen kann, ohne im Turbinenlaufrad Arbeit zu leisten, im Vergleich zu herkömmlichen Lösungen erheblich verringert wird.According to the invention, it is proposed to arrange the variable turbine geometry, in particular a number of stator blades, which are arranged in a circle around a turbine wheel of a turbine part of a charging device, in particular an exhaust gas turbocharger, such that one blade end of the respective stator blades, in particular with closed variable turbine geometry (ie closed VTG ), radially possible close to the turbine inlet, that is as close as possible to the circumference of the turbine runner. The shorter the individual guide vanes, which are arranged, for example, along a blade ring and can be adjusted by means of an electric drive, can be designed, the smaller the variable turbine geometry builds in the radial direction. This affects the size of the charging device, in particular an exhaust gas turbocharger, low. Following the solution proposed by the invention, the individual blades, which are arranged distributed on a blade ring around the entrance of the turbine runner wheel, are arranged eccentrically to their respective axes of rotation. The eccentricity in which the wing-shaped profiled vanes are arranged in their axes of rotation along the blade ring, is selected so that the blade end of the respective vanes in the salaried state, ie in the position in which the guide vane is set in the direction of the circumference of the turbine runner , becomes minimal. The minimization of the distance of the blade end with respect to the circumference of the turbine runner has the result that the gap or the gap surface, via which gaseous medium - in the present case exhaust gas - can flow out, without in the turbine runner Work is significantly reduced compared to traditional solutions.
Durch die erfindungsgemäß vorgeschlagene Lösung kann das Schaufelende bei geschlossener Stellung radial näher an den Umfang des Turbinenlaufrades positioniert werden, wodurch sich eine Erhöhung des Wirkungsgrades des Turbinenteiles erzielen lässt.The inventively proposed solution, the blade end can be positioned radially closer to the periphery of the turbine runner in the closed position, which can achieve an increase in the efficiency of the turbine part.
Mit der erfindungsgemäß vorgeschlagenen Lösung der Variablen Turbinengeometrie (VTG) lässt sich eine Verringerung der Spaltfläche zwischen dem Turbinengehäuse und den Leitschaufeln der erfindungsgemäß vorgeschlagenen Variablen Turbinengeometrie erreichen. So kann der Teil der Abgasströmung, der zwischen den Leitschaufeln der VTG und dem Gehäuse des Turbinenteiles durchströmt, und die durch die Leitschaufeln erzeugte gerichtete Strömung negativ beeinflusst zu einer Falschanströmung des Turbinenrades geführt werden, entscheidend herabgesetzt werden, was den erreichbaren Wirkungsgrad des Turbinenteiles erhöht.With the solution of the variable turbine geometry (VTG) proposed according to the invention, a reduction in the gap area between the turbine housing and the guide vanes of the variable turbine geometry proposed according to the invention can be achieved. Thus, the part of the exhaust gas flow passing through between the vanes of the VTG and the housing of the turbine part and the directional flow generated by the vanes can be negatively influenced to a false flow of the turbine wheel can be significantly reduced, which increases the achievable efficiency of the turbine part.
Bei der Variablen Turbinengeometrie(VTG) mit die erfindungsgemäß vorgeschlagene exzentrisch angeordneten Leitschaufeln wird eine Position der Leitschaufeln, in der diese in radialer Richtung um einen kleinen Winkel verstellt sind, als offene Position bezeichnet, in der ein großer Strömungsquerschnitt geöffnet ist. Stehen die Leitschaufeln der Variablen Turbinengeometrie nahezu in Umfangsrichtung, so steht der Strömung nur eine kleine Fläche zur Durchströmung in radiale Richtung in Bezug auf den Umfang des Turbinenlaufrades zur Verfügung. Diese Position wird dementsprechend als geschlossene Position bezeichnet.In the variable turbine geometry (VTG) with the inventively proposed eccentrically arranged vanes, a position of the vanes in which they are adjusted in the radial direction by a small angle, referred to as the open position in which a large flow cross-section is opened. If the vanes of the variable turbine geometry are nearly circumferentially, only a small area for flow in the radial direction with respect to the circumference of the turbine runner is available to the flow. This position is accordingly referred to as a closed position.
In einer weiteren vorteilhaften Ausgestaltung des der Erfindung zugrunde liegenden Gedankens ist die Schaufelkette, d. h. der Umfang der durch die in geschlossene Position gefahrenen Leitschaufeln entlang des Schaufelkranzes gebildet ist, insgesamt näher an den Umfang des Turbinenlaufrades gerückt. Aufgrund dieser Maßnahme kann erreicht werden, dass die Länge der einzelnen flügelartig profilierten Leitschaufeln sowie deren Anzahl reduziert bzw. optimiert werden kann. Kürzere Schaufeln verringern die sich einstellenden aerodynamischen Kräfte auf die Leitschaufeln und verringern dadurch die zur Verstellung notwendige Aktuatorkraft. Eine geringere Schaufelanzahl ergibt Kostenvorteile hinsichtlich der Anzahl der Teile sowie der Montage.In a further advantageous embodiment of the idea underlying the invention, the blade chain, ie the circumference of the guide vanes driven along in the closed position along the blade ring, is moved closer to the circumference of the turbine runner overall. Due to this measure can be achieved that the length of the individual wing-like profiled vanes and their number can be reduced or optimized. Shorter vanes reduce the adjusting aerodynamic forces on the vanes, thereby reducing the actuator force necessary for adjustment. A smaller number of blades results in cost advantages in terms of the number of parts and assembly.
In einer weiteren Ausführungsvariante des der Erfindung zugrunde liegenden Gedankens kann an einer Drehachse, an der eine Leitschaufel exzentrisch zur Drehachse aufgenommen ist, eine Hilfsschaufel oder ein Hilfsflügel angeordnet werden, welches das Moment, das zur Betätigung der jeweiligen Drehachse erforderlich ist, günstig beeinflusst, d. h. im vorliegenden Falle herabsetzt. Eine Herabsetzung des zur Betätigung des Schaufelkranzes der Variablen Turbinengeometrie (VTG) erforderlichen Momentes ermöglicht den Einsatz eines kleiner bauenden Aktuators. Durch das Vorsehen eines Hilfsflügels oder einer Hilfsschaufel, die in einem Anstellwinkel an der Drehachse in Bezug auf die flügelartig profilierte Leitschaufel angebracht wird, kann das auf die Drehachse wirkende Moment über den gesamten Stellbereich der variablen Turbinengeometrie günstig beeinflusst werden. Dieses wird in keiner Stellposition zu groß, so dass der Aktuator, insbesondere ein eingesetzter elektrischer Aktuator zur gemeinsamen Betätigung der Drehachsen, bzw. des Schaufelkranzes kleiner dimensioniert werden kann. Die Hilfsschaufel bzw. der Hilfsflügel, die/der in einem Anstellwinkel zur Leitschaufel an der Drehachse aufgenommen ist, bilden mit der Leitschaufel einen trichterförmigen Kanal, dessen Eintrittsquerschnitt auf der Anströmseite größer ist als auf der Ausströmseite.In a further embodiment variant of the idea underlying the invention, an auxiliary blade or an auxiliary blade can be arranged on an axis of rotation, on which a guide blade is accommodated eccentrically to the axis of rotation, which favorably influences the moment required for actuating the respective axis of rotation, d , H. in the present case. A reduction in the moment required to operate the vane ring of the Variable Turbine Geometry (VTG) allows the use of a smaller actuator. By providing an auxiliary blade or an auxiliary blade, which is mounted at an angle of attack on the axis of rotation with respect to the wing-like profiled guide vane, the moment acting on the axis of rotation can be favorably influenced over the entire range of the variable turbine geometry. This is too large in any position, so that the actuator, in particular an inserted electric actuator for joint operation of the axes of rotation, or the blade ring can be made smaller. The auxiliary blade or the auxiliary wing, which is received at an angle to the guide vane on the axis of rotation, form with the guide vane a funnel-shaped channel whose inlet cross-section is larger on the upstream side than on the outflow side.
Anhand der Zeichnung wird die Erfindung nachstehend eingehender beschrieben.With reference to the drawing, the invention will be described below in more detail.
Es zeigt:
- Figur 1
- eine aus dem Stand der Technik bekannte Ausführungsform eines Turbinenlauf rades mit variabler Turbinengeometrie (VTG),
- Figur 1.1
- eine Leitschaufel gemäß dem Stand der Technik im abgestellten Zustand,
- Figur 1.2
- eine Leitschaufel gemäß dem Stand der Technik im angestellten Zustand,
- Figur 2
- die erfindungsgemäß vorgeschlagene variable Turbinengeometrie,
- Figur 2.1
- eine erfindungsgemäß vorgeschlagene Leitschaufel im nicht angestellten Zustand,
- Figur 2.2
- eine erfindungsgemäß vorgeschlagene Leitschaufel im an den Umfang des Turbinenlaufrades angestellten Zustand und
- Figur 3
- eine Ausführungsvariante einer erfindungsgemäß vorgeschlagenen Leitschaufel, die exzentrisch an einer Drehachse aufgenommen ist und darüber hinaus eine Hilfsschaufel bzw. einen Hilfsflügel umfasst.
- FIG. 1
- a known from the prior art embodiment of a turbine wheel with variable turbine geometry (VTG),
- Figure 1.1
- a vane according to the prior art in the parked state,
- Figure 1.2
- a vane according to the prior art in the salaried state,
- FIG. 2
- the inventively proposed variable turbine geometry,
- Figure 2.1
- a guide vane proposed in accordance with the invention in the unoccupied state,
- Figure 2.2
- an inventively proposed vane in employed at the periphery of the turbine runner state and
- FIG. 3
- a variant of an inventive proposed vane, which is eccentrically received on a rotation axis and beyond an auxiliary blade or an auxiliary wing comprises.
Wie
Konzentrisch zum Umfang 32 des Turbinenlaufrades 10 ist ein Schaufelkranz 24 angeordnet. Am Schaufelkranz 24 befindet sich eine Anzahl von Schaufeln 28 einer Variablen Turbinengeometrie (VTG). Der Vollständigkeit halber sei erwähnt, dass die Achse des Turbinenlaufrades 10, die mit der Achse des Schaufelkranzes 24 zusammenfällt, mit Bezugszeichen 26 identifiziert ist.Concentric with the
Aus
Der Darstellung gemäß
Der Umfang 32 des Turbinenlaufrades 10 gemäß der Darstellung in
Aus der Darstellung gemäß
Ein Vergleich der Verstellbewegungen der Schaufel 28 der Variablen Turbinengeometrie (VTG) gemäß den
Ein weiterer Vorteil der erfindungsgemäß vorgeschlagenen Lösung der Variablen Turbinengeometrie ist der Umstand, dass die Drehachse 36 radial weiter entfernt von der Achse 26 des Turbinenlaufrades 10 angeordnet werden kann, die Leitschaufeln 40 jedoch nicht verschoben werden. Dies ergibt sich durch die erfindungsgemäße exzentrische Lagerung der Leitschaufeln 40, an deren Drehachsen 36. Die Verstellmechanik zur Verstellung der Leitschaufeln 40 der Variablen Turbinengeometrie befindet sich auf der Lagergehäuseseite der Lagerung des Turbinenlaufrades 10. Die Größe dieses Lagergehäuses in nicht in gleichem Maße zu verkleinern wie der Umfang des Turbinenlaufrades 10. Damit ist es bei kleinen Turbinenlaufrädern 10 schwierig, die Drehachsen 36 der Leitschaufeln 40 nahe an den Umfang des Turbinenrades 10 zu legen, ohne dass sich Überschneidungen zwischen dem Verstellmechanismus und dem Lagergehäuse ergeben. Die erfindungsgemäß vorgeschlagene Lösung ermöglicht es, die Drehachsen 86 der Leitschaufeln 40 radial weiter vom Turbinenrad 10 zu entfernen, die Leitschaufeln 40 selbst jedoch aber nicht zu verschieben.A further advantage of the variable turbine geometry solution proposed according to the invention is the fact that the axis of
Bei den in
In
Eine weitere vorteilhafte Ausführungsvariante der erfindungsgemäß vorgeschlagenen Lösung ist in
Claims (10)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200710060044 DE102007060044A1 (en) | 2007-12-13 | 2007-12-13 | Variable turbine geometry |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2071134A2 true EP2071134A2 (en) | 2009-06-17 |
EP2071134A3 EP2071134A3 (en) | 2010-10-27 |
Family
ID=40418455
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08170220A Withdrawn EP2071134A3 (en) | 2007-12-13 | 2008-11-28 | Turbine with variable geometry |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2071134A3 (en) |
DE (1) | DE102007060044A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2397652A3 (en) * | 2010-06-20 | 2014-12-17 | Honeywell International Inc. | Multiple airfoil vane for a turbocharger |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009020592A1 (en) * | 2009-05-09 | 2010-11-11 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device i.e. exhaust gas turbocharger, for motor vehicle, has flow channel lying between rotatably supported guide vanes, where one guide vane is flow-permeable and forms another flow channel |
DE102012101974A1 (en) * | 2012-03-08 | 2013-09-12 | Ihi Charging Systems International Gmbh | Turbine i.e. radial-flow turbine, for supercharger for compressing air supplied to internal combustion engine of motor vehicle, has mean line surface positioned relative to rotational axis in flow channel |
DE102019127980A1 (en) * | 2019-10-16 | 2021-04-22 | Ihi Charging Systems International Gmbh | Adjustable diffuser for an exhaust gas routing section of an exhaust gas turbocharger and an exhaust gas turbocharger |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3033519A (en) | 1958-09-12 | 1962-05-08 | United Aircraft Corp | Turbine nozzle vane construction |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1071420B (en) * | 1956-05-31 | 1959-12-17 | The Garrett Corporation, Los Aneles, Calif. (V. St. A.) | Adjustable guide device for turbines, in particular gas turbines |
US3101926A (en) * | 1960-09-01 | 1963-08-27 | Garrett Corp | Variable area nozzle device |
US3069070A (en) * | 1961-11-14 | 1962-12-18 | Worthington Corp | Diffuser vane system for turbomachinery |
-
2007
- 2007-12-13 DE DE200710060044 patent/DE102007060044A1/en not_active Withdrawn
-
2008
- 2008-11-28 EP EP08170220A patent/EP2071134A3/en not_active Withdrawn
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3033519A (en) | 1958-09-12 | 1962-05-08 | United Aircraft Corp | Turbine nozzle vane construction |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2397652A3 (en) * | 2010-06-20 | 2014-12-17 | Honeywell International Inc. | Multiple airfoil vane for a turbocharger |
Also Published As
Publication number | Publication date |
---|---|
EP2071134A3 (en) | 2010-10-27 |
DE102007060044A1 (en) | 2009-06-18 |
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