EP3400373B1 - Rotor blade for a gas turbine with cooled rubbing edge - Google Patents
Rotor blade for a gas turbine with cooled rubbing edge Download PDFInfo
- Publication number
- EP3400373B1 EP3400373B1 EP17707889.6A EP17707889A EP3400373B1 EP 3400373 B1 EP3400373 B1 EP 3400373B1 EP 17707889 A EP17707889 A EP 17707889A EP 3400373 B1 EP3400373 B1 EP 3400373B1
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- EP
- European Patent Office
- Prior art keywords
- rotor blade
- depression
- edge
- blade according
- rubbing
- 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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- 238000001816 cooling Methods 0.000 claims description 74
- 239000012809 cooling fluid Substances 0.000 claims description 34
- 230000002093 peripheral effect Effects 0.000 claims description 22
- 238000005266 casting Methods 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000010146 3D printing Methods 0.000 claims description 2
- 238000005259 measurement Methods 0.000 claims 2
- 239000000463 material Substances 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 238000007790 scraping Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Images
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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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
- F05D2260/20—Heat transfer, e.g. cooling
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Definitions
- the present invention relates to a rotor blade for a gas turbine having the features of claim 1.
- the gas turbine system In a gas turbine system, thermal energy and / or flow energy of a hot gas generated by burning a fuel is converted into rotational energy, which is usually converted into electrical energy by means of a generator.
- the gas turbine system has a flow channel, in the axial direction of which a turbine rotor is rotatably mounted.
- This comprises a plurality of wheel disks, on the radially outer end faces of which a plurality of rotor blades are arranged in the form of a blade ring.
- the rotor blades each have blade roots which are inserted into one or more receiving grooves formed on the end faces of the wheel disks and are fixed therein.
- Blade platforms are formed on the upper side of the blade roots, from the outer sides of which facing away from the wheel disk blade blades protrude into the flow channel.
- the hot gas flows through the flow channel, the flowing hot gas applying a force to the rotor blades which, due to the shape of the blade blades, is converted into a torque acting on the turbine rotor, which drives the turbine rotor to rotate.
- rotor blades which, even under high thermal loads, have sufficient mechanical strength for the operation of the gas turbine system.
- rotor blades are provided with complex coating systems.
- rotor blades are cooled while the gas turbine system is in operation.
- cavities and cooling channels are formed in their interior, through which a cooling fluid, mostly air, flows.
- Common cooling methods are, for example, impingement cooling, in which the cooling fluid is guided in such a way that it strikes the wall of the airfoil from the inside, or film cooling, in which the cooling fluid flows outward from the interior of the airfoil through cooling bores formed in the airfoil body to form a cooling film on the outside of the EP 2 378 076 A formed cooling bores in a recess at the tip of an airfoil are known.
- US 2014/044557 A1 known to produce the airfoils of cooled rotor blades in a casting process.
- Commonly cast airfoils each include a hollow airfoil body which is closed in the area of the airfoil tip by what is known as a crown base. Furthermore, in the area of the blade tip, the airfoil body has a rubbing edge which is cast on the outside flush with the airfoil body and along the outer contour the peripheral wall of the airfoil body protrudes in the radial direction.
- a narrow radial gap of a predetermined width remains between the rubbing edge and a channel wall delimiting the flow channel of the gas turbine system, in order on the one hand to enable low-friction rotation of the turbine rotor in the flow channel, but on the other hand to allow only a small part of the hot gas to flow unused through the radial gap.
- Changes in the radial gap can occur after the turbine system has been in operation for a certain period of time.
- the turbine runner can leave its originally central position by creeping, the length of the rotor blades can increase as a result of the centrifugal force or an originally circular flow channel can be ovalized.
- the cooling fluid outlet openings with the removed airfoil material can then become clogged, as a result of which cooling of the abrading edges is impaired or prevented.
- the inadequate cooling of the rubbing edges leads to greater wear and, consequently, to a shorter service life of the airfoils.
- the present invention creates a rotor blade for a gas turbine of the type mentioned at the outset, in which at least one recess is formed in the end face of the rubbing edge, into which at least some of the cooling channels open in such a way that the cooling fluid outlet openings are completely in a bottom area of the at least lie a depression.
- the invention is based on the idea of lowering the cooling fluid outlet openings in relation to the radial direction with respect to the end face of the rubbing edge. According to the invention, this is achieved in that at least one recess is formed in the end face of the rubbing edge and at least some of the cooling outlet openings are arranged completely in a bottom area of the at least one recess. In this way, the cooling fluid outlet openings are removed from the contact area between the end face of the rubbing edge and the duct wall, as a result of which clogging of the cooling fluid outlet openings with removed airfoil material is reduced or prevented. As a result, the cooling capacity is essentially retained over the operating time of the gas turbine system, which is associated with a correspondingly long service life of the blades.
- the base area of the at least one depression is arranged between the end face of the rubbing edge and the outer surface of the crown base in relation to the radial direction.
- the bottom area is preferably designed as a flat bottom surface which, compared to the end face, has a depth which is in the range from 0.5 mm to 4.5 mm and preferably in the range from 0.5 mm to 2.5 mm.
- Such a radial position of the bottom area has the effect, on the one hand, that the cooling fluid outlet openings are arranged in the immediate vicinity of the free end area of the abrading edge, as a result of which effective cooling of this area of the abrading edge can be ensured.
- the small depth of the bottom surface of the recess compared to the front surface is sufficient in order to prevent material particles removed from the end face from clogging the cooling fluid outlet openings, which is associated with a constant cooling performance.
- the rubbing edge has a total height in relation to the radial direction relative to the outer surface of the crown base which is in the range from 1 mm to 10 mm, advantageously in the range from 1.5 mm to 6 mm and preferably 3.5 mm. In rubbing edges with a total height in this area, depressions with a suitable depth can easily be formed.
- an inner surface of the rubbing edge is inclined outwardly with respect to the radial direction, forming a first angle of inclination, and is largely straight when viewed along the radial direction, the first angle of inclination being measured in a plane extending in the radial direction, which perpendicularly intersects the rubbing edge, and in is in the range from 0 ° to 45 ° and is preferably more than 10 ° and / or less than 30 °.
- the at least one depression extends to an inside of the rubbing edge, forming a stepped cross section, wherein in particular a step corner of the cross section, preferably the inside corner, is rounded.
- at least one recess is designed to be open to the inside. Such depressions can be produced simply during the casting of the airfoil body or only afterwards, for example by milling or eroding.
- cooling channels are opposite a plane perpendicular to the radial direction in the direction of the leading edge of the rotor blade or inclined in the direction of the trailing edge of the rotor blade with the formation of a fourth angle of inclination, the fourth angle of inclination in the direction of the leading edge of the rotor blade being measured in a plane which perpendicularly intersects the measuring plane of the first angle of inclination, in the range between 30 ° and 80 ° and in particular 45 °.
- Cooling channels with such an inclination in the direction of the leading edge or in the direction of the trailing edge have a greater length, as a result of which the convective cooling of the abrading edge can be improved.
- cooling channels inclined towards the leading edge the jets are guided over the tips of the rubbing edge on the suction side and cool the surface where it is usually hottest.
- they can favorably influence the direction of flow of the exiting cooling fluid. Cooling channels with different directions of inclination can penetrate one another or cross without penetration.
- the end face of the rubbing edge preferably has a width which is less than the thickness of the circumferential wall of the blade body in the region of the at least one recess.
- the end face of the rubbing edge can have a width which is less than the width of the bottom region of the at least one recess. In this way, only a relatively narrow outer area of the abrading edge forms its radially outer end area.
- cooling channels are inclined relative to the radial direction transversely to the inner surface of the rubbing edge with the formation of a second angle of inclination, in particular the second inclination angle of the cooling channels, which are each measured in a plane extending in the radial direction, which perpendicularly intersects the rubbing edge, equal to or are approximately equal to the first angle of inclination of the inner surface of the rubbing edge.
- Cooling channels with such an inclination lead this out of the cooling fluid outlet openings exiting cooling fluid from the inside to the outer end area of the scraper edge.
- the end face of the rubbing edge and the bottom area of the at least one recess jointly have a width that is approximately equal to the thickness of the circumferential wall of the blade body in the area of the at least one recess.
- Such rubbing edges essentially represent a continuation of the circumferential wall of the blade body beyond the crown base.
- the recess in the end face of the rubbing edge can be designed as a groove leaving an outside end face section and an inside end face section, in particular the inner corners of the recess being rounded.
- the width of the outside end face section and the width of the inside end face section of the abrading edge can each be in the range of 0.5 mm to 5 mm and preferably at least 1 mm, the ratio between the outside width and the inside width is in the range between 0.7 mm and 1.3 mm, in particular 0.9 and 1.1, and is preferably 1.
- the circumferential wall tapers in the area of the recess in the direction of the crown base in favor of the cavity, the thickness of the circumferential wall being reduced from an initial thickness to a tapered thickness that is at least half as large as the initial thickness, and the tapering over a radial section of the peripheral wall takes place, the height of which is at least five times and at most ten times as great as the initial thickness.
- the cooling channels can be designed in such a way that they extend closer to the outside of the abrading edge, which is accompanied by improved convective cooling of the abrading edge.
- the cooling fluid outlet openings are advantageously arranged next to one another and at a distance from one another, in particular equidistantly and / or along a line. Cooling fluid outlet openings arranged in this way are particularly suitable for cooling the abrading edge along its circumferential extent. In principle, however, the cooling fluid outlet openings can be distributed as desired.
- the at least one depression can only be provided in a section of the rubbing edge that protrudes from the suction-side wall section of the surrounding wall. In this way, the cooling of the section of the rubbing edge protruding from the suction-side wall section of the peripheral wall can be improved.
- a plurality of depressions arranged next to one another in the circumferential direction can be provided, into each of which a part of the cooling channels opens and which in particular each have at least one feature mentioned above.
- Several depressions lead to a corresponding grouping of the cooling channels.
- each cooling channel extends in a straight line and / or has a circular cross section with a diameter which is in the range from 0.25 mm to 2 mm and is preferably 0.6 mm.
- the cooling ducts can be widened in the area of the cooling fluid outlet openings, the widenings in particular having the shape of a cylinder whose height is at most five times, preferably as large as the diameter of the cooling duct and / or its diameter is at most three times, preferably twice as large as that Diameter of the cooling channel.
- Such widened cooling fluid outlet openings can act as a diffuser and expand the exiting cooling fluid flow accordingly, so that a large area of the rubbing edge can be cooled according to the principle of film cooling.
- the cooling fluid outlet openings can also be widened conically, semi-conically or in a fan-like manner.
- the cooling channels are advantageously designed as bores. Rectilinear cooling channels with a circular cross section can easily be introduced into a cast airfoil body by drilling.
- a transition area between an inner surface of the rubbing edge and the outer surface of the crown base is rounded. Which improves the aerodynamic Blade tip properties. Otherwise, the inner surface of the abradable edge, viewed along the radial direction, is largely straight.
- the airfoil body is produced by casting or in a generative process, in particular by means of 3D printing.
- Casting has proven to be a suitable manufacturing process, particularly for cooled airfoils with a cavity in their interior.
- generative processes are also suitable for the production of airfoil bodies.
- the Figures 1 to 3 show a rotor blade for a gas turbine according to a first embodiment of the present invention.
- the rotor blade comprises an airfoil 1 extending in a radial direction R with a cast airfoil body 2.
- the airfoil body 2 has a circumferential wall 3 which has a pressure-side wall section 3a and a suction-side wall section 3b.
- the blade body 2 comprises a plate-shaped crown base 4, which is connected to the peripheral wall 3 in the area of the blade tip 5.
- the circumferential wall 3 and the crown base 4 define a cavity 6 in the airfoil body 2 through which a cooling fluid flows during the operation of the gas turbine.
- the airfoil body 2 comprises a rubbing edge 7.
- the rubbing edge 7 extends along the circumferential wall 3 and is aligned with the latter on the outside.
- the rubbing edge 7 protrudes radially above the crown bottom 4 and has a total height h relative to the radial direction R opposite the outer surface 4a of the crown bottom, which is measured perpendicular to the outer surface 4a of the crown bottom and is approximately 3 mm.
- an inner surface 7a of the abrading edge 7 is largely straight and inclined with respect to the radial direction R by a first angle of inclination ⁇ of approx.
- a transition area 8 between the inner surface 7a of the rubbing edge 7 and the outer surface 4a of the crown base 4 is rounded.
- a recess 9 is formed which extends to the inside of the rubbing edge 7, forming a stepped cross section.
- the inner corner 10 of the stepped cross-section is rounded.
- the bottom area 9a of the recess 9 is designed as a flat bottom surface and, in relation to the radial direction R, is arranged between the end surface 7b of the rubbing edge 7 and the outer surface 4a of the crown base 4.
- the outer surface 4a of the crown bottom 4, the bottom surface 9a of the recess 9 and the end face 7b of the rubbing edge 7 extend parallel to each other and perpendicular to the radial direction R.
- the recess 9 has a depth h 1 compared to the end face 7b, which as perpendicular distance between the bottom surface 9a and the end face 7b is measured and is approximately 1 mm.
- the vertically measured height h 2 of the bottom surface of the recess 9 above the outer surface 4a of the crown bottom 4 is approximately 2 mm.
- the bottom surface 9a of the recess 9 and the outer surface 4a of the crown bottom 4 can, however, also be inclined to one another and / or to the radial direction R, the depth h 1 and the height h 2 then being determined in relation to the inner corner 10.
- the end face 7b of the rubbing edge 7 has a width a 1 which is less than the thickness d 1 of the peripheral wall 3 of the blade body 2 in the area of the recess 9.
- the width a 1 of the end face 7b is the Abrasive edge 7 in the region of the recess 9 is less than the width b 1 of the bottom region 9a the recess 9.
- the end face 7b of the rubbing edge 7 and the bottom area 9a of the recess 9 have a width a 1 + b 1 , which is approximately equal to the thickness d 1 of the peripheral wall 3 of the airfoil body 2 in the area of the recess 9, the Thickness d 1 is measured as the vertical distance between the outer surface and the inner surface of the surrounding wall 3.
- the widths a 1 and b 1 are each measured parallel to one another and to the outer surface 4 a of the crown base 4.
- Other embodiments of the present invention can have relative proportions of the widths a 1 and b 1 and of the thickness d 1 which differ from those selected here.
- cooling channels 11 are formed which, starting from the cavity 6, extend to cooling fluid outlet openings 12 which are provided in the rubbing edge 7.
- the cooling channels 11 open into the recess 9 in such a way that the cooling fluid outlet openings 12 are arranged completely in the bottom region 9 a of the recess 9.
- the cooling fluid outlet openings 12 in the recess 9 are arranged equidistantly and alongside one another along a line.
- Each cooling channel 11 is designed as a bore and extends in a straight line. It has a circular cross-section with a diameter that is approximately 0.6 mm.
- Each cooling channel 11 is inclined with respect to the radial direction R transversely to the inner surface 7a of the scraping edge 7, the second angles of inclination ⁇ of the cooling channels 11, which are each measured in a plane extending in the radial direction R, which perpendicularly intersects the scraping edge 7, for example are equal to the first angle of inclination ⁇ of the inner surface 7a of the rubbing edge 7.
- the Figure 4 shows a rotor blade for a gas turbine according to a second embodiment of the present invention.
- the structure of this rotor blade basically agrees with the structure of the Figures 1 to 3 first embodiment shown.
- the cooling channels are widened in the area of the cooling fluid outlet openings.
- the widened cooling fluid opening 12a has the shape of a cylinder whose height h 5 is equal to the diameter of the cooling channel 11 and whose diameter c 5 is twice the diameter of the cooling channel 11, resulting in a cross-sectional area for the cylinder that is four times as large like the cross-sectional area of the cooling channel 11.
- a widened cooling flow is correspondingly generated during operation of the rotor blade, with which a large area of the rubbing edge 7 can be cooled.
- the Figure 5 Fig. 3 shows a moving blade for a gas turbine according to a third embodiment of the present invention. It basically has the same structure as that in the Figures 1 to 3 illustrated blade.
- the recess 9 is designed as a groove leaving an outside end face section and an inside end face section, i.e. does not extend to the inside of the rubbing edge 7, but is also delimited on the inside by the rubbing edge 7.
- the outside end face 7b has a width a 2
- the inside end face 7b has a width c 2
- the bottom region 9a of the recess 9 has a width b 2 .
- the first angle of inclination ⁇ is the Inner surface 7a of the rubbing edge 7 compared to the radial direction R is correspondingly smaller.
- the Figure 6 Fig. 3 shows a moving blade for a gas turbine according to a fourth embodiment of the present invention. It differs from the previously described embodiments in that the peripheral wall 3 tapers in the direction of the crown base 4 in favor of the cavity 6.
- the thickness of the peripheral wall 3 is reduced from an initial thickness d 1 to a tapered thickness d 2 , which is about half the size of the initial thickness d 1 .
- the tapering takes place over a radial section of the circumferential wall 3, the height 1 of which is approximately five times as great as the initial thickness d 1 .
- the taper runs linearly, ie the inside of the circumferential wall 3 is flat and, based on embodiments without tapering of the circumferential wall 3, is inclined by an angle ⁇ .
- the inclination angle ⁇ of the cooling channels 11 is selected to be smaller such that the cooling channels 11 extend closer to the outside of the rubbing edge 7, whereby the convective cooling of the rubbing edge 7 is improved.
- the transition area to the crown bottom 4 is rounded, the curvature being defined by a radius of curvature r 2 , which can deviate from the radius of curvature r 1 of embodiments without tapering the circumferential wall 3.
- a radius of curvature r 2 is shown, which is approximately twice as large as r 1 .
- the transition area of the taper facing away from the crown bottom 4 is rounded to avoid an edge, the rounding being defined by a radius of curvature r 3 .
- the Figure 7 Fig. 3 shows a moving blade for a gas turbine according to a fifth embodiment of the present invention. It has the same basic structure as the previously described embodiments.
- the cooling channels are inclined in relation to a plane perpendicular to the radial direction R in the direction of the trailing edge of the rotor blade.
- the third angles of inclination ⁇ are measured in the direction of the trailing edge of the rotor blade in a plane which perpendicularly intersects the measuring plane of the first angle of inclination ⁇ and are 45 °.
- the cooling channels 11 have a greater length, as a result of which the convective cooling of the rubbing edge 7 is improved.
- the Figure 8 Fig. 3 shows a moving blade for a gas turbine according to a sixth embodiment of the present invention. It differs from the in Figure 7 Embodiments illustrated in that further cooling channels 11 are provided, which are inclined with respect to a plane perpendicular to the radial direction R in the direction of the leading edge of the rotor blade.
- the fourth angles of inclination ⁇ are measured in the direction of the leading edge of the rotor blade in a plane which perpendicularly intersects the measuring plane of the first angle of inclination ⁇ and are 45 °.
- the cooling channels 11 of different directions of inclination penetrate one another.
- the fourth angle of inclination ⁇ can also be selected to differ from the third angle of inclination ⁇ .
- the cooling channels 11 are not or only slightly clogged by material removal from the end face 7b of the rubbing edge 7. This ensures constant cooling of the rubbing edge 7 during operation of the gas turbine and thus a long service life of the rotor blade.
- Another advantage of the rotor blade according to the invention can be seen in the simple manufacture of the recess 9 and the cooling channels 11. Due to the small depth of the recess 9, effective cooling of the abrading edge 7 remains possible over its entire height h. In addition, the cooling fluid flowing out of the cooling fluid outlet openings 12 is hardly deflected on its short path to the outside step of the rubbing edge 7 during operation of the gas turbine, which is associated with effective cooling of the blade tip 5.
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Description
Die vorliegende Erfindung betrifft eine Laufschaufel für eine Gasturbine mit den Merkmalen des Anspruchs 1.The present invention relates to a rotor blade for a gas turbine having the features of claim 1.
In einer Gasturbinenanlage wird thermische Energie und/oder Strömungsenergie eines durch Verbrennung eines Brennstoffs erzeugten Heißgases in Rotationsenergie umgewandelt, die meist mittels eines Generators in elektrische Energie konvertiert wird. Dazu besitzt die Gasturbinenanlage einen Strömungskanal, in dessen axialer Richtung ein Turbinenläufer drehbar gelagert ist. Dieser umfasst eine Mehrzahl von Radscheiben, an deren radial äußeren Stirnflächen jeweils eine Mehrzahl von Laufschaufeln in Form eines Schaufelkranzes angeordnet sind. Die Laufschaufeln weisen hierzu jeweils Schaufelfüße auf, die in eine oder mehrere an den Stirnflächen der Radscheiben ausgebildete Aufnahmenuten eingesetzt und darin festgelegt sind.In a gas turbine system, thermal energy and / or flow energy of a hot gas generated by burning a fuel is converted into rotational energy, which is usually converted into electrical energy by means of a generator. For this purpose, the gas turbine system has a flow channel, in the axial direction of which a turbine rotor is rotatably mounted. This comprises a plurality of wheel disks, on the radially outer end faces of which a plurality of rotor blades are arranged in the form of a blade ring. For this purpose, the rotor blades each have blade roots which are inserted into one or more receiving grooves formed on the end faces of the wheel disks and are fixed therein.
An der Oberseite der Schaufelfüße sind Schaufelplattformen ausgebildet, von deren von der Radscheibe weg weisenden Außenseiten Schaufelblätter in den Strömungskanal vorstehen. Während des Betriebs der Gasturbinenanlage wird der Strömungskanal von dem Heißgas durchströmt, wobei das strömende Heißgas die Laufschaufeln mit einer Kraft beaufschlagt, die aufgrund der Form der Schaufelblätter in ein auf den Turbinenläufer wirkendes Drehmoment umgewandelt wird, das den Turbinenläufer rotierend antreibt.Blade platforms are formed on the upper side of the blade roots, from the outer sides of which facing away from the wheel disk blade blades protrude into the flow channel. During the operation of the gas turbine system, the hot gas flows through the flow channel, the flowing hot gas applying a force to the rotor blades which, due to the shape of the blade blades, is converted into a torque acting on the turbine rotor, which drives the turbine rotor to rotate.
Der thermodynamische Wirkungsgrad von Gasturbinenanlagen ist umso größer, je höher die Heißgastemperatur in der Gasturbinenanlage ist. Der Höhe der Heißgastemperatur sind jedoch Grenzen durch die thermische Belastbarkeit der Laufschaufeln gesetzt. Dementsprechend besteht eine Zielsetzung darin, Laufschaufeln zu schaffen, die auch bei hohen thermischen Belastungen eine für den Betrieb der Gasturbinenanlage ausreichende mechanische Festigkeit besitzen. Hierzu werden Laufschaufeln mit aufwendigen Beschichtungssystemen versehen. Zur weiteren Erhöhung der maximal zulässigen Heißgastemperatur werden Laufschaufeln während des Betriebs der Gasturbinenanlage gekühlt. Dazu sind in ihrem Inneren Hohlräume und Kühlkanäle ausgebildet, die von einem Kühlfluid, zumeist Luft durchströmt werden. Gängige Kühlverfahren sind beispielsweise die Prallkühlung, bei der das Kühlfluid derart geführt wird, dass es von innen auf die Wandung des Schaufelblatts prallt, oder die Filmkühlung, bei der das Kühlfluid durch in dem Schaufelblattkörper ausgebildete Kühlbohrungen aus dem Inneren des Schaufelblatts nach außen strömt, um an dessen Außenseite einen Kühlfilm zu bilden Aus der
So ist es beispielsweise aus der
Nach einer gewissen Betriebsdauer der Turbinenanlage kann es zu Veränderungen des Radialspalts kommen. Beispielsweise kann der Turbinenläufer durch Kriechen seine ursprünglich zentrale Lage verlassen, die Länge der Laufschaufeln infolge der Zentrifugalkraft zunehmen oder sich ein ursprünglich kreisrunder Strömungskanal ovalisieren. Diese Effekte resultieren aus einem Setzen und/oder einer Längung infolge thermischer Belastung durch das Heißgas und/oder von rotationsbedingten Fliehkräften beziehungsweise der Schwerkraft. Der dadurch bewirkte Kontakt zwischen den Stirnflächen der Anstreifkanten und der Kanalwandung führt zu einem reibungsbedingten Abtrag von Material in Form von Metallstaub oder Metallspänen von den Anstreifkanten. Dann können sich die Kühlfluidaustrittsöffnungen mit dem abgetragenen Schaufelblattmaterial zusetzen, wodurch ein Kühlen der Anstreifkanten beeinträchtigt oder verhindert wird. Die unzureichende Kühlung der Anstreifkanten führt zu einem höheren Verschleiß und folglich zu einer geringeren Lebensdauer der Schaufelblätter.Changes in the radial gap can occur after the turbine system has been in operation for a certain period of time. For example, the turbine runner can leave its originally central position by creeping, the length of the rotor blades can increase as a result of the centrifugal force or an originally circular flow channel can be ovalized. These effects result from settling and / or elongation as a result of thermal loading from the hot gas and / or from centrifugal forces or gravity caused by rotation. The resulting contact between the end faces of the rubbing edges and the duct wall leads to a friction-related removal of material in the form of metal dust or metal chips from the rubbing edges. The cooling fluid outlet openings with the removed airfoil material can then become clogged, as a result of which cooling of the abrading edges is impaired or prevented. The inadequate cooling of the rubbing edges leads to greater wear and, consequently, to a shorter service life of the airfoils.
Ausgehend von diesem Stand der Technik ist es eine Aufgabe der vorliegenden Erfindung, eine Laufschaufel für eine Gasturbine der eingangs genannten Art zu schaffen, die einen alternativen Aufbau besitzt und eine zuverlässige Kühlung der Anstreifkante ermöglicht.Based on this prior art, it is an object of the present invention to create a rotor blade for a gas turbine of the type mentioned at the beginning, which has an alternative structure and enables reliable cooling of the abrading edge.
Zur Lösung dieser Aufgabe schafft die vorliegende Erfindung eine Laufschaufel für eine Gasturbine der eingangs genannten Art, bei der in der Stirnfläche der Anstreifkante wenigstens eine Vertiefung ausgebildet ist, in die zumindest ein Teil der Kühlkanäle derart mündet, dass die Kühlfluidaustrittsöffnungen vollständig in einem Bodenbereich der wenigstens einen Vertiefung liegen.To solve this problem, the present invention creates a rotor blade for a gas turbine of the type mentioned at the outset, in which at least one recess is formed in the end face of the rubbing edge, into which at least some of the cooling channels open in such a way that the cooling fluid outlet openings are completely in a bottom area of the at least lie a depression.
Der Erfindung liegt die Überlegung zugrunde, die Kühlfluidaustrittsöffnungen bezogen auf die radiale Richtung gegenüber der Stirnfläche der Anstreifkante abzusenken. Dies wird erfindungsgemäß dadurch bewirkt, dass in der Stirnfläche der Anstreifkante wenigstens eine Vertiefung ausgebildet ist und zumindest ein Teil der Kühlaustrittsöffnungen vollständig in einem Bodenbereich der wenigstens einen Vertiefung angeordnet sind. Auf diese Weise sind die Kühlfluidaustrittsöffnungen von dem Kontaktbereich zwischen der Stirnfläche der Anstreifkante und der Kanalwandung entfernt, wodurch ein Zusetzen der Kühlfluidaustrittsöffnungen mit abgetragenem Schaufelblattmaterial reduziert oder verhindert wird. Infolge dessen bleibt die Kühlleistung über die Betriebsdauer der Gasturbinenanlage im Wesentlichen erhalten, was mit einer entsprechend langen Lebensdauer der Schaufelblätter einhergeht.The invention is based on the idea of lowering the cooling fluid outlet openings in relation to the radial direction with respect to the end face of the rubbing edge. According to the invention, this is achieved in that at least one recess is formed in the end face of the rubbing edge and at least some of the cooling outlet openings are arranged completely in a bottom area of the at least one recess. In this way, the cooling fluid outlet openings are removed from the contact area between the end face of the rubbing edge and the duct wall, as a result of which clogging of the cooling fluid outlet openings with removed airfoil material is reduced or prevented. As a result, the cooling capacity is essentially retained over the operating time of the gas turbine system, which is associated with a correspondingly long service life of the blades.
Weiter ist der Bodenbereich der wenigstens einen Vertiefung bezogen auf die radiale Richtung zwischen der Stirnfläche der Anstreifkante und der Außenfläche des Kronenbodens angeordnet. Vorzugsweise ist dabei der Bodenbereich als eine flache Bodenfläche ausgebildet, die gegenüber der Stirnfläche eine Tiefe besitzt, die im Bereich von 0,5 mm bis 4,5 mmm und bevorzugt im Bereich von 0,5 mm bis 2,5 mm liegt. Eine solche radiale Position des Bodenbereichs bewirkt einerseits, dass die Kühlfluidaustrittsöffnungen in unmittelbarer Nähe des freien Endbereichs der Anstreifkante angeordnet sind, wodurch sich eine effektive Kühlung dieses Bereichs der Anstreifkante gewährleisten lässt. Die geringe Tiefe der Bodenfläche der Vertiefung gegenüber der Stirnfläche reicht andererseits aus, um zu verhindern, dass von der Stirnfläche abgetragene Materialpartikel die Kühlfluidaustrittsöffnungen zusetzen, was mit einer gleichbleibenden Kühlleistung einhergeht.Furthermore, the base area of the at least one depression is arranged between the end face of the rubbing edge and the outer surface of the crown base in relation to the radial direction. The bottom area is preferably designed as a flat bottom surface which, compared to the end face, has a depth which is in the range from 0.5 mm to 4.5 mm and preferably in the range from 0.5 mm to 2.5 mm. Such a radial position of the bottom area has the effect, on the one hand, that the cooling fluid outlet openings are arranged in the immediate vicinity of the free end area of the abrading edge, as a result of which effective cooling of this area of the abrading edge can be ensured. On the other hand, the small depth of the bottom surface of the recess compared to the front surface is sufficient in order to prevent material particles removed from the end face from clogging the cooling fluid outlet openings, which is associated with a constant cooling performance.
In bekannter Weise besitzt die Anstreifkante bezogen auf die radiale Richtung gegenüber der Außenfläche des Kronenbodens eine Gesamthöhe, die im Bereich von 1 mm bis 10 mm, vorteilhaft im Bereich von 1,5 mm bis 6 mm liegt und bevorzugt 3,5 mm beträgt. In Anstreifkanten mit einer Gesamthöhe in diesem Bereich lassen sich Vertiefungen mit geeigneter Tiefe ohne Weiteres ausbilden.In a known manner, the rubbing edge has a total height in relation to the radial direction relative to the outer surface of the crown base which is in the range from 1 mm to 10 mm, advantageously in the range from 1.5 mm to 6 mm and preferably 3.5 mm. In rubbing edges with a total height in this area, depressions with a suitable depth can easily be formed.
Darüber hinaus ist eine Innenfläche der Anstreifkante gegenüber der radialen Richtung nach außen unter Ausbildung eines ersten Neigungswinkels geneigt sowie längs der Radialrichtung betrachtet größtenteils gerade, wobei der erste Neigungswinkel in einer sich in radialer Richtung erstreckenden Ebene gemessen wird, welche die Anstreifkante senkrecht durchschneidet, und in dem Bereich von 0° bis 45° liegt und bevorzugt mehr als 10° und/oder weniger als 30° beträgt. Infolge der Neigung der Innenfläche der Anstreifkante verbreitert sich die Anstreifkante von der Stirnfläche in Richtung des Kronenbodens. Dies verbessert die Stabilität der Anstreifkante und verbessert zusätzlich den Wärmetransport zwischen der Anstreifkante und dem Kronenboden beziehungsweise der Umfangswandung.In addition, an inner surface of the rubbing edge is inclined outwardly with respect to the radial direction, forming a first angle of inclination, and is largely straight when viewed along the radial direction, the first angle of inclination being measured in a plane extending in the radial direction, which perpendicularly intersects the rubbing edge, and in is in the range from 0 ° to 45 ° and is preferably more than 10 ° and / or less than 30 °. As a result of the inclination of the inner surface of the abrading edge, the abrading edge widens from the end face in the direction of the crown base. This improves the stability of the abrading edge and additionally improves the heat transfer between the abrading edge and the crown base or the peripheral wall.
Zudem erstreckt sich die wenigstens eine Vertiefung unter Bildung eines abgestuften Querschnitts bis zu einer Innenseite der Anstreifkante, wobei insbesondere eine Stufenecke des Querschnitts, bevorzugt die Innenecke abgerundet ist. Bei dieser Ausgestaltung ist wenigstens eine Vertiefung zur Innenseite hin offen ausgebildet. Derartige Vertiefungen können bereits während des Gießens des Schaufelblattkörpers oder erst nachträglich beispielsweise durch Fräsen oder Erodieren einfach hergestellt werden.In addition, the at least one depression extends to an inside of the rubbing edge, forming a stepped cross section, wherein in particular a step corner of the cross section, preferably the inside corner, is rounded. In this embodiment, at least one recess is designed to be open to the inside. Such depressions can be produced simply during the casting of the airfoil body or only afterwards, for example by milling or eroding.
Weiter sind zumindest einige Kühlkanäle gegenüber einer zu der radialen Richtung senkrechten Ebene in Richtung der Anströmkante der Laufschaufel oder in Richtung der Abströmkante der Laufschaufel unter Ausbildung eines vierten Neigungswinkels geneigt, wobei der vierte Neigungswinkel in Richtung der Anströmkante der Laufschaufel jeweils in einer Ebene, welche die Messebene des ersten Neigungswinkels senkrecht schneidet, gemessen werden, im Bereich zwischen 30° und 80° liegen und insbesondere 45° betragen. Kühlkanäle mit einer solchen Neigung in Richtung der Anströmkante oder in Richtung der Abströmkante weisen eine größere Länge auf, wodurch sich die konvektive Kühlung der Anstreifkante verbessern kann. Insbesondere durch eine zur Anströmkante geneigte Anordnung von Kühlkanälen werden die Strahlen über die Spitzen der saugseitigen Anstreifkante geführt und kühlen dort die Oberfläche, wo sie in der Regel am heißesten wird. Zudem können sie die Strömungsrichtung des austretenden Kühlfluids günstig beeinflussen. Kühlkanäle unterschiedlicher Neigungsrichtungen können sich durchdringen oder ohne Durchdringung kreuzen.Furthermore, at least some cooling channels are opposite a plane perpendicular to the radial direction in the direction of the leading edge of the rotor blade or inclined in the direction of the trailing edge of the rotor blade with the formation of a fourth angle of inclination, the fourth angle of inclination in the direction of the leading edge of the rotor blade being measured in a plane which perpendicularly intersects the measuring plane of the first angle of inclination, in the range between 30 ° and 80 ° and in particular 45 °. Cooling channels with such an inclination in the direction of the leading edge or in the direction of the trailing edge have a greater length, as a result of which the convective cooling of the abrading edge can be improved. In particular, by an arrangement of cooling channels inclined towards the leading edge, the jets are guided over the tips of the rubbing edge on the suction side and cool the surface where it is usually hottest. In addition, they can favorably influence the direction of flow of the exiting cooling fluid. Cooling channels with different directions of inclination can penetrate one another or cross without penetration.
Bevorzugt besitzt in dem Bereich der wenigstens einen Vertiefung die Stirnfläche der Anstreifkante eine Breite, die geringer ist als die Dicke der Umfangswandung des Schaufelblattkörpers in dem Bereich der wenigstens einen Vertiefung. Dazu kann in dem Bereich der Vertiefung die Stirnfläche der Anstreifkante eine Breite besitzen, die geringer ist als die Breite des Bodenbereichs der wenigstens einen Vertiefung. Auf diese Weise bildet nur ein relativ schmaler Außenbereich der Anstreifkante deren radial äußeren Endbereich.In the region of the at least one recess, the end face of the rubbing edge preferably has a width which is less than the thickness of the circumferential wall of the blade body in the region of the at least one recess. For this purpose, in the region of the recess, the end face of the rubbing edge can have a width which is less than the width of the bottom region of the at least one recess. In this way, only a relatively narrow outer area of the abrading edge forms its radially outer end area.
Weiter sind die Kühlkanäle gegenüber der radialen Richtung quer zu der Innenfläche der Anstreifkante unter Ausbildung eines zweiten Neigungswinkels geneigt, wobei insbesondere die zweite Neigungswinkel der Kühlkanäle, die jeweils in einer sich in radialer Richtung erstreckenden Ebene gemessen werden, welche die Anstreifkante senkrecht durchschneidet, gleich oder etwa gleich dem ersten Neigungswinkel der Innenfläche der Anstreifkante sind. Kühlkanäle mit einer solchen Neigung leiten das aus den Kühlfluidaustrittsöffnungen austretende Kühlfluid von innen zu dem äußeren Endbereich der Anstreifkante.Furthermore, the cooling channels are inclined relative to the radial direction transversely to the inner surface of the rubbing edge with the formation of a second angle of inclination, in particular the second inclination angle of the cooling channels, which are each measured in a plane extending in the radial direction, which perpendicularly intersects the rubbing edge, equal to or are approximately equal to the first angle of inclination of the inner surface of the rubbing edge. Cooling channels with such an inclination lead this out of the cooling fluid outlet openings exiting cooling fluid from the inside to the outer end area of the scraper edge.
Vorteilhaft besitzen in dem Bereich der wenigstens einen Vertiefung die Stirnfläche der Anstreifkante und der Bodenbereich der wenigstens einen Vertiefung gemeinsam eine Breite, die etwa gleich der Dicke der Umfangswandung des Schaufelblattkörpers in dem Bereich der wenigstens einen Vertiefung ist. Derartige Anstreifkanten stellen im Wesentlichen eine Fortsetzung der Umfangswandung des Schaufelblattkörpers über den Kronenboden hinaus dar.Advantageously, in the area of the at least one recess, the end face of the rubbing edge and the bottom area of the at least one recess jointly have a width that is approximately equal to the thickness of the circumferential wall of the blade body in the area of the at least one recess. Such rubbing edges essentially represent a continuation of the circumferential wall of the blade body beyond the crown base.
Alternativ kann die Vertiefung in der Stirnfläche der Anstreifkante als Nut unter Belassung eines außenseitigen Stirnflächenabschnitts und eines innenseitigen Stirnflächenabschnitts ausgebildet sein, wobei insbesondere die Innenecken der Vertiefung abgerundet sind.Alternatively, the recess in the end face of the rubbing edge can be designed as a groove leaving an outside end face section and an inside end face section, in particular the inner corners of the recess being rounded.
In diesem Fall können in dem Bereich der Vertiefung die Breite des außenseitigen Stirnflächenabschnitts und die Breite des innenseitigen Stirnflächenabschnitts der Anstreifkante jeweils im Bereich von 0,5 mm bis 5 mm liegen und bevorzugt mindestens 1 mm betragen, wobei das Verhältnis zwischen der außenseitigen Breite und der innenseitigen Breite im Bereich zwischen 0,7 mm und 1,3 mm, insbesondere 0,9 und 1,1 liegt und bevorzugt 1 ist.In this case, the width of the outside end face section and the width of the inside end face section of the abrading edge can each be in the range of 0.5 mm to 5 mm and preferably at least 1 mm, the ratio between the outside width and the inside width is in the range between 0.7 mm and 1.3 mm, in particular 0.9 and 1.1, and is preferably 1.
Gemäß einer weiteren Variante verjüngt sich in dem Bereich der Vertiefung die Umfangswandung in Richtung des Kronenbodens zugunsten des Hohlraums, wobei sich die Dicke der Umfangswandung von einer Ausgangsdicke auf eine verjüngte Dicke reduziert, die mindestens halb so groß wie die Ausgangsdicke ist, und die Verjüngung über einen radialen Abschnitt der Umfangswandung erfolgt, dessen Höhe mindestens fünfmal und höchstens zehnmal so groß ist wie die Ausgangsdicke. Infolge der reduzierten Dicke der Umfangswandung unmittelbar unterhalb des Kronenbodens können die Kühlkanäle derart ausgebildet sein, dass sie sich näher zu der Außenseite der Anstreifkante erstrecken, was mit einer verbesserten konvektiven Kühlung der Anstreifkante einhergeht.According to a further variant, the circumferential wall tapers in the area of the recess in the direction of the crown base in favor of the cavity, the thickness of the circumferential wall being reduced from an initial thickness to a tapered thickness that is at least half as large as the initial thickness, and the tapering over a radial section of the peripheral wall takes place, the height of which is at least five times and at most ten times as great as the initial thickness. As a result of the reduced thickness of the circumferential wall directly below the crown base, the cooling channels can be designed in such a way that they extend closer to the outside of the abrading edge, which is accompanied by improved convective cooling of the abrading edge.
Vorteilhaft sind in der wenigstens einen Vertiefung die Kühlfluidaustrittsöffnungen nebeneinander und beabstandet zueinander insbesondere äquidistant und/oder entlang einer Linie angeordnet. Derartig angeordnete Kühlfluidaustrittsöffnungen eignen sich in besonderem Maße dazu, die Anstreifkante entlang Ihrer umfänglichen Erstreckung zu kühlen. Grundsätzlich können die Kühlfluidaustrittsöffnungen aber beliebig verteilt sein.In the at least one recess, the cooling fluid outlet openings are advantageously arranged next to one another and at a distance from one another, in particular equidistantly and / or along a line. Cooling fluid outlet openings arranged in this way are particularly suitable for cooling the abrading edge along its circumferential extent. In principle, however, the cooling fluid outlet openings can be distributed as desired.
Bei einer erfindungsgemäßen Laufschaufel kann die wenigstens eine Vertiefung nur in einem von dem saugseitigen Wandabschnitt der Umgebungswandung abragenden Abschnitt der Anstreifkante vorgesehen sein. Auf diese Weise lässt sich die Kühlung des von dem saugseitigen Wandabschnitt der Umfangswandung abragenden Abschnitts der Anstreifkante verbessern.In the case of a rotor blade according to the invention, the at least one depression can only be provided in a section of the rubbing edge that protrudes from the suction-side wall section of the surrounding wall. In this way, the cooling of the section of the rubbing edge protruding from the suction-side wall section of the peripheral wall can be improved.
In einer Variante der vorliegenden Erfindung ist genau eine Vertiefung vorgesehen. Dies führt zu einer besonders einfachen Ausführungsform einer erfindungsgemäßen Laufschaufel.In a variant of the present invention, exactly one recess is provided. This leads to a particularly simple embodiment of a rotor blade according to the invention.
Alternativ dazu kann eine Mehrzahl von in der Umfangsrichtung nebeneinander angeordneten Vertiefungen vorgesehen sein, in die jeweils ein Teil der Kühlkanäle mündet und die insbesondere jeweils wenigstens ein oben genanntes Merkmal aufweisen. Mehrere Vertiefungen führen zu einer entsprechenden Gruppierung der Kühlkanäle.As an alternative to this, a plurality of depressions arranged next to one another in the circumferential direction can be provided, into each of which a part of the cooling channels opens and which in particular each have at least one feature mentioned above. Several depressions lead to a corresponding grouping of the cooling channels.
Gemäß einer Variante erstreckt sich jeder Kühlkanal geradlinig und/oder besitzt einen kreisförmigen Querschnitt mit einem Durchmesser, der im Bereich von 0,25 mm bis 2 mm liegt und bevorzugt 0,6 mm beträgt.According to a variant, each cooling channel extends in a straight line and / or has a circular cross section with a diameter which is in the range from 0.25 mm to 2 mm and is preferably 0.6 mm.
Dabei können die Kühlkanäle im Bereich der Kühlfluidaustrittsöffnungen aufgeweitet sein, wobei die Aufweitungen insbesondere die Form eines Zylinders besitzen, dessen Höhe höchstens fünfmal, bevorzugt ebenso groß ist wie der Durchmesser des Kühlkanals und/oder dessen Durchmesser höchstens dreimal, bevorzugt doppelt so groß ist wie der Durchmesser des Kühlkanals. Derartig aufgeweitete Kühlfluidaustrittsöffnungen können als Diffusor wirken und den austretenden Kühlfluidstrom entsprechend aufweiten, sodass nach dem Prinzip der Filmkühlung ein großer Bereich der Anstreifkante gekühlt werden kann. Alternativ zu der zylindrischen Form können die Kühlfluidaustrittsöffnungen auch konisch, halb-konisch oder fächerartig aufgeweitet sein.The cooling ducts can be widened in the area of the cooling fluid outlet openings, the widenings in particular having the shape of a cylinder whose height is at most five times, preferably as large as the diameter of the cooling duct and / or its diameter is at most three times, preferably twice as large as that Diameter of the cooling channel. Such widened cooling fluid outlet openings can act as a diffuser and expand the exiting cooling fluid flow accordingly, so that a large area of the rubbing edge can be cooled according to the principle of film cooling. As an alternative to the cylindrical shape, the cooling fluid outlet openings can also be widened conically, semi-conically or in a fan-like manner.
Vorteilhaft sind die Kühlkanäle als Bohrungen ausgebildet. Durch Bohren lassen sich geradlinige Kühlkanäle mit kreisförmigem Querschnitt einfach in einen gegossenen Schaufelblattkörper einbringen.The cooling channels are advantageously designed as bores. Rectilinear cooling channels with a circular cross section can easily be introduced into a cast airfoil body by drilling.
Gemäß einer Weiterentwicklung ist ein Übergangsbereich zwischen einer Innenfläche der Anstreifkante und der Außenfläche des Kronenbodens abgerundet. Die verbessert die aerodynamischen Eigenschaften der Schaufelspitze. Ansonsten ist die Innenfläche der Anstreifkante längs der Radialrichtung betrachtet, größtenteils gerade.According to a further development, a transition area between an inner surface of the rubbing edge and the outer surface of the crown base is rounded. Which improves the aerodynamic Blade tip properties. Otherwise, the inner surface of the abradable edge, viewed along the radial direction, is largely straight.
In an sich bekannter Weise ist der Schaufelblattkörper durch Gießen oder in einem generativen Verfahren, insbesondere mittels 3D-Drucken hergestellt. Gießen hat sich insbesondere für gekühlte Schaufelblätter mit einem Hohlraum in ihrem Inneren als ein geeignetes Herstellungsverfahren herausgestellt. Aber auch generative Verfahren sind zur Herstellung von Schaufelblattkörpern geeignet.In a manner known per se, the airfoil body is produced by casting or in a generative process, in particular by means of 3D printing. Casting has proven to be a suitable manufacturing process, particularly for cooled airfoils with a cavity in their interior. But generative processes are also suitable for the production of airfoil bodies.
Weitere Vorteile und Merkmale der vorliegenden Erfindung werden anhand von sechs Ausführungsformen einer erfindungsgemäßen Laufschaufel unter Bezugnahme auf die beiliegende Zeichnung deutlich. Darin ist:
- Figur 1
- eine perspektivische Teilansicht eines Schaufelblatts einer Laufschaufel gemäß einer ersten Ausführungsform der vorliegenden Erfindung;
- Figur 2
- eine vergrößerte Teilansicht der in der
Figur 1 dargestellten Laufschaufel; Figur 3- eine vergrößerte Querschnittsansicht der in
Figur 2 dargestellten Laufschaufel entlang der mit III bezeichneten Linie; Figur 4- eine vergrößerte Querschnittsansicht eines Schaufelblatts einer Laufschaufel gemäß einer zweiten Ausführungsform der vorliegenden Erfindung, die
der Figur 3 entspricht; Figur 5- eine vergrößerte Querschnittsansicht eines Schaufelblatts einer Laufschaufel gemäß einer dritten Ausführungsform der vorliegenden Erfindung, die
der Figur 3 entspricht; Figur 6- eine vergrößerte Querschnittsansicht eines Schaufelblatts einer Laufschaufel gemäß einer vierten Ausführungsform der vorliegenden Erfindung, die
der Figur 3 entspricht; - Figur 7
- eine vergrößerte Teilansicht eines Schaufelblatts einer Laufschaufel gemäß einer fünften Ausführungsform der vorliegenden Erfindung, die der
Figur 2 entspricht; und Figur 8- eine vergrößerte Teilansicht eines Schaufelblatts einer Laufschaufel gemäß einer sechsten Ausführungsform der vorliegenden Erfindung, die der
Figur 2 entspricht.
- Figure 1
- a partial perspective view of an airfoil of a rotor blade according to a first embodiment of the present invention;
- Figure 2
- an enlarged partial view of the in FIG
Figure 1 illustrated blade; - Figure 3
- an enlarged cross-sectional view of the FIG
Figure 2 illustrated rotor blade along the line designated III; - Figure 4
- FIG. 8 is an enlarged cross-sectional view of an airfoil of a rotor blade according to a second embodiment of the present invention, which is shown in FIG
Figure 3 corresponds to; - Figure 5
- FIG. 8 is an enlarged cross-sectional view of an airfoil of a moving blade according to a third embodiment of the present invention, which is shown in FIG
Figure 3 corresponds to; - Figure 6
- FIG. 10 is an enlarged cross-sectional view of an airfoil of a moving blade according to a fourth embodiment of the present invention, which is shown in FIG
Figure 3 corresponds to; - Figure 7
- FIG. 8 is an enlarged partial view of an airfoil of a moving blade according to a fifth embodiment of the present invention, which is shown in FIG
Figure 2 corresponds to; and - Figure 8
- FIG. 8 is an enlarged partial view of an airfoil of a moving blade according to a sixth embodiment of the present invention, which is shown in FIG
Figure 2 corresponds to.
Die
Weiterhin umfasst der Schaufelblattkörper 2 eine Anstreifkante 7. Die Anstreifkante 7 erstreckt sich entlang der Umfangswandung 3 und fluchtet außenseitig mit dieser. Dabei steht die Anstreifkante 7 radial über den Kronenboden 4 vor und besitzt bezogen auf die radiale Richtung R gegenüber der Außenfläche 4a des Kronenbodens eine Gesamthöhe h, die senkrecht zu der Außenfläche 4a des Kronenbodens gemessen wird und etwa 3 mm beträgt. Eine Innenfläche 7a der Anstreifkante 7 ist gemäß der Querschnittsansicht größtenteils geradlinig ausgestaltet und gegenüber der radialen Richtung R um einen ersten Neigungswinkel δ von ca. 25° geneigt, der in einer sich in radialer Richtung (R) erstreckenden Ebene gemessen wird, welche die Anstreifkante 7 senkrecht durchschneidet. Ein Übergangsbereich 8 zwischen der Innenfläche 7a der Anstreifkante 7 und der Außenfläche 4a des Kronenbodens 4 ist abgerundet ausgebildet.Furthermore, the airfoil body 2 comprises a rubbing edge 7. The rubbing edge 7 extends along the
In einem von dem saugseitigen Wandabschnitt der Umfangswandung 3 abragenden Abschnitt der Anstreifkante 7 ist eine Vertiefung 9 ausgebildet, die sich unter Bildung eines abgestuften Querschnitts bis zu der Innenseite der Anstreifkante 7 erstreckt. Dabei ist die Innenecke 10 des abgestuften Querschnitts abgerundet. Der Bodenbereich 9a der Vertiefung 9 ist als eine flache Bodenfläche ausgebildet und bezogen auf die radiale Richtung R zwischen der Stirnfläche 7b der Anstreifkante 7 und der Außenfläche 4a des Kronenbodens 4 angeordnet. Dabei erstrecken sich die Außenfläche 4a des Kronenbodens 4, die Bodenfläche 9a der Vertiefung 9 und Stirnfläche 7b der Anstreifkante 7 parallel zueinander und senkrecht zu der radialen Richtung R. Auf diese Weise besitzt die Vertiefung 9 gegenüber der Stirnfläche 7b eine Tiefe h1, die als senkrechter Abstand zwischen der Bodenfläche 9a und der Stirnfläche 7b gemessen wird und ca. 1 mm beträgt. Entsprechend beträgt die senkrecht gemessene Höhe h2 der Bodenfläche der Vertiefung 9 über der Außenfläche 4a des Kronenbodens 4 ca. 2 mm. Die Bodenfläche 9a der Vertiefung 9 und die Außenfläche 4a des Kronenbodens 4 können aber auch zueinander und/oder zu der radialen Richtung R geneigt sein, wobei die Tiefe h1 bzw. die Höhe h2 dann jeweils bezogen auf die Innenecke 10 zu bestimmen sind.In a section of the rubbing edge 7 protruding from the suction-side wall section of the
In dem Bereich der Vertiefung 9 besitzt die Stirnfläche 7b der Anstreifkante 7 eine Breite a1, die geringer ist als die Dicke d1 der Umfangswandung 3 des Schaufelblattkörpers 2 in dem Bereich der Vertiefung 9. Darüber hinaus ist die Breite a1 der Stirnfläche 7b der Anstreifkante 7 in dem Bereich der Vertiefung 9 geringer als die Breite b1 des Bodenbereichs 9a der Vertiefung 9. Gemeinsam besitzen die Stirnfläche 7b der Anstreifkante 7 und der Bodenbereich 9a der Vertiefung 9 eine Breite a1+b1, die etwa gleich der Dicke d1 der Umfangswandung 3 des Schaufelblattkörpers 2 in dem Bereich der Vertiefung 9 ist, wobei die Dicke d1 als senkrechter Abstand zwischen der Außenfläche und der Innenfläche der Umgebungswandung 3 gemessen wird. Wie der
In dem Schaufelblattkörper 2 sind Kühlkanäle 11 ausgebildet, die sich ausgehend vom dem Hohlraum 6 zu Kühlfluidaustrittsöffnungen 12 erstrecken, die in der Anstreifkante 7 vorgesehen sind. Die Kühlkanäle 11 münden derart in die Vertiefung 9, dass die Kühlfluidaustrittsöffnungen 12 vollständig in dem Bodenbereich 9a der Vertiefung 9 angeordnet sind. Dabei sind die Kühlfluidaustrittsöffnungen 12 in der Vertiefung 9 äquidistant und entlang einer Linie nebeneinander angeordnet. Jeder Kühlkanal 11 ist als Bohrung ausgebildet und erstreckt sich geradlinig. Er besitzt einen kreisförmigen Querschnitt mit einem Durchmesser, der etwa 0,6 mm beträgt. Jeder Kühlkanal 11 ist gegenüber der radialen Richtung R quer zu der Innenfläche 7a der Anstreifkante 7 geneigt, wobei die zweiten Neigungswinkel θ der Kühlkanäle 11, die jeweils in einer sich in radialer Richtung R erstreckenden Ebene gemessen werden, welche die Anstreifkante 7 senkrecht durchschneidet, etwa gleich dem ersten Neigungswinkel δ der Innenfläche 7a der Anstreifkante 7 sind.In the airfoil body 2, cooling
Die
Die
Die
Die
Die
Ein Vorteil der erfindungsgemäßen Laufschaufel besteht darin, dass die Kühlkanäle 11 nicht oder nur geringfügig durch Materialabtrag von der Stirnfläche 7b der Anstreifkante 7 zugesetzt werden. Dies gewährleistet eine während des Betriebs der Gasturbine gleichbleibende Kühlung der Anstreifkante 7 und somit eine lange Lebensdauer der Laufschaufel. Ein weiterer Vorteil der erfindungsgemäßen Laufschaufel zeigt sich in der einfachen Herstellbarkeit der Vertiefung 9 sowie der Kühlkanäle 11. Aufgrund der geringen Tiefe der Vertiefung 9 bleibt eine effektive Kühlung der Anstreifkante 7 über ihre gesamte Höhe h möglich. Zudem wird das aus den Kühlfluidaustrittsöffnungen 12 strömende Kühlfluid auf seinem kurzen Weg zu der außenseitigen Stufe der Anstreifkante 7 während des Betriebs der Gasturbine kaum abgelenkt, was mit einer effektiven Kühlung der Schaufelspitze 5 einher geht.One advantage of the rotor blade according to the invention is that the cooling
Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele eingeschränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen.Although the invention has been illustrated and described in more detail by the preferred exemplary embodiment, the invention is not restricted by the disclosed examples and other variations can be derived therefrom by the person skilled in the art without departing from the scope of protection of the invention.
Claims (21)
- Rotor blade for a gas turbine, comprising a blade aerofoil (1) which extends in a radial direction (R) and which has a blade aerofoil body (2) having a peripheral wall (3) with a pressure-side wall section (3a) and with a suction-side wall section (3b), having a plate-like crown base (4) which is connected to the peripheral wall (3) in the region of the blade tip (5), and having a rubbing edge (7) which extends along the peripheral wall (3), wherein the peripheral wall (3) and the crown base (4) define a cavity (6) in the blade aerofoil body (2), and in the blade aerofoil body (2) there are formed cooling ducts (11) which extend from the cavity (6) to cooling fluid outlet openings (12) provided in the rubbing edge (7),
wherein, in the end surface (7b) of the rubbing edge (7), there is formed at least one depression (9) into which at least some of the cooling ducts (11) open such that the cooling fluid outlet openings (12) are situated completely in a base region (9a) of the depression (9),
wherein, with respect to the radial direction (R), the base region (9a) of the at least one depression (9) is arranged between the end surface (7b) of the rubbing edge (7) and the outer surface (4a) of the crown base (4),
wherein the at least one depression (9) extends as far as an inner side of the rubbing edge (7) so as to form a stepped cross section, and
wherein an inner surface (7a) of the rubbing edge (7) is, in relation to the radial direction (R), outwardly inclined so as to form a first inclination angle (δ) and is, as viewed along the radial direction, largely rectilinear, and measurement is carried out in a plane which extends in the radial direction (R) and which perpendicularly intersects the rubbing edge (7), wherein the cooling ducts (11) are, in relation to the radial direction (R), inclined so as to form a second inclination angle (θ), wherein the second inclination angles of the cooling ducts (11), which angles are each measured in a plane which extends in the radial direction (R) and which perpendicularly intersects the rubbing edge (7), are equal or approximately equal to the first inclination angle (δ) of the inner surface (7a) of the rubbing edge (7),
characterized in that the rubbing edge (7) is aligned on the outside with the peripheral wall (3) and projects radially above the crown base (4), wherein
the first inclination angle (δ) lies in the range of 0° to 45°, and
wherein each cooling duct (11) is, in relation to a plane which is perpendicular to the radial direction (R), inclined in the direction of the leading edge of the rotor blade, or in the direction of the trailing edge of the rotor blade, so as to form a third or a fourth inclination angle (α, β), wherein the third inclination angle (α) in the direction of the trailing edge of the rotor blade and the fourth inclination angle (β) in the direction of the leading edge of the rotor blade are each measured in a plane which perpendicularly intersects the measurement plane of the first inclination angle (δ) and each lie in the range between 30° and 80°, such that, due to the arrangement of cooling ducts (11) inclined towards the leading edge, the cooling jets thereof are, during operation, able to be conducted over the tip of the rubbing edge (7) arranged on the suction side. - Rotor blade according to Claim 1,
characterized in that
the base region (9a) is formed as a planar base surface which, in relation to the end surface (7b), has a depth (h1) which lies in the range of 0.5 mm to 4.5 mm and preferably in the range of 0.5 mm to 2.5 mm. - Rotor blade according to either of Claims 1 and 2,
characterized in that,
with respect to the radial direction (R), the rubbing edge (7) has, in relation to the outer surface (4a) of the crown base (4), an overall height (h) which lies in the range of 1 mm to 10 mm, advantageously in the range of 1.5 mm to 6 mm, and is preferably 3.5 mm, wherein a height h2 of the base surface of the depression (9) above the outer surface (4a) of the crown base (4) advantageously lies in the range between 60% and 80% of the overall height (h). - Rotor blade according to one of the preceding claims,
characterized in that
the first inclination angle (δ) is less than 30° and/or greater than 10°. - Rotor blade according to one of the preceding claims,
characterized in that
a step corner of the cross section, preferably the inner corner (10), is rounded. - Rotor blade according to Claim 5,
characterized in that,
in the region of the at least one depression (9), the end surface (7b) of the rubbing edge (7) has a width (a1) which is less than the thickness (d1) of the peripheral wall (3) of the blade aerofoil body (2) in the region of the at least one depression (9). - Rotor blade according to either of Claims 5 and 6,
characterized in that,
in the region of the at least one depression (9), the end surface (7b) of the rubbing edge (7) has a width (a1) which is less than the width (b1) of the base region (9a) of the at least one depression (9). - Rotor blade according to one of Claims 5 to 7,
characterized in that,
in the region of the at least one depression (9), the end surface (7b) of the rubbing edge (7) and the base region (9a) of the depression (9) have, in combination, a width (a1+b1) which is approximately equal to the thickness (d1) of the peripheral wall (3) of the blade aerofoil body (2) in the region of the at least one depression (9). - Rotor blade according to one of Claims 1 to 4,
characterized in that
the depression (9) in the end surface (7b) of the rubbing edge (7) is formed as a groove, with an outer end-surface section and an inner end-surface section being left in the process, wherein in particular, the inner corners (10) of the depression (9) are rounded. - Rotor blade according to Claim 9,
characterized in that,
in the region of the depression (9), the width (a2) of the outer end-surface section and the width (c2) of the inner end-surface section of the rubbing edge (7) each lie in the range of 0.5 mm to 5 mm and are preferably at least 1 mm, wherein the ratio between the outer width (a2) and the inner width (c2) lies in the range between 0.7 and 1.3, in particular 0.9 and 1.1, and is preferably 1. - Rotor blade according to one of the preceding claims,
characterized in that,
in the region of the depression (9), the peripheral wall (3) narrows in the direction of the crown base (4) in favour of the cavity (6), wherein the thickness of the peripheral wall (3) is reduced from an initial thickness (d1) to a narrowed thickness (d2) which is at least half as large as the initial thickness (d1), and wherein in particular, the narrowing occurs over a radial section of the peripheral wall (3), the height (1) of which radial section is at least five times and at most ten times as large as the initial thickness (d1). - Rotor blade according to one of the preceding claims,
characterized in that
the at least one depression (9) is provided only in a section of the rubbing edge (7) that projects from the suction-side wall section (3b) of the peripheral wall (3). - Rotor blade according to one of the preceding claims,
characterized in that
precisely one depression (9) is provided. - Rotor blade according to one of Claims 1 to 12,
characterized in that
there is provided a plurality of depressions (9) which are arranged mutually adjacently in the peripheral direction, into each of which some of the cooling ducts (11) open and which in particular have at least one feature from Claims 2 to 10. - Rotor blade according to one of the preceding claims,
characterized in that,
in the at least one depression (9), the cooling fluid outlet openings (12) are, in the peripheral direction, arranged mutually adjacently and spaced apart from one another, in particular in an equidistant manner and/or along a line. - Rotor blade according to one of the preceding claims,
characterized in that
each cooling duct (11) extends rectilinearly and/or has a circular cross section with a diameter which lies in the range of 0.25 mm to 2 mm and is preferably 0.6 mm. - Rotor blade according to one of the preceding claims,
characterized in that
the cooling ducts (11) are widened in the region of the cooling fluid outlet openings (12), wherein the widenings (12a) in particular have the form of a cylinder whose height (h5) is at most five times as large as, preferably as large as, the diameter of a cooling duct (11) and/or whose diameter (c5) is at most three times as large as, preferably twice as large as, the diameter of a cooling duct (11). - Rotor blade according to either of Claims 16 and 17,
characterized in that
the cooling ducts (11) are formed as bores. - Rotor blade according to Claim 16 to 18 and Claim 4,
characterized in that
the third and/or fourth inclination angle are/is 45°. - Rotor blade according to one of the preceding claims,
characterized in that
a transition region (8) between an inner surface (7a) of the rubbing edge (7) and the outer surface (4a) of the crown base (4) is rounded. - Rotor blade according to one of the preceding claims,
characterized in that
the blade aerofoil body (2) is produced by casting or in a generative process, in particular by means of 3D printing.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP16159107.8A EP3216983A1 (en) | 2016-03-08 | 2016-03-08 | Rotor blade for a gas turbine with cooled rubbing edge |
PCT/EP2017/054734 WO2017153219A1 (en) | 2016-03-08 | 2017-03-01 | Rotor blade for a gas turbne with a cooled sweep edge |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3400373A1 EP3400373A1 (en) | 2018-11-14 |
EP3400373B1 true EP3400373B1 (en) | 2021-04-28 |
Family
ID=55486583
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16159107.8A Withdrawn EP3216983A1 (en) | 2016-03-08 | 2016-03-08 | Rotor blade for a gas turbine with cooled rubbing edge |
EP17707889.6A Active EP3400373B1 (en) | 2016-03-08 | 2017-03-01 | Rotor blade for a gas turbine with cooled rubbing edge |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16159107.8A Withdrawn EP3216983A1 (en) | 2016-03-08 | 2016-03-08 | Rotor blade for a gas turbine with cooled rubbing edge |
Country Status (4)
Country | Link |
---|---|
US (1) | US11136892B2 (en) |
EP (2) | EP3216983A1 (en) |
CN (1) | CN209976583U (en) |
WO (1) | WO2017153219A1 (en) |
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US10436038B2 (en) | 2015-12-07 | 2019-10-08 | General Electric Company | Turbine engine with an airfoil having a tip shelf outlet |
CA2958459A1 (en) | 2016-02-19 | 2017-08-19 | Pratt & Whitney Canada Corp. | Compressor rotor for supersonic flutter and/or resonant stress mitigation |
CN109154200B (en) * | 2016-05-24 | 2021-06-15 | 通用电气公司 | Airfoil and blade for a turbine engine, and corresponding method of flowing a cooling fluid |
US11480057B2 (en) * | 2017-10-24 | 2022-10-25 | Raytheon Technologies Corporation | Airfoil cooling circuit |
JP6979382B2 (en) | 2018-03-29 | 2021-12-15 | 三菱重工業株式会社 | Turbine blades and gas turbines |
DE102020202891A1 (en) * | 2020-03-06 | 2021-09-09 | Siemens Aktiengesellschaft | Turbine Blade Tip, Turbine Blade, and Process |
US11608746B2 (en) * | 2021-01-13 | 2023-03-21 | General Electric Company | Airfoils for gas turbine engines |
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US5261789A (en) | 1992-08-25 | 1993-11-16 | General Electric Company | Tip cooled blade |
US5733102A (en) * | 1996-12-17 | 1998-03-31 | General Electric Company | Slot cooled blade tip |
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US7597539B1 (en) * | 2006-09-27 | 2009-10-06 | Florida Turbine Technologies, Inc. | Turbine blade with vortex cooled end tip rail |
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US8113779B1 (en) * | 2008-09-12 | 2012-02-14 | Florida Turbine Technologies, Inc. | Turbine blade with tip rail cooling and sealing |
US8066485B1 (en) * | 2009-05-15 | 2011-11-29 | Florida Turbine Technologies, Inc. | Turbine blade with tip section cooling |
US8182221B1 (en) * | 2009-07-29 | 2012-05-22 | Florida Turbine Technologies, Inc. | Turbine blade with tip sealing and cooling |
US8197211B1 (en) * | 2009-09-25 | 2012-06-12 | Florida Turbine Technologies, Inc. | Composite air cooled turbine rotor blade |
GB201006451D0 (en) * | 2010-04-19 | 2010-06-02 | Rolls Royce Plc | Blades |
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-
2016
- 2016-03-08 EP EP16159107.8A patent/EP3216983A1/en not_active Withdrawn
-
2017
- 2017-03-01 CN CN201790000656.0U patent/CN209976583U/en active Active
- 2017-03-01 WO PCT/EP2017/054734 patent/WO2017153219A1/en active Application Filing
- 2017-03-01 US US16/081,205 patent/US11136892B2/en active Active
- 2017-03-01 EP EP17707889.6A patent/EP3400373B1/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
US11136892B2 (en) | 2021-10-05 |
EP3216983A1 (en) | 2017-09-13 |
CN209976583U (en) | 2020-01-21 |
EP3400373A1 (en) | 2018-11-14 |
WO2017153219A1 (en) | 2017-09-14 |
US20200386104A1 (en) | 2020-12-10 |
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