EP3473808A1 - Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale - Google Patents

Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale Download PDF

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Publication number
EP3473808A1
EP3473808A1 EP17197244.1A EP17197244A EP3473808A1 EP 3473808 A1 EP3473808 A1 EP 3473808A1 EP 17197244 A EP17197244 A EP 17197244A EP 3473808 A1 EP3473808 A1 EP 3473808A1
Authority
EP
European Patent Office
Prior art keywords
rib
airfoil
cooling hole
cooling
cavity
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.)
Granted
Application number
EP17197244.1A
Other languages
German (de)
English (en)
Other versions
EP3473808B1 (fr
Inventor
Tobias Buchal
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP17197244.1A priority Critical patent/EP3473808B1/fr
Priority to US16/145,792 priority patent/US10746027B2/en
Publication of EP3473808A1 publication Critical patent/EP3473808A1/fr
Application granted granted Critical
Publication of EP3473808B1 publication Critical patent/EP3473808B1/fr
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Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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 invention relates to an airfoil for an internally cooled turbine blade according to the preamble of claim 1.
  • the invention further relates to a method for producing a blade.
  • Turbine blades and their blades are long known from the extensive existing state of the art.
  • they are designed to be coolable. They have to inside a cavity, which can be flowed through during operation of a coolant, usually cooling air.
  • a coolant usually cooling air.
  • the cooling air heated by flowing through is blown into the working fluid of the gas turbine and admixed thereto. If the cooling fluid is cooling air, this is taken from the compressor associated with the gas turbine.
  • this can continue to contain dust and dirt particles that can be deposited in it as it flows through the compressor and also when flowing through the turbine blade.
  • special shaped inlets can be used for cooling air openings. In this case, it is achieved by an ovalization of the inlet region of the cooling air hole that a entrained particle can not penetrate into the hole.
  • the disadvantage is that such hole enemas can not be produced on the inside of usually produced by investment casting blades by drilling, but only by casting.
  • the cooling air holes then have a comparatively large diameter of at least about 2 mm, which undesirably increases the cooling air consumption. Smaller diameters can not be produced with sufficient accuracy.
  • the object of the invention is therefore to provide an airfoil for an internally cooled turbine blade, the cooling holes has a lower tendency to fouling entrained in the cooling air particles.
  • Another object of the invention is to provide a method by means of which blades according to the invention can be produced simply and with increased reliability than heretofore.
  • This first object is achieved by an airfoil according to claim 1 and the second-mentioned object by a manufacturing method according to claim 11.
  • the present invention contemplates that in an airfoil for an internally cooled turbine blade, comprising a suction side sidewall and a pressure sidewall extending from a common leading edge to a common trailing edge and in a spanwise direction from a root end to a head end, at least one cavity partially enclose, wherein the head-side end comprises a top wall bounding the cavity top wall, in which at least one cooling hole, preferably a plurality of cooling holes for discharging internally flowable cooling fluid is or are in the cavity at least one of the top wall in the direction of the foot side Endrangende rib, preferably a plurality of such ribs, protruding from the inner surface of the suction-side side wall surrounding this rib or of the inner surface of the pressure-side side wall surrounding this rib and that a - related on the cooling fluid - inflow opening of the at least one cooling hole in the respective ribs opens laterally.
  • the invention is based on the finding that the lateral arrangement of the inflow opening of the cooling hole in a From the inner surface of the side wall protruding rib, the inflow of entrained in the cooling air particles significantly impeded. Due to the difficult influx of particles into the cooling hole, the risk of clogging decreases, which can increase the service life of the airfoil and a turbine blade equipped therewith.
  • the lateral arrangement of the inflow opening in the rib can be realized in the case of rectilinear cooling holes, when a channel axis of the cooling hole is arranged inclined relative to the longitudinal direction of the rib between the head-end and foot-end. It is irrelevant whether the cooling hole or the rib is strictly radially aligned.
  • the laterally arrangement can be realized if the cooling hole along its channel axis is not rectilinear, but curved. Then it is sufficient if the cooling hole in the region of the inflow opening - ie immediately downstream thereof - is inclined relative to the local longitudinal extension of the rib.
  • Such curved cooling holes can be easily produced by erosion.
  • the orientation of the rib is of minor relevance. In both cases, a grinding or slate cut results to form an elliptical inflow opening.
  • the inflow opening has an elliptical shape with a smaller axis and a larger axis, wherein the smaller axis is smaller than the diameter of the remaining cooling hole.
  • Such an inflow opening can be produced in the airfoil or in the turbine blade by eroding or by laser drilling. Due to the further reduced size of the inflow opening, particles which are very similar or larger than the diameter of the remaining cooling hole do not enter the cooling hole. Only those which are so small that they are discharged again without being adhered to them with the cooling fluid arrive. This reduces the risk of blockage of the cooling hole.
  • the rib in question in a normal Spannweiteraum cross-sectional plane a curved contour with a - based on the remaining inner surface - maximum rib height H, wherein the inflow-side end of the respective cooling hole is arranged laterally of the location of the maximum rib height
  • the rib may also have an angular, for example triangular or rectangular contour instead of the curved contour.
  • in conjunction with the curved rib contour can be achieved by drilling the cooling hole a contour for the inflow opening, which is similar to an employee ellipse.
  • the longer axis of the ellipse is parallel or acute-angled to the inner surface of the respective side wall, but arranged in the rib surface. Due to the elliptical inlet contour of the inflow opening, a comparatively narrow inlet slot can be provided while achieving a comparatively large inflow cross-section, whose shorter axis is selected to be smaller than the diameter of particles typically entrained in the cooling air. The risk of constipation can therefore be reduced.
  • the rib in question is inclined starting from its head-side end to its end arranged at the end in the direction of the front edge or in the direction of the trailing edge.
  • the rib in question preferably extends straight from its head-side end to its foot-side end, but the longitudinal extent of the rib with respect Spannweiteiques an angle greater than 0 °, for example 25 °.
  • the cavity adjoining the respective rib is such that its essential coolant supply is arranged on that side of the respective rib which faces away from the surface of the rib which has the inflow-side end of the cooling hole.
  • the respective partial cavity of the airfoil, in which the rib in question is arranged is supplied with coolant at a certain position.
  • the respective rib is located downstream of this specific position of the coolant supply, wherein the upstream end of the cooling hole is disposed on the side of the rib, which is opposite to the incoming cooling air flow; the inflow opening is arranged in the lee of the respective rib.
  • the inflow-side end is in the slipstream. Particles entrained in the coolant thus flow along the inner surface of the respective side wall to the rib, are lifted off the latter and then forcibly flow through the inflow opening of the cooling hole due to their inertia, without being able to enter it.
  • This design significantly reduces the likelihood of blockage of cooling holes.
  • At least one sealing tip is arranged on the outwardly facing surface of the tip wall, wherein more preferably the relevant Cooling hole extends at least partially, preferably completely through said sealing tip.
  • sealing tips can be provided, which are internally cool despite their relatively small wall thickness.
  • the wall thicknesses of such sealing tips may have a size of about 2 mm, wherein the cooling holes may have a diameter of 1.0 mm and smaller.
  • rib and cooling hole pairs according to the invention can be applied to both side walls of the airfoil. It is of course also possible to produce such airfoils or turbine blades by additive methods, for example selective laser melting or the like.
  • FIG. 1 shows a turbine blade 10 in a perspective view.
  • the turbine blade 10 is according to FIG. 1 designed as a blade. It comprises a fir tree-shaped blade root 12 and a platform 14 arranged thereon. Accordingly, the platform 14 is adjoined by an airfoil 16 which is aerodynamically curved. Whether the blade 16 is covered by a thermal protective layer or not, is irrelevant to the invention.
  • the airfoil 16 includes a suction sidewall 22 and a pressure sidewall 24. Relative to a hot gas flowing around the airfoil 16, these walls extend from a leading edge 18 to a trailing edge 20. Along the trailing edge 20 are provided a plurality of coolant venting orifices 28 are separated by webs 30 disposed therebetween.
  • the airfoil 16 extends along a spanwise direction, which coincides with a radial direction of a turbine, from a root end 26 to a head end 27.
  • the latter is also known as a blade tip.
  • FIG. 2 shows a sectional view through the airfoil 16 according to the section line II - II as a first embodiment of an airfoil 16 according to the invention in the FIG. 2 only the radial outer end of the blade 16, ie the blade tip, is shown in relation to the span or radial direction R of the gas turbine.
  • the airfoil 1 Installed in a gas turbine, the airfoil 1 extends in the radial direction R.
  • Further axes of the gas turbine are denoted by A and U, where A stands for axial direction and U represents the circumferential direction. These are subsequently used as needed to simplify the description of the arrangement.
  • the airfoil 16 has at the head end 27 a top wall 34 which defines a cavity 32 to the outside.
  • the tip wall 34 is substantially at a right angle to the suction-side side wall 22 and passes into this.
  • a rib 38 is arranged on an inner surface 40 of the suction-side side wall 22 facing the cavity 32.
  • the rib 38 extends rectilinearly from its head end 46 to its base end 44.
  • a further extending in the axial direction rib 39 is provided to deflect at possibly radially occurring cooling flow particles.
  • a sealing tip 48 is also arranged and part of this.
  • Such sealing tips also known in English as “squealer tips”, are usually perceived as radial extensions of the side walls 22, 24 of the turbine blade 10. They serve to reduce a gap between the blade tip and the opposed hot gas path boundary of the gas turbine.
  • the sealing tips 48 may be disposed continuously with respect to the outer side surfaces of the suction-side side wall 22 and the pressure-side side wall 24, respectively, as shown.
  • a cooling hole 36 extends through the top wall 34 together with the sealing tip 48 into the rib 38.
  • the cooling hole 36 has an inflow opening 42 for a cooling fluid.
  • a cooling fluid which can be supplied to the cavity 32, can flow into said opening 42, flow along the cooling hole 36 and exit at the outer end. Meanwhile, the cooling fluid cools the local area of the suction side wall 22, the tip wall 34, and more particularly, the sealing tip 48. It will be understood that at the blade tip of a turbine blade 10, more of those shown and described in more detail below Pairs of cooling holes 36 and ribs 38 may be provided. This is especially true when the sealing tip 48 extends along the entire circumference of the airfoil 16.
  • the cooling hole 36 does not necessarily have to extend through the sealing tip 48. According to an alternative embodiment, the cooling hole 36 also end laterally of the sealing tip 48. It can end, for example, on the hot gas side or in the top clearance 39.
  • FIG. 3 shows the top view of the interior of the blade tip according to the section line III-III FIG. 2 . Due to the reference of the different directions when the airfoil 16 is installed in a gas turbine, it can be seen that the rib 38 is inclined with respect to the radial direction.
  • the rib 38 according to the embodiment shown here extends in a straight-line manner from its head-side end 46 to its foot-side end 44.
  • the cooling hole 36 extending through the sealing tip 48, the tip wall 34, into the rib 38 is parallel to the radial direction R aligned, but inclined in the circumferential direction ( Fig. 2 ).
  • a channel axis 37 of the cooling hole 36 in the region of the inflow opening 42 is inclined at an obtuse angle with respect to the longitudinal extent of the rib 38.
  • the cooling hole 36 as well as the rib 38 in the circumferential direction U and / or in the axial direction A may be inclined.
  • An axially inclined cooling hole 36 is as a second embodiment in FIG. 5 shown and empties in the radially outwardly curved rib 38. Further shows FIG. 5
  • an elliptical inflow opening 42 whose shorter axis 54 is smaller than the diameter of the remaining, in cross-section circular cooling hole 36th
  • FIG. 4 shows the section through the blade tip side end 27 of the airfoil 16 according to the section line IV-IV FIG. 2 ,
  • two ribs 38 according to the invention are provided on the suction side, the first of which protrudes asymmetrically from the inner surface 40 of the suction-side side wall 22.
  • the second of the two ribs 38 according to the invention in this cross-sectional view which cross-sectional plane is normal to the radial direction R, is triangular in shape.
  • the transition from the inner surface 40 to the side surface of the rib 38 can also be designed steplessly and thus aerodynamically with low loss, in particular on its inflow side.
  • the cooling holes 36 open into one of the side surfaces of the ribs 38.
  • the position of the opening 42 is according to the invention in the side surface of the rib 38, which is arranged away from a maximum rib height H.
  • the rib height H is based on the remaining inner surface 40 of the suction-side wall 22.
  • a cooling fluid preferably cooling air
  • the cooling fluid flows through the cavity 32, and the cooling fluid has a predetermined main flow direction 50 due to the topology of the cavity 32 and the position of a cooling air feed and the position of adjacent outflow passages.
  • This main flow direction is to be determined in the immediate vicinity of the rib 38 according to the invention. Since the cooling fluid can never be completely free of dirt particles, it is advantageous if the inflow opening 42 of the cooling hole 36 is arranged on the side of the respective rib 38 which faces away from the cooling fluid flowing towards the relevant rib.
  • the inflow opening 42 of the cooling hole 36 is, so to speak, in the lee of the lee - the maximum rib height H. From the cooling fluid entrained particles are due to the shape of the rib 38 directed into a flow path in which they increasingly with distance traveled away from the inner surfaces of the side walls 22, 24 to the location of the maximum rib height H. Then they flow due to their inertia and of the inlet opening 42 pointing away flow direction past it; they can only flow into the cooling hole 36 under difficult conditions. As a result, particle-poorer air-in comparison with the prior art-flows into the cooling holes 36 and thus the risk of blockage is reduced. This allows the use of cooling holes 36 with a particularly small diameter, for example, less than a millimeter at a reduced risk of clogging of the inlet openings 42 and the cooling holes 36 by entrained particles.
  • the inflow opening 42 of the opening into the rib 38 cooling holes 36 is not circular, but elliptically inclined with a longer axis and a shorter axis. Even thereby, it would be difficult for the linear cooling hole 36 in alignment flowing cooling air particles to flow into the respective cooling hole 36.
  • the cooling hole 36 can be made after drilling the turbine blade 10 by drilling subsequently.
  • the inclined rib 38 (FIG. Fig. 3 ) has the advantage that the cooling hole 36 can be located in a comparatively large axial section AB.
  • the cooling hole 36 has an elliptically shaped inflow opening 42, which is always located on the side lying downstream of the incoming cooling fluid in the lee. This improves the manufacturability of such a turbine blade 10, since the section AB, in which the cooling hole is to be drilled, is comparatively large and thus easier to hit.
  • the invention provides an airfoil 16 for an internally cooled turbine blade 10 comprising a suction side wall 22 and a pressure side sidewall 24 extending from a common leading edge 18 to a common trailing edge 20 and in a spanwise direction from a root end 26 to a head end Extending end 27 at least partially enclose a cavity, wherein the head-side end 27 comprises a cavity 32 head-bounding top wall 34 in which at least one cooling hole 36, preferably more cooling holes 36 is provided for discharging flowable inside cooling fluid or are.
  • rib in the cavity 32 at least one extending from the top wall 34 in the direction of the foot end 42 rib preferably a plurality of such ribs 38 from which this rib surrounding inner surfaces 40 of the suction-side side wall 22 and / or the inner surface 40 of the pressure-side side wall 24 protrudes and that one - based on the cooling fluid - inflow opening 42 of the at least one cooling hole 36 in the respective rib 38 opens laterally ,

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17197244.1A 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale Active EP3473808B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17197244.1A EP3473808B1 (fr) 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
US16/145,792 US10746027B2 (en) 2017-10-19 2018-09-28 Blade airfoil for an internally cooled turbine rotor blade, and method for producing the same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17197244.1A EP3473808B1 (fr) 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale

Publications (2)

Publication Number Publication Date
EP3473808A1 true EP3473808A1 (fr) 2019-04-24
EP3473808B1 EP3473808B1 (fr) 2020-06-17

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US (1) US10746027B2 (fr)
EP (1) EP3473808B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3851633A1 (fr) * 2020-01-15 2021-07-21 Raytheon Technologies Corporation Dispositif de purge de saleté aux extrémités des ailettes de turbines
EP3974619B1 (fr) * 2020-09-25 2023-11-15 Doosan Enerbility Co., Ltd. Aube rotorique de turbine et turbine à gaz

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10551327B2 (en) * 2018-04-11 2020-02-04 General Electric Company Cooling hole inspection system
GB2591298B (en) * 2020-01-27 2022-06-08 Gkn Aerospace Sweden Ab Outlet guide vane cooler

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0965728A2 (fr) 1998-06-19 1999-12-22 Rolls-Royce Plc Piège à particules dans un système de refroidissement des turbines à gaz
EP1793086A2 (fr) 2005-12-03 2007-06-06 Rolls-Royce plc Aube de turbine
EP1793087A1 (fr) * 2005-12-05 2007-06-06 General Electric Company Aube de turbine à extrémité mousse
US20120308392A1 (en) * 2011-05-31 2012-12-06 General Electric Company Ceramic-Based Tip Cap for a Turbine Bucket
US20170159450A1 (en) * 2015-12-07 2017-06-08 General Electric Company Fillet optimization for turbine airfoil

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4142824A (en) * 1977-09-02 1979-03-06 General Electric Company Tip cooling for turbine blades
JPH0663442B2 (ja) * 1989-09-04 1994-08-22 株式会社日立製作所 タービン翼
US6224336B1 (en) * 1999-06-09 2001-05-01 General Electric Company Triple tip-rib airfoil
EP1488077B1 (fr) * 2002-03-25 2006-07-12 ALSTOM Technology Ltd Aube de turbine refroidie
GB201120273D0 (en) * 2011-11-24 2012-01-04 Rolls Royce Plc Aerofoil cooling arrangement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0965728A2 (fr) 1998-06-19 1999-12-22 Rolls-Royce Plc Piège à particules dans un système de refroidissement des turbines à gaz
EP1793086A2 (fr) 2005-12-03 2007-06-06 Rolls-Royce plc Aube de turbine
EP1793087A1 (fr) * 2005-12-05 2007-06-06 General Electric Company Aube de turbine à extrémité mousse
US20120308392A1 (en) * 2011-05-31 2012-12-06 General Electric Company Ceramic-Based Tip Cap for a Turbine Bucket
US20170159450A1 (en) * 2015-12-07 2017-06-08 General Electric Company Fillet optimization for turbine airfoil

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3851633A1 (fr) * 2020-01-15 2021-07-21 Raytheon Technologies Corporation Dispositif de purge de saleté aux extrémités des ailettes de turbines
US11274559B2 (en) 2020-01-15 2022-03-15 Raytheon Technologies Corporation Turbine blade tip dirt removal feature
EP3974619B1 (fr) * 2020-09-25 2023-11-15 Doosan Enerbility Co., Ltd. Aube rotorique de turbine et turbine à gaz

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US20190120066A1 (en) 2019-04-25
EP3473808B1 (fr) 2020-06-17
US10746027B2 (en) 2020-08-18

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