EP2469035B1 - Refroidissement du bord d'attaque d'un composant de turbine à gaz - Google Patents
Refroidissement du bord d'attaque d'un composant de turbine à gaz Download PDFInfo
- Publication number
- EP2469035B1 EP2469035B1 EP11250867.6A EP11250867A EP2469035B1 EP 2469035 B1 EP2469035 B1 EP 2469035B1 EP 11250867 A EP11250867 A EP 11250867A EP 2469035 B1 EP2469035 B1 EP 2469035B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- leading edge
- boxcar
- turbine engine
- engine component
- cooling tube
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims description 48
- 229910010293 ceramic material Inorganic materials 0.000 claims description 2
- 239000012809 cooling fluid Substances 0.000 claims 1
- 239000002184 metal Substances 0.000 description 4
- 230000001419 dependent effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
Images
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
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- 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
- 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
-
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/11—Two-dimensional triangular
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/27—Three-dimensional hyperboloid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/323—Arrangement of components according to their shape convergent
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
Definitions
- the present disclosure relates to a cooling tube in the vicinity of the leading edge of a turbine engine component at the outer diameter airfoil-to-platform fillet and a casting core for forming same.
- Document US 7,217,094 B2 discloses a turbine engine component comprising: an airfoil portion having a leading edge; a platform; a leading edge airfoil to platform fillet; and a cooling tube having an entrance end and an exit end; wherein said leading edge of said airfoil portion includes a leading edge boxcar and an interior portion of said airfoil portion includes a cavity through which cooling air flows; wherein said boxcar has a plurality of cooling film holes; and wherein said exit end of said cooling tube meets said leading edge boxcar at an end of said leading edge boxcar and said entrance end meets said cavity.
- vanes can be subjected to severe heating conditions in the region of the fillet which extends from the leading edge of the airfoil to the platform. Increased metal temperatures in this region can lead to thermal strains and reduced part life.
- a turbine engine component according to claim 1 and which broadly comprises an airfoil portion having a leading edge, a platform, a leading edge airfoil to platform fillet, and a cooling tube located within said fillet, which cooling tube has a flared entrance end and a flared exit end.
- a core being part of said turbine engine component, which core broadly comprises a first portion for forming the cavity within the airfoil portion of said component, a second portion for forming the leading edge boxcar in the leading edge of said airfoil portion, and a third portion for forming the cooling tube which extends between an end of said leading edge boxcar and said internal cavity, which third portion has a flared entrance end and a flared exit end.
- leading edge airfoil-to-platform fillet cooling tube is set forth in the following detailed description and the following drawings wherein like reference numerals depict like elements.
- Fig. 1 illustrates a turbine engine component 10, in particular a turbine vane.
- the component 10 has an airfoil portion 12 and a platform 14.
- the airfoil portion 12 is joined to the platform 14 by an outer diameter fillet 16 at the leading edge 18 of the airfoil portion 12.
- the outer diameter fillet 16 was uncooled due to geometry constraints of the impingement cavity, preventing impingement heat transfer from occurring and also preventing film holes from being drilled through the fillet.
- a new design feature has been developed that provides convective heat transfer to the outer diameter fillet 16.
- Fig. 2 illustrates a cooling configuration for the turbine engine component 10 which is comprised of three separate impingement cavities 20, also known as boxcars.
- impingement cavities 20 also known as boxcars.
- crossover holes 22 in the impingement rib 24 are designed to maximize heat transfer at the nose 26 of the leading edge 18.
- Film cooling holes 28 are drilled into the leading edge impingement cavity as an additional means for cooling the airfoil portion 12.
- the new design feature comprises a fillet cooling tube 30.
- the cooling tube 30 connects the outer diameter of the leading edge boxcar 20 to the leading edge feed cavity 34.
- the cross sectional area of the cooling tube 30 is to be between 25% and 100% of the cross sectional area of the impingement cavity/boxcar 20 to ensure adequate coolant velocity in the cooling tube.
- the ends 31 and 33 of the cooling tube 30 flare out at a blend radius 36 at the junction to the boxcar 20 and the feed cavity 34. This bellmouth shape at the entrance and exit ends 31 and 33 of the tube 30 helps to minimize pressure losses of the cooling air through the cooling tube 30.
- the cross-sectional shape of the cooling tube 30 is dependent on the cross-sectional shape of the boxcar 20 to which it is connected. Since cooling holes are drilled into the outer diameter leading edge boxcar 20, a pressure ratio exists across the fillet cooling tube 30, allowing cooling air to travel from the feed cavity 34 to the leading edge boxcar 30. The cooling air convectively cools the airfoil-to-platform fillet 16, reducing metal temperature and increasing part life.
- a core 60 which may be used to form the leading edge boxcar(s) 20, the cavity 34 internal to the airfoil portion, and the cooling tube 30.
- the core 60 may be formed from a ceramic material.
- the core has a first portion 62 which forms the interior cavity 34, a leading edge portion 64 which forms the leading edge boxcar 20, a plurality of shaped portions 66 which form the cross-over holes, and an arcuate portion 68 which forms the fillet cooling tube.
- the portion 68 has two bellmouth shaped end portions 70 and 72 which form the entrance and exit ends of the fillet cooling tube 30.
- the fillet cooling tube 30 described herein will provide convective heat transfer in the outer diameter leading edge airfoil-to-platform fillet 16, reducing metal temperatures.
- the impingement cavity 20 to which the fillet cooling tube is connected needs film holes 28 or other cooling features that promote a positive pressure ratio from the feed cavity 34 to the impingement cavity 20.
- the ends 31 and 33 of the fillet cooling tube 30 are flared at the junction to the boxcar 20 and the feed cavity 34 to minimize cooling flow pressure losses as cooling air moves through the tube 30.
- the blend radius of the flare is determined by the specific shape of the boxcar support tube.
- the cross-sectional shape of the fillet cooling tube 30 is dependent on the cross-sectional shape of the impingement cavity (boxcar) it is connecting to.
- the cross sectional shape of the tube 30 may be circular, elliptical, triangular, or square.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (9)
- Composant de turbine à gaz (10) comprenant :une portion de profil d'aile (12) présentant un bord d'attaque (18) ;une plateforme (14) ;un raccordement de profil d'aile de bord d'attaque à la plateforme (16) ; etun tube de refroidissement (30) situé dans ledit raccordement (16), ledit tube de refroidissement présentant une extrémité d'entrée évasée (31) et une extrémité de sortie évasée (33) ;dans lequel ledit bord d'attaque (18) de ladite portion de profil d'aile (12) inclut un tiroir de bord d'attaque (20) et une portion intérieure de ladite portion de profil d'aile inclut une cavité (34) au travers de laquelle de l'air de refroidissement s'écoule ;dans lequel ledit tiroir (20) présente une pluralité de trous de film de refroidissement (28) ; etdans lequel ladite extrémité de sortie dudit tube de refroidissement (30) rencontre ledit tiroir de bord d'attaque (20) à une extrémité dudit tiroir de bord d'attaque (20) et ladite extrémité d'entrée rencontre ladite cavité (34).
- Composant de moteur à turbine selon la revendication 1, dans lequel ladite extrémité d'entrée (31) et ladite extrémité de sortie (33) sont chacune en forme d'entonnoir.
- Composant de moteur à turbine selon la revendication 1, comprenant en outre une pluralité de trous de croisement (22) pour permettre au fluide de refroidissement de s'écouler de ladite cavité (34) audit tiroir (20).
- Composant de moteur à turbine selon l'une quelconque des revendications précédentes, dans lequel ledit tube (30) présente une zone de section transversale qui est entre 25 % et 100 % d'une zone de section transversale dudit tiroir (20).
- Composant de moteur à turbine selon la revendication 4, dans lequel ledit tube (30) présente une zone de section transversale qui est entre 50 % et 100 % d'une zone de section transversale dudit tiroir (20).
- Composant de moteur à turbine selon l'une quelconque des revendications précédentes, dans lequel ledit tube (30) présente une forme de section transversale sélectionnée à partir du groupe constitué de circulaire, elliptique, triangulaire et carrée.
- Noyau (60) qui est une partie d'un composant de moteur à turbine (10) selon l'une quelconque des revendications précédentes, ledit noyau comprenant :une première portion (62) pour la formation de la cavité (34) dans la portion de profil d'aile dudit composant (10) ;une deuxième portion (64) pour la formation du tiroir de bord d'attaque (20) dans le bord d'attaque de ladite portion de profil d'aile ;une troisième portion (68) pour la formation du tube de refroidissement (30) qui s'étend entre une extrémité dudit tiroir de bord d'attaque (20) et ladite cavité interne (34).
- Noyau selon la revendication 7, dans lequel ledit noyau (60) est formé d'un matériau céramique.
- Noyau selon la revendication 7 ou la revendication 8, dans lequel ledit noyau (60) présente au moins une quatrième portion (66) adaptée pour former au moins un trou de croisement (22) entre ledit tiroir de bord d'attaque (20) et ladite cavité (34).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/977,418 US20120163993A1 (en) | 2010-12-23 | 2010-12-23 | Leading edge airfoil-to-platform fillet cooling tube |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2469035A2 EP2469035A2 (fr) | 2012-06-27 |
EP2469035A3 EP2469035A3 (fr) | 2017-12-13 |
EP2469035B1 true EP2469035B1 (fr) | 2020-04-01 |
Family
ID=45001667
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11250867.6A Active EP2469035B1 (fr) | 2010-12-23 | 2011-10-21 | Refroidissement du bord d'attaque d'un composant de turbine à gaz |
Country Status (2)
Country | Link |
---|---|
US (1) | US20120163993A1 (fr) |
EP (1) | EP2469035B1 (fr) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9551226B2 (en) | 2013-10-23 | 2017-01-24 | General Electric Company | Turbine bucket with endwall contour and airfoil profile |
US9638041B2 (en) | 2013-10-23 | 2017-05-02 | General Electric Company | Turbine bucket having non-axisymmetric base contour |
US9347320B2 (en) | 2013-10-23 | 2016-05-24 | General Electric Company | Turbine bucket profile yielding improved throat |
US9528379B2 (en) * | 2013-10-23 | 2016-12-27 | General Electric Company | Turbine bucket having serpentine core |
US9797258B2 (en) | 2013-10-23 | 2017-10-24 | General Electric Company | Turbine bucket including cooling passage with turn |
US9376927B2 (en) | 2013-10-23 | 2016-06-28 | General Electric Company | Turbine nozzle having non-axisymmetric endwall contour (EWC) |
US9670784B2 (en) | 2013-10-23 | 2017-06-06 | General Electric Company | Turbine bucket base having serpentine cooling passage with leading edge cooling |
JP5717904B1 (ja) * | 2014-08-04 | 2015-05-13 | 三菱日立パワーシステムズ株式会社 | 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法 |
US10378371B2 (en) * | 2014-12-18 | 2019-08-13 | United Technologies Corporation | Anti-rotation vane |
US10612392B2 (en) | 2014-12-18 | 2020-04-07 | United Technologies Corporation | Gas turbine engine component with conformal fillet cooling path |
US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
EP3415250A1 (fr) * | 2017-06-15 | 2018-12-19 | Siemens Aktiengesellschaft | Noyau de coulage avec pont de croisement |
US10612394B2 (en) * | 2017-07-21 | 2020-04-07 | United Technologies Corporation | Airfoil having serpentine core resupply flow control |
KR101937586B1 (ko) * | 2017-09-12 | 2019-01-10 | 두산중공업 주식회사 | 베인 조립체, 터빈 및 이를 포함하는 가스터빈 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5245821A (en) * | 1991-10-21 | 1993-09-21 | General Electric Company | Stator to rotor flow inducer |
US5340278A (en) * | 1992-11-24 | 1994-08-23 | United Technologies Corporation | Rotor blade with integral platform and a fillet cooling passage |
US7217094B2 (en) * | 2004-10-18 | 2007-05-15 | United Technologies Corporation | Airfoil with large fillet and micro-circuit cooling |
US7249933B2 (en) * | 2005-01-10 | 2007-07-31 | General Electric Company | Funnel fillet turbine stage |
US7632071B2 (en) * | 2005-12-15 | 2009-12-15 | United Technologies Corporation | Cooled turbine blade |
US7927073B2 (en) * | 2007-01-04 | 2011-04-19 | Siemens Energy, Inc. | Advanced cooling method for combustion turbine airfoil fillets |
US7621718B1 (en) * | 2007-03-28 | 2009-11-24 | Florida Turbine Technologies, Inc. | Turbine vane with leading edge fillet region impingement cooling |
ES2442873T3 (es) * | 2008-03-31 | 2014-02-14 | Alstom Technology Ltd | Perfil aerodinámico de turbina de gas |
US8172533B2 (en) * | 2008-05-14 | 2012-05-08 | United Technologies Corporation | Turbine blade internal cooling configuration |
GB0811391D0 (en) * | 2008-06-23 | 2008-07-30 | Rolls Royce Plc | A rotor blade |
US8794906B1 (en) * | 2010-06-22 | 2014-08-05 | Florida Turbine Technologies, Inc. | Turbine stator vane with endwall cooling |
-
2010
- 2010-12-23 US US12/977,418 patent/US20120163993A1/en not_active Abandoned
-
2011
- 2011-10-21 EP EP11250867.6A patent/EP2469035B1/fr active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP2469035A3 (fr) | 2017-12-13 |
US20120163993A1 (en) | 2012-06-28 |
EP2469035A2 (fr) | 2012-06-27 |
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