EP2469035A2 - Turbine engine component comprising a leading edge airfoil-to-platform fillet cooling tube - Google Patents

Turbine engine component comprising a leading edge airfoil-to-platform fillet cooling tube Download PDF

Info

Publication number
EP2469035A2
EP2469035A2 EP11250867A EP11250867A EP2469035A2 EP 2469035 A2 EP2469035 A2 EP 2469035A2 EP 11250867 A EP11250867 A EP 11250867A EP 11250867 A EP11250867 A EP 11250867A EP 2469035 A2 EP2469035 A2 EP 2469035A2
Authority
EP
European Patent Office
Prior art keywords
leading edge
turbine engine
engine component
boxcar
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.)
Granted
Application number
EP11250867A
Other languages
German (de)
French (fr)
Other versions
EP2469035A3 (en
EP2469035B1 (en
Inventor
Jeffrey R. Levine
Brandon S. Donnell
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2469035A2 publication Critical patent/EP2469035A2/en
Publication of EP2469035A3 publication Critical patent/EP2469035A3/en
Application granted granted Critical
Publication of EP2469035B1 publication Critical patent/EP2469035B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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.
  • 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 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 for forming part of a turbine engine component which core broadly comprises a first portion for forming an internal cavity within an airfoil portion of said component, a second portion for forming a leading edge boxcar in a leading edge of said airfoil portion, and a third portion for forming a cooling tube which extends between 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)

Abstract

A turbine engine component (10) includes an airfoil portion having a leading edge (18), a platform (14), a leading edge airfoil to platform fillet (16), and a cooling tube (30) located within said fillet (16). The cooling tube (30) has a flared entrance (31) end and a flared exit end (33).
The invention also extends to a core used to form the turbine engine component.

Description

    STATEMENT OF GOVERNMENT INTEREST
  • The subject matter described herein was made with government support under Contract No. N00019-02-C-3003 awarded by the Department of the Navy. The government of the United States of America may have rights to the subject matter described herein.
    • BACKGROUND
  • 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.
  • 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.
  • The prior technology for forming impingement cavities in vanes has not incorporated features that adequately cool the airfoil-to-platform fillet radius.
    • SUMMARY
  • Accordingly, it is desirable to reduce metal temperatures in the leading edge outer diameter airfoil-to-platform fillet so as to reduce thermal strains and increase part life. Described herein is a way to cool this region using convective cooling.
  • In accordance with the present disclosure, there is provided a turbine engine component 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.
  • Further in accordance with the present disclosure, there is provided a core for forming part of a turbine engine component, which core broadly comprises a first portion for forming an internal cavity within an airfoil portion of said component, a second portion for forming a leading edge boxcar in a leading edge of said airfoil portion, and a third portion for forming a cooling tube which extends between said leading edge boxcar and said internal cavity, which third portion has a flared entrance end and a flared exit end.
  • Other details of the leading edge airfoil-to-platform fillet cooling tube are set forth in the following detailed description and the following drawings wherein like reference numerals depict like elements.
    • BRIEF DESCRIPTION OF THE DRAWINGS
    • Fig. 1 is a schematic illustration of a turbine vane having a leading edge airfoil-to-platform fillet;
    • Fig. 2 is a schematic illustration of a turbine vane having a fillet cooling tube in accordance with the present invention;
    • Fig. 3 is a schematic illustration of a core used to form the fillet cooling tube of Fig. 2;
    • Fig. 4 is a sectional view taken along lines 4-4 in Fig. 3; and
    • Fig. 5 is a sectional view taken along lines 5-5 in Fig. 3.
    DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT(S)
  • 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. In previous designs, 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. As described herein, 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. In order to achieve a desirable oxidation life for the leading edge 18, 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.
  • By adding an additional flow path for cooling air, additional internal cooling is achieved in a critical region.
  • Referring now to Figs. 3 to 5, there is shown 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. As can be seen from Fig. 3, 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. As can be seen from Fig. 3, 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.
  • As noted above, 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.
  • There has been provided herein a leading edge airfoil-to-platform fillet cooling tube. While the cooling tube has been described in the context of a specific embodiment thereof, other unforeseen alternatives, modifications, or variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embraces those alternatives, modifications, and variations as fall within the broad scope of the appended claims.

Claims (13)

  1. A turbine engine component (10) comprising:
    an airfoil portion (12) having a leading edge (18);
    a platform (14);
    a leading edge airfoil to platform fillet (16); and
    a cooling tube (30) located within said fillet (16), said cooling tube having a flared entrance end (31) and a flared exit end (33).
  2. The turbine engine component of claim 1, wherein said entrance end (31) and said exit end (33) are each bellmouth shaped.
  3. The turbine engine component of claim 1 or claim 2, wherein said leading edge (18) of said airfoil portion (12) includes a leading edge boxcar (20) and an interior portion of said airfoil portion includes a cavity (34) through which cooling air flows.
  4. The turbine engine component of claim 3, further comprising a plurality of cross-over holes (22) for allowing cooling fluid to flow from said cavity (34) to said boxcar (20).
  5. The turbine engine component of claim 3 or claim 4, wherein said boxcar (20) has a plurality of cooling film holes (28).
  6. The turbine engine component of any preceding claim, wherein said tube (30) has a cross-sectional area which is between 25% and 100% of a cross-sectional area of said boxcar (20).
  7. The turbine engine component of any preceding claim, wherein said tube (30) has a cross-sectional area which is between 50% and 100% of a cross-sectional area of said boxcar (20).
  8. The turbine engine component of any preceding claim, wherein said tube (30) has a cross-sectional shape selected from the group consisting of circular, elliptical, triangular, and square.
  9. The turbine engine component of any preceding claim, wherein said cooling tube (30 meets said leading edge boxcar (20) at an end of said leading edge boxcar (20).
  10. A core (60) for forming part of a turbine engine component (10), said core comprising:
    a first portion (62) for forming an internal cavity (34) within an airfoil portion of said component (10);
    a second portion (64) for forming a leading edge boxcar (20) in a leading edge of said airfoil portion;
    a third portion (68) for forming a cooling tube (30) which extends between said leading edge boxcar (20) and said internal cavity (34); and
    said third portion (68) having a flared entrance end (70) and a flared exit end (72).
  11. The core according to claim 10, wherein said core (60) is formed from a ceramic material.
  12. The core according to claim 10 or claim 11, wherein said core (60) has at least one fourth portion (66) adapted to form at least one cross-over hole (22) between said leading edge boxcar (20) and said cavity (34).
  13. The core according to any of claims 10 to 12, wherein said entrance end (70) and said exit end (72) are each bellmouthed shaped.
EP11250867.6A 2010-12-23 2011-10-21 Turbine engine component comprising a leading edge airfoil-to-platform fillet cooling tube Active EP2469035B1 (en)

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 true EP2469035A2 (en) 2012-06-27
EP2469035A3 EP2469035A3 (en) 2017-12-13
EP2469035B1 EP2469035B1 (en) 2020-04-01

Family

ID=45001667

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11250867.6A Active EP2469035B1 (en) 2010-12-23 2011-10-21 Turbine engine component comprising a leading edge airfoil-to-platform fillet cooling tube

Country Status (2)

Country Link
US (1) US20120163993A1 (en)
EP (1) EP2469035B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3415250A1 (en) * 2017-06-15 2018-12-19 Siemens Aktiengesellschaft Casting core with crossover bridge

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9528379B2 (en) * 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core
US9376927B2 (en) 2013-10-23 2016-06-28 General Electric Company Turbine nozzle having non-axisymmetric endwall contour (EWC)
US9551226B2 (en) 2013-10-23 2017-01-24 General Electric Company Turbine bucket with endwall contour and airfoil profile
US9797258B2 (en) 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
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
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
JP5717904B1 (en) * 2014-08-04 2015-05-13 三菱日立パワーシステムズ株式会社 Stator blade, gas turbine, split ring, stator blade remodeling method, and split ring remodeling method
US10612392B2 (en) 2014-12-18 2020-04-07 United Technologies Corporation Gas turbine engine component with conformal fillet cooling path
US10378371B2 (en) * 2014-12-18 2019-08-13 United Technologies Corporation Anti-rotation vane
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
US10612394B2 (en) * 2017-07-21 2020-04-07 United Technologies Corporation Airfoil having serpentine core resupply flow control
KR101937586B1 (en) * 2017-09-12 2019-01-10 두산중공업 주식회사 Vane of turbine, turbine and gas turbine comprising it

Family Cites Families (11)

* Cited by examiner, † Cited by third party
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 (en) * 2008-03-31 2014-02-14 Alstom Technology Ltd Aerodynamic gas turbine profile
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3415250A1 (en) * 2017-06-15 2018-12-19 Siemens Aktiengesellschaft Casting core with crossover bridge

Also Published As

Publication number Publication date
EP2469035A3 (en) 2017-12-13
EP2469035B1 (en) 2020-04-01
US20120163993A1 (en) 2012-06-28

Similar Documents

Publication Publication Date Title
EP2469035B1 (en) Turbine engine component comprising a leading edge airfoil-to-platform fillet cooling tube
EP1600604B1 (en) Cooler rotor blade and method for cooling a rotor blade
US7841828B2 (en) Turbine airfoil with submerged endwall cooling channel
EP2369135B1 (en) Blade outer air seal for a gas turbine engine and corresponding gas turbine engine
EP2860359B1 (en) Arrangement for cooling a component in the hot gas path of a gas turbine
US8714909B2 (en) Platform with cooling circuit
US9051943B2 (en) Gas turbine engine heat exchanger fins with periodic gaps
EP3184745B1 (en) Multi-wall blade with cooling circuit
EP1607578B1 (en) Cooled rotor blade
US20140023497A1 (en) Cooled turbine blade tip shroud with film/purge holes
US9328616B2 (en) Film-cooled turbine blade for a turbomachine
JP4929097B2 (en) Gas turbine blade
US20180135423A1 (en) Double impingement slot cap assembly
EP2597260B1 (en) Bucket assembly for turbine system
EP2597263A1 (en) Bucket assembly for turbine system
US9822646B2 (en) Turbine airfoil cooling system with spanwise extending fins
US8714927B1 (en) Microcircuit skin core cut back to reduce microcircuit trailing edge stresses
CN104884741B (en) Blade for turbine
EP3828383A1 (en) Airfoil with trailing edge cooling circuit
US20150260102A1 (en) Heat exchanger for a turbo engine
US6824352B1 (en) Vane enhanced trailing edge cooling design
US10612396B2 (en) Mechanical component
US10920610B2 (en) Casting plug with flow control features
EP2754857A1 (en) Cooling configuration, corresponding stator heat shield, blade, and vane for a gas turbine
EP3121377A1 (en) Turbine rotors including turbine blades having turbulator cooled tip pockets

Legal Events

Date Code Title Description
AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: UNITED TECHNOLOGIES CORPORATION

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 9/04 20060101AFI20171103BHEP

Ipc: F01D 5/18 20060101ALI20171103BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20180613

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20191011

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 1251575

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200415

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602011065958

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200701

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200401

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200702

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200817

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200701

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200801

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1251575

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602011065958

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

26N No opposition filed

Effective date: 20210112

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201021

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20201031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201031

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201031

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200401

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602011065958

Country of ref document: DE

Owner name: RAYTHEON TECHNOLOGIES CORPORATION (N.D.GES.D.S, US

Free format text: FORMER OWNER: UNITED TECHNOLOGIES CORPORATION, FARMINGTON, CONN., US

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230520

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230920

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230920

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230920

Year of fee payment: 13