US20120163993A1 - Leading edge airfoil-to-platform fillet cooling tube - Google Patents

Leading edge airfoil-to-platform fillet cooling tube Download PDF

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Publication number
US20120163993A1
US20120163993A1 US12/977,418 US97741810A US2012163993A1 US 20120163993 A1 US20120163993 A1 US 20120163993A1 US 97741810 A US97741810 A US 97741810A US 2012163993 A1 US2012163993 A1 US 2012163993A1
Authority
US
United States
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.)
Abandoned
Application number
US12/977,418
Other languages
English (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
Priority to US12/977,418 priority Critical patent/US20120163993A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Donnell, Brandon S., LEVINE, JEFFREY R
Priority to EP11250867.6A priority patent/EP2469035B1/fr
Publication of US20120163993A1 publication Critical patent/US20120163993A1/en
Abandoned legal-status Critical Current

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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
    • 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 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 ;
  • FIG. 5 is a sectional view taken along lines 5 - 5 in FIG. 3 .
  • 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 70 and 72 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 70 and 72 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)
US12/977,418 2010-12-23 2010-12-23 Leading edge airfoil-to-platform fillet cooling tube Abandoned US20120163993A1 (en)

Priority Applications (2)

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
EP11250867.6A EP2469035B1 (fr) 2010-12-23 2011-10-21 Refroidissement du bord d'attaque d'un composant de turbine à gaz

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 (1)

Publication Number Publication Date
US20120163993A1 true US20120163993A1 (en) 2012-06-28

Family

ID=45001667

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/977,418 Abandoned US20120163993A1 (en) 2010-12-23 2010-12-23 Leading edge airfoil-to-platform fillet cooling tube

Country Status (2)

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

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150110640A1 (en) * 2013-10-23 2015-04-23 General Electric Company Turbine bucket having serpentine core
US9347320B2 (en) 2013-10-23 2016-05-24 General Electric Company Turbine bucket profile yielding improved throat
US9376927B2 (en) 2013-10-23 2016-06-28 General Electric Company Turbine nozzle having non-axisymmetric endwall contour (EWC)
US20160208629A1 (en) * 2014-12-18 2016-07-21 United Technologies Corporation Anti-rotation vane
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
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
US20170211421A1 (en) * 2014-08-04 2017-07-27 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
US9797258B2 (en) 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
US10107108B2 (en) 2015-04-29 2018-10-23 General Electric Company Rotor blade having a flared tip
US20180361465A1 (en) * 2017-06-15 2018-12-20 Siemens Aktiengesellschaft Casting core with crossover bridge
US20190024514A1 (en) * 2017-07-21 2019-01-24 United Technologies Corporation Airfoil having serpentine core resupply flow control
US20200024952A1 (en) * 2017-09-12 2020-01-23 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly, turbine including vane assembly, and gasturbine including vane assembly
US10612392B2 (en) 2014-12-18 2020-04-07 United Technologies Corporation Gas turbine engine component with conformal fillet cooling path

Citations (11)

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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
US20060153681A1 (en) * 2005-01-10 2006-07-13 General Electric Company Funnel fillet turbine stage
US7217094B2 (en) * 2004-10-18 2007-05-15 United Technologies Corporation Airfoil with large fillet and micro-circuit cooling
US20080166240A1 (en) * 2007-01-04 2008-07-10 Siemens Power Generation, Inc. Advanced cooling method for combustion turbine airfoil fillets
US20090285684A1 (en) * 2008-05-14 2009-11-19 United Technologies Corporation Turbine blade internal cooling configuration
US7621718B1 (en) * 2007-03-28 2009-11-24 Florida Turbine Technologies, Inc. Turbine vane with leading edge fillet region impingement cooling
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
US20100254824A1 (en) * 2008-03-31 2010-10-07 Shailendra Naik Gas turbine airfoil
US8657576B2 (en) * 2008-06-23 2014-02-25 Rolls-Royce Plc Rotor blade
US8794906B1 (en) * 2010-06-22 2014-08-05 Florida Turbine Technologies, Inc. Turbine stator vane with endwall cooling

Patent Citations (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
US20060153681A1 (en) * 2005-01-10 2006-07-13 General Electric Company Funnel fillet turbine stage
US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
US20080166240A1 (en) * 2007-01-04 2008-07-10 Siemens Power Generation, 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
US20100254824A1 (en) * 2008-03-31 2010-10-07 Shailendra Naik Gas turbine airfoil
US20090285684A1 (en) * 2008-05-14 2009-11-19 United Technologies Corporation Turbine blade internal cooling configuration
US8657576B2 (en) * 2008-06-23 2014-02-25 Rolls-Royce Plc Rotor blade
US8794906B1 (en) * 2010-06-22 2014-08-05 Florida Turbine Technologies, Inc. Turbine stator vane with endwall cooling

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150110640A1 (en) * 2013-10-23 2015-04-23 General Electric Company Turbine bucket having serpentine core
US9347320B2 (en) 2013-10-23 2016-05-24 General Electric Company Turbine bucket profile yielding improved throat
US9376927B2 (en) 2013-10-23 2016-06-28 General Electric Company Turbine nozzle having non-axisymmetric endwall contour (EWC)
US9797258B2 (en) 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
US9528379B2 (en) * 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core
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
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
US20170211421A1 (en) * 2014-08-04 2017-07-27 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
US10724404B2 (en) * 2014-08-04 2020-07-28 Mitsubishi Hitachi Power Systems, Ltd. Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
US20160208629A1 (en) * 2014-12-18 2016-07-21 United Technologies Corporation Anti-rotation vane
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
US20180361465A1 (en) * 2017-06-15 2018-12-20 Siemens Aktiengesellschaft Casting core with crossover bridge
US20190024514A1 (en) * 2017-07-21 2019-01-24 United Technologies Corporation Airfoil having serpentine core resupply flow control
US10612394B2 (en) * 2017-07-21 2020-04-07 United Technologies Corporation Airfoil having serpentine core resupply flow control
US20200024952A1 (en) * 2017-09-12 2020-01-23 Doosan Heavy Industries & Construction Co., Ltd. Vane assembly, turbine including vane assembly, and gasturbine including vane assembly
US10844723B2 (en) * 2017-09-12 2020-11-24 DOOSAN Heavy Industries Construction Co., LTD Vane assembly, turbine including vane assembly, and gasturbine including vane assembly

Also Published As

Publication number Publication date
EP2469035A3 (fr) 2017-12-13
EP2469035B1 (fr) 2020-04-01
EP2469035A2 (fr) 2012-06-27

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Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:LEVINE, JEFFREY R;DONNELL, BRANDON S.;REEL/FRAME:025565/0835

Effective date: 20101223

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION