EP2565383A3 - Airfoil with nonlinear cooling passage - Google Patents

Airfoil with nonlinear cooling passage Download PDF

Info

Publication number
EP2565383A3
EP2565383A3 EP12182433.8A EP12182433A EP2565383A3 EP 2565383 A3 EP2565383 A3 EP 2565383A3 EP 12182433 A EP12182433 A EP 12182433A EP 2565383 A3 EP2565383 A3 EP 2565383A3
Authority
EP
European Patent Office
Prior art keywords
airfoil
cooling passage
cooling channel
interior cooling
exterior
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
EP12182433.8A
Other languages
German (de)
French (fr)
Other versions
EP2565383A2 (en
EP2565383B1 (en
Inventor
William Abdel-Messeh
Justin D. Piggush
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 EP2565383A2 publication Critical patent/EP2565383A2/en
Publication of EP2565383A3 publication Critical patent/EP2565383A3/en
Application granted granted Critical
Publication of EP2565383B1 publication Critical patent/EP2565383B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • B22C9/103—Multipart 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
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • 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
    • F05D2260/221—Improvement of heat transfer

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Abstract

An example method of manufacturing an airfoil (30) includes providing a ceramic core (64) corresponding to an interior cooling channel (42). A refractory metal core (66) is provided that corresponds to a cooling passage (46). The cores are arranged in a mold (60). An airfoil structure (30) is cast about the cores to provide a turbine engine airfoil. The turbine engine airfoil (30) includes a wall (44) providing the interior cooling channel (42) and an exterior airfoil surface (34). The cooling passage (46) is provided in the wall (44) and fluidly connects the interior cooling channel (42) to the exterior airfoil surface (34). The cooling passage (46) includes multiple inlets (48) and multiple outlets (50) respectively adjoining the interior cooling channel (42) and the exterior airfoil surface (34). At least one of a first inlet (48) and outlet (50) has a different structural flow characteristic than at least one of a second inlet and outlet (48,50).
EP12182433.8A 2011-08-31 2012-08-30 Airfoil with cooling passage Active EP2565383B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/222,490 US20130052037A1 (en) 2011-08-31 2011-08-31 Airfoil with nonlinear cooling passage

Publications (3)

Publication Number Publication Date
EP2565383A2 EP2565383A2 (en) 2013-03-06
EP2565383A3 true EP2565383A3 (en) 2016-09-07
EP2565383B1 EP2565383B1 (en) 2019-10-02

Family

ID=46888909

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12182433.8A Active EP2565383B1 (en) 2011-08-31 2012-08-30 Airfoil with cooling passage

Country Status (2)

Country Link
US (1) US20130052037A1 (en)
EP (1) EP2565383B1 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014126565A1 (en) 2013-02-14 2014-08-21 United Technologies Corporation Gas turbine engine component having surface indicator
US10563517B2 (en) * 2013-03-15 2020-02-18 United Technologies Corporation Gas turbine engine v-shaped film cooling hole
US20140360155A1 (en) * 2013-06-07 2014-12-11 General Electric Company Microchannel systems and methods for cooling turbine components of a gas turbine engine
JP6245740B2 (en) * 2013-11-20 2017-12-13 三菱日立パワーシステムズ株式会社 Gas turbine blade
US10352181B2 (en) * 2014-11-26 2019-07-16 Ansaldo Energia Ip Uk Limited Leading edge cooling channel for airfoil
US9963975B2 (en) 2015-02-09 2018-05-08 United Technologies Corporation Trip strip restagger
US10156157B2 (en) * 2015-02-13 2018-12-18 United Technologies Corporation S-shaped trip strips in internally cooled components
US10408079B2 (en) 2015-02-18 2019-09-10 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
US20170335692A1 (en) * 2016-05-20 2017-11-23 United Technologies Corporation Refractory metal core and components formed thereby
US10323569B2 (en) 2016-05-20 2019-06-18 United Technologies Corporation Core assemblies and gas turbine engine components formed therefrom
US10422232B2 (en) * 2017-05-22 2019-09-24 United Technologies Corporation Component for a gas turbine engine
US10508555B2 (en) 2017-12-05 2019-12-17 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US10648345B2 (en) 2017-12-05 2020-05-12 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US10626735B2 (en) * 2017-12-05 2020-04-21 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US11149556B2 (en) * 2018-11-09 2021-10-19 Raytheon Technologies Corporation Minicore cooling passage network having sloped impingement surface
US11339718B2 (en) 2018-11-09 2022-05-24 Raytheon Technologies Corporation Minicore cooling passage network having trip strips

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2358226A (en) * 2000-01-13 2001-07-18 Alstom Power Cooled blade for a gas turbine
US20050265838A1 (en) * 2003-03-12 2005-12-01 George Liang Leading edge diffusion cooling of a turbine airfoil for a gas turbine engine
EP1790823A2 (en) * 2005-11-23 2007-05-30 United Technologies Corporation Microcircuit cooling for turbine vanes
EP1972396A1 (en) * 2007-03-14 2008-09-24 United Technologies Corporation Cast features for a turbine engine airfoil
EP2131011A2 (en) * 2008-06-05 2009-12-09 United Technologies Corporation Particle resistant in-wall cooling passage inlet
EP2159375A2 (en) * 2008-08-29 2010-03-03 United Technologies Corporation A turbine engine airfoil with convective cooling, the corresponding core and the method for manufacturing this airfoil

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5486093A (en) * 1993-09-08 1996-01-23 United Technologies Corporation Leading edge cooling of turbine airfoils
US7306026B2 (en) * 2005-09-01 2007-12-11 United Technologies Corporation Cooled turbine airfoils and methods of manufacture
US7845906B2 (en) * 2007-01-24 2010-12-07 United Technologies Corporation Dual cut-back trailing edge for airfoils
US7857589B1 (en) * 2007-09-21 2010-12-28 Florida Turbine Technologies, Inc. Turbine airfoil with near-wall cooling
US8449254B2 (en) * 2010-03-29 2013-05-28 United Technologies Corporation Branched airfoil core cooling arrangement
US8366395B1 (en) * 2010-10-21 2013-02-05 Florida Turbine Technologies, Inc. Turbine blade with cooling

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2358226A (en) * 2000-01-13 2001-07-18 Alstom Power Cooled blade for a gas turbine
US20050265838A1 (en) * 2003-03-12 2005-12-01 George Liang Leading edge diffusion cooling of a turbine airfoil for a gas turbine engine
EP1790823A2 (en) * 2005-11-23 2007-05-30 United Technologies Corporation Microcircuit cooling for turbine vanes
EP1972396A1 (en) * 2007-03-14 2008-09-24 United Technologies Corporation Cast features for a turbine engine airfoil
EP2131011A2 (en) * 2008-06-05 2009-12-09 United Technologies Corporation Particle resistant in-wall cooling passage inlet
EP2159375A2 (en) * 2008-08-29 2010-03-03 United Technologies Corporation A turbine engine airfoil with convective cooling, the corresponding core and the method for manufacturing this airfoil

Also Published As

Publication number Publication date
US20130052037A1 (en) 2013-02-28
EP2565383A2 (en) 2013-03-06
EP2565383B1 (en) 2019-10-02

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