SG11201403624WA - Airfoil with improved internal cooling channel pedestals - Google Patents

Airfoil with improved internal cooling channel pedestals

Info

Publication number
SG11201403624WA
SG11201403624WA SG11201403624WA SG11201403624WA SG11201403624WA SG 11201403624W A SG11201403624W A SG 11201403624WA SG 11201403624W A SG11201403624W A SG 11201403624WA SG 11201403624W A SG11201403624W A SG 11201403624WA SG 11201403624W A SG11201403624W A SG 11201403624WA
Authority
SG
Singapore
Prior art keywords
airfoil
pedestals
cooling channel
internal cooling
improved internal
Prior art date
Application number
SG11201403624WA
Inventor
Edwin Otero
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 SG11201403624WA publication Critical patent/SG11201403624WA/en

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
    • F01D5/187—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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
SG11201403624WA 2012-03-07 2013-02-14 Airfoil with improved internal cooling channel pedestals SG11201403624WA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/413,969 US9297261B2 (en) 2012-03-07 2012-03-07 Airfoil with improved internal cooling channel pedestals
PCT/US2013/026010 WO2013133945A1 (en) 2012-03-07 2013-02-14 Airfoil with improved internal cooling channel pedestals

Publications (1)

Publication Number Publication Date
SG11201403624WA true SG11201403624WA (en) 2014-10-30

Family

ID=49112821

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201403624WA SG11201403624WA (en) 2012-03-07 2013-02-14 Airfoil with improved internal cooling channel pedestals

Country Status (4)

Country Link
US (1) US9297261B2 (en)
EP (1) EP2823151B1 (en)
SG (1) SG11201403624WA (en)
WO (1) WO2013133945A1 (en)

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WO2015065717A1 (en) * 2013-10-29 2015-05-07 United Technologies Corporation Pedestals with heat transfer augmenter
US9732617B2 (en) 2013-11-26 2017-08-15 General Electric Company Cooled airfoil trailing edge and method of cooling the airfoil trailing edge
US20150204237A1 (en) * 2014-01-17 2015-07-23 General Electric Company Turbine blade and method for enhancing life of the turbine blade
WO2015116338A1 (en) 2014-01-30 2015-08-06 United Technologies Corporation Trailing edge cooling pedestal configuration for a gas turbine engine airfoil
EP3105425B1 (en) 2014-02-13 2019-03-20 United Technologies Corporation Gas turbine engine component cooling circuit with respirating pedestal
US20150322797A1 (en) 2014-05-09 2015-11-12 United Technologies Corporation Blade element cross-ties
US20150361922A1 (en) * 2014-06-13 2015-12-17 Honeywell International Inc. Heat exchanger designs using variable geometries and configurations
US10196900B2 (en) * 2014-12-15 2019-02-05 United Technologies Corporation Heat transfer pedestals with flow guide features
US10612392B2 (en) 2014-12-18 2020-04-07 United Technologies Corporation Gas turbine engine component with conformal fillet cooling path
US10458252B2 (en) * 2015-12-01 2019-10-29 United Technologies Corporation Cooling passages for a gas path component of a gas turbine engine
US20170175532A1 (en) * 2015-12-21 2017-06-22 United Technologies Corporation Angled heat transfer pedestal
US10570749B2 (en) * 2016-01-22 2020-02-25 United Technologies Corporation Gas turbine blade with pedestal array
US10563518B2 (en) 2016-02-15 2020-02-18 General Electric Company Gas turbine engine trailing edge ejection holes
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10364685B2 (en) 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10443397B2 (en) 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil
US10408062B2 (en) 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
DE102017218886A1 (en) * 2017-10-23 2019-04-25 MTU Aero Engines AG Shovel and rotor for a turbomachine and turbomachine
US10801790B2 (en) 2018-03-16 2020-10-13 Hamilton Sundstrand Corporation Plate fin heat exchanger flexible manifold structure
US11686530B2 (en) 2018-03-16 2023-06-27 Hamilton Sundstrand Corporation Plate fin heat exchanger flexible manifold
US10989067B2 (en) 2018-07-13 2021-04-27 Honeywell International Inc. Turbine vane with dust tolerant cooling system
KR102114681B1 (en) 2018-09-21 2020-05-25 두산중공업 주식회사 Turbine blade having pin-fin array
US10907480B2 (en) * 2018-09-28 2021-02-02 Raytheon Technologies Corporation Ribbed pin fins
EP3653984B1 (en) * 2018-11-16 2023-01-25 Hamilton Sundstrand Corporation Plate fin heat exchanger flexible manifold structure
FR3094032B1 (en) * 2019-03-22 2021-05-21 Safran Aircraft Engines AIRCRAFT TURBOMACHINE BLADE AND ITS MANUFACTURING PROCESS BY LOST WAX MOLDING
US11230929B2 (en) * 2019-11-05 2022-01-25 Honeywell International Inc. Turbine component with dust tolerant cooling system
FR3107920B1 (en) * 2020-03-03 2023-11-10 Safran Aircraft Engines Hollow turbomachine blade and inter-blade platform equipped with projections disrupting the cooling flow
FR3108363B1 (en) * 2020-03-18 2022-03-11 Safran Aircraft Engines Turbine blade with three types of trailing edge cooling holes
US20240044255A1 (en) * 2022-08-02 2024-02-08 Raytheon Technologies Corporation Asymmetric heat transfer member fillet to direct cooling flow
JP2024043164A (en) * 2022-09-16 2024-03-29 三菱重工航空エンジン株式会社 Heat exchange partition
GB202216739D0 (en) * 2022-11-10 2022-12-28 Rolls Royce Plc Tie for a component

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US4236870A (en) 1977-12-27 1980-12-02 United Technologies Corporation Turbine blade
US5197852A (en) 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US5243759A (en) * 1991-10-07 1993-09-14 United Technologies Corporation Method of casting to control the cooling air flow rate of the airfoil trailing edge
US5503529A (en) 1994-12-08 1996-04-02 General Electric Company Turbine blade having angled ejection slot
US6234754B1 (en) * 1999-08-09 2001-05-22 United Technologies Corporation Coolable airfoil structure
US6974308B2 (en) 2001-11-14 2005-12-13 Honeywell International, Inc. High effectiveness cooled turbine vane or blade
US6969230B2 (en) 2002-12-17 2005-11-29 General Electric Company Venturi outlet turbine airfoil
US7175386B2 (en) 2003-12-17 2007-02-13 United Technologies Corporation Airfoil with shaped trailing edge pedestals
US7837440B2 (en) 2005-06-16 2010-11-23 General Electric Company Turbine bucket tip cap
US7311498B2 (en) 2005-11-23 2007-12-25 United Technologies Corporation Microcircuit cooling for blades
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GB0905736D0 (en) 2009-04-03 2009-05-20 Rolls Royce Plc Cooled aerofoil for a gas turbine engine

Also Published As

Publication number Publication date
EP2823151A1 (en) 2015-01-14
WO2013133945A1 (en) 2013-09-12
US9297261B2 (en) 2016-03-29
EP2823151B1 (en) 2018-05-30
EP2823151A4 (en) 2015-06-03
US20130232991A1 (en) 2013-09-12

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