Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method

Lacy, Benjamin Paul; Sezer, Ibrahim; VanTassel, Brad Wilson

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Title: Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method

Abstract

A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.

Inventors:: Lacy, Benjamin Paul; Sezer, Ibrahim; VanTassel, Brad Wilson

Issue Date:: Tue Feb 07 00:00:00 EST 2023

Research Org.:: General Electric Co., Schenectady, NY (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1987104

Patent Number(s):: 11572803

Application Number:: 17/816,574

Assignee:: General Electric Company (Schenectady, NY)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES

F - MECHANICAL ENGINEERING 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

Show more

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D25/12 - Cooling
F01D5/187 - {Convection cooling}
F01D9/04 - forming ring or sector
F01D9/065 - {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

F - MECHANICAL ENGINEERING 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
F05D2220/30 - in turbines
F05D2240/121 - related to the leading edge of a stator vane
F05D2240/128 - Nozzles
F05D2260/202 - by film cooling
F05D2260/204 - by the use of microcircuits

Show less

DOE Contract Number:: FE0031611

Resource Type:: Patent

Resource Relation:: Patent File Date: 08/01/2022

Country of Publication:: United States

Language:: English

Citation Formats


                    Lacy, Benjamin Paul, Sezer, Ibrahim, and VanTassel, Brad Wilson. Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method.  United States: N. p., 2023. 
        Web.

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                    Lacy, Benjamin Paul, Sezer, Ibrahim, & VanTassel, Brad Wilson. Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method.  United States.

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                    Lacy, Benjamin Paul, Sezer, Ibrahim, and VanTassel, Brad Wilson. Tue .  
        "Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method".  United States.  https://www.osti.gov/servlets/purl/1987104.

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@article{osti_1987104,

  title        = {Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method},

  author       = {Lacy, Benjamin Paul and Sezer, Ibrahim and VanTassel, Brad Wilson},

  abstractNote = {A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Tue Feb 07 00:00:00 EST 2023},

  month        = {Tue Feb 07 00:00:00 EST 2023}

}

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Title: Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method

Abstract

Citation Formats

Turbine engine airfoil patent, September 2020

Near wall leading edge cooling channel for airfoil patent, May 2021

Engine Component with Hollow Turbulators patent-application, February 2019

Dual-Wall Airfoil with Leading Edge Cooling Slot patent-application, February 2020

Curved Passages for a Turbine Component patent-application, November 2012

Near Wall Leading Edge Cooling Channel for Airfoil patent-application, November 2020

Cooled turbine airfoils and methods of manufacture patent, December 2007

Turbine vane with counter flow cooling passages patent, August 2013

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Turbine nozzle with cooling channel coolant discharge plenum patent, June 2018

Gas turbine engine components having internal hybrid cooling cavities patent, October 2019

Airfoil leading edge impingement cooling patent, May 2020

Edge coupon including cooling circuit for airfoil patent, March 2020

Method and system for providing cooling for turbine components patent, August 2016

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Dual-wall impingement cavity for components of gas turbine engines patent, July 2020

Method Of Manufacturing A Component And Thermal Management Process patent-application, March 2015

Components for Gas Turbine Engines patent-application, December 2020

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Turbine Engine Component with a Core Tie Hole patent-application, October 2018

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Micro channel and methods of manufacturing a micro channel patent, June 2017

Curved electrode and method for electrical discharge machining curved cooling holes patent, June 1997

Coolable airfoil for a gas turbine engine patent, August 2000

Dual Fuel Lance with Cooling Microchannels patent-application, March 2020

Hot gas path component trailing edge having near wall cooling features patent, May 2018

Components with conformal curved film holes and methods of manufacture patent, March 2014

Leading edge cooling channel for airfoil patent, July 2019

Turbine Airfoils with Micro Cooling Features patent-application, February 2017

System and Method for Cooling Trailing Edge and/or Leading Edge of Hot Gas Flow Path Component patent-application, September 2017

Turbine blade with near wall cooling channels patent, July 2014

Turbine rotor blade with super cooling patent, October 2014

Gas Turbine Engine and Cooled Flowpath Component Therefor patent-application, August 2012

Method for providing a curved cooling channel in a gas turbine component as well as coolable blade for a gas turbine component patent, November 2003

Turbine Blade Cooling patent-application, January 2019

Gas turbine engines with improved leading edge airfoil cooling patent, March 2021

System and Method for Near Wall Cooling for Turbine Component patent-application, December 2018

Curved cooling passages for a turbine component patent, June 2014

Apparatus for cooling a platform of a turbine component patent, September 2013

Turbine nozzle with inner band and outer band cooling patent, July 2018

System and method for cooling turbine shroud patent, March 2019

Turbine Airfoil Cooling System with Leading Edge Impingement Cooling System and Nearwall Impingement System patent-application, March 2017

Hot gas path component cooling system patent, February 2014

Leading edge hybrid cavities and cores for airfoils of gas turbine engine patent, November 2020

Turbine engine airfoil
patent, September 2020

Near wall leading edge cooling channel for airfoil
patent, May 2021

Engine Component with Hollow Turbulators
patent-application, February 2019

Dual-Wall Airfoil with Leading Edge Cooling Slot
patent-application, February 2020

Curved Passages for a Turbine Component
patent-application, November 2012

Near Wall Leading Edge Cooling Channel for Airfoil
patent-application, November 2020

Cooled turbine airfoils and methods of manufacture
patent, December 2007

Turbine vane with counter flow cooling passages
patent, August 2013

Turbine blade with near wall cooling channels
patent, March 2014

Bore-Cooled Film Dispensing Pedestals
patent-application, July 2016

Turbine Blade with Near Wall Microcircuit Edge Cooling
patent-application, June 2015

Turbine nozzle with cooling channel coolant discharge plenum
patent, June 2018

Gas turbine engine components having internal hybrid cooling cavities
patent, October 2019

Airfoil leading edge impingement cooling
patent, May 2020

Edge coupon including cooling circuit for airfoil
patent, March 2020

Method and system for providing cooling for turbine components
patent, August 2016

Airfoil leading edge cooling channels
patent, April 2020

Dual-wall impingement cavity for components of gas turbine engines
patent, July 2020

Method Of Manufacturing A Component And Thermal Management Process
patent-application, March 2015

Components for Gas Turbine Engines
patent-application, December 2020

Turbine airfoil with endwall horseshoe cooling slot
patent, March 2009

Hot gas path component having near wall cooling features
patent, November 2017

Turbine Engine Component with a Core Tie Hole
patent-application, October 2018

Cooling Assembly for a Turbine Assembly
patent-application, October 2021

Micro channel and methods of manufacturing a micro channel
patent, June 2017

Curved electrode and method for electrical discharge machining curved cooling holes
patent, June 1997

Coolable airfoil for a gas turbine engine
patent, August 2000

Dual Fuel Lance with Cooling Microchannels
patent-application, March 2020

Hot gas path component trailing edge having near wall cooling features
patent, May 2018

Components with conformal curved film holes and methods of manufacture
patent, March 2014

Leading edge cooling channel for airfoil
patent, July 2019

Turbine Airfoils with Micro Cooling Features
patent-application, February 2017

System and Method for Cooling Trailing Edge and/or Leading Edge of Hot Gas Flow Path Component
patent-application, September 2017

Turbine blade with near wall cooling channels
patent, July 2014

Turbine rotor blade with super cooling
patent, October 2014

Gas Turbine Engine and Cooled Flowpath Component Therefor
patent-application, August 2012

Method for providing a curved cooling channel in a gas turbine component as well as coolable blade for a gas turbine component
patent, November 2003

Turbine Blade Cooling
patent-application, January 2019

Gas turbine engines with improved leading edge airfoil cooling
patent, March 2021

System and Method for Near Wall Cooling for Turbine Component
patent-application, December 2018

Curved cooling passages for a turbine component
patent, June 2014

Apparatus for cooling a platform of a turbine component
patent, September 2013

Turbine nozzle with inner band and outer band cooling
patent, July 2018

System and method for cooling turbine shroud
patent, March 2019

Turbine Airfoil Cooling System with Leading Edge Impingement Cooling System and Nearwall Impingement System
patent-application, March 2017

Hot gas path component cooling system
patent, February 2014

Leading edge hybrid cavities and cores for airfoils of gas turbine engine
patent, November 2020