Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

Lee, Ching-Pang; Heneveld, Benjamin E.; Brown, Glenn E.; Klinger, Jill

Title: Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

Abstract

A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Inventors:: Lee, Ching-Pang; Heneveld, Benjamin E.; Brown, Glenn E.; Klinger, Jill

Issue Date:: 2015-05-26

Research Org.:: Siemens Aktiengesellschaft, Munchen, DE (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1182596

Patent Number(s):: 9039371

Application Number:: 14/068,070

Assignee:: Siemens Aktiengesellschaft (Munchen, DE)

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

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/187 - {Convection cooling}
F01D9/02 - Nozzles

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
F05D2240/122 - related to the trailing edge of a stator vane
F05D2240/304 - related to the trailing edge of a rotor blade
F05D2260/201 - by impingement of a fluid
F05D2260/2212 - by creating turbulence

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02T - CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
Y02T50/60 - Efficient propulsion technologies

Show less

DOE Contract Number:: SC0001359

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; 17 WIND ENERGY

Citation Formats


                    Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., and Klinger, Jill. Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements.  United States: N. p., 2015. 
        Web.

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                    Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., & Klinger, Jill. Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements.  United States.

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                    Lee, Ching-Pang, Heneveld, Benjamin E., Brown, Glenn E., and Klinger, Jill. Tue .  
        "Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements".  United States.  https://www.osti.gov/servlets/purl/1182596.

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@article{osti_1182596,

  title        = {Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements},

  author       = {Lee, Ching-Pang and Heneveld, Benjamin E. and Brown, Glenn E. and Klinger, Jill},

  abstractNote = {A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2015},

  month        = {5}

}

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Similar Records

Title: Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

Abstract

Citation Formats

Transpiration Cooled Blades For Turbines, Compressors, And The Like patent, March 1966

Coolable wall patent, October 1978

Air-cooled turbine blade patent, January 1980

Turbine blade patent, December 1980

Cooled turbine vane patent, October 1981

Film cooled vanes and turbines patent, September 1988

Internally cooled airfoil patent, September 1993

Cooled aerofoil blade for vane for a gas turbine engine patent, November 1993

Chordally bifurcated turbine blade patent, October 1994

Cooled airfoils for a gas turbine engine patent, December 1997

Turbomachinery airfoil with optimized heat transfer patent, August 1999

Multiple impingement airfoil cooling patent, January 2001

Low cost airfoil cooling circuit with sidewall impingement cooling chambers patent, March 2001

Coolable airfoil structure patent, May 2001

Gas turbine cooling moving blade patent, July 2001

Turbine blade with preferentially-cooled trailing edge pressure wall patent, August 2001

Air-cooled turbine blade patent, August 2002

Crossover cooled airfoil trailing edge patent, August 2003

Multiple impingement cooled structure patent, August 2004

Impingement cooling of gas turbine blades or vanes patent, June 2006

Vortex cooling system for a turbine blade patent, October 2006

Turbine blade cooling system patent, February 2008

Turbine blade with cooling and with improved service life patent, March 2010

Turbine airfoil with multiple impingement cooling circuit patent, April 2010

Two piece hollow turbine blade with serpentine cooling circuits patent, January 2011

Film-cooling augmentation device and turbine airfoil incorporating the same patent, November 2011

Turbine blade with serpentine cooling circuit formed within the tip shroud patent, January 2012

Turbine blade with multi-impingement cooling patent, March 2013

Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method patent-application, April 2009

Turbine Blade Incorporating Trailing Edge Cooling Design patent-application, June 2013

Designing a Turbine Blade Cooling System Using a Generalised Regression Genetic Algorithm journal, January 2003

Transpiration Cooled Blades For Turbines, Compressors, And The Like
patent, March 1966

Coolable wall
patent, October 1978

Air-cooled turbine blade
patent, January 1980

Turbine blade
patent, December 1980

Cooled turbine vane
patent, October 1981

Film cooled vanes and turbines
patent, September 1988

Internally cooled airfoil
patent, September 1993

Cooled aerofoil blade for vane for a gas turbine engine
patent, November 1993

Chordally bifurcated turbine blade
patent, October 1994

Cooled airfoils for a gas turbine engine
patent, December 1997

Turbomachinery airfoil with optimized heat transfer
patent, August 1999

Multiple impingement airfoil cooling
patent, January 2001

Low cost airfoil cooling circuit with sidewall impingement cooling chambers
patent, March 2001

Coolable airfoil structure
patent, May 2001

Gas turbine cooling moving blade
patent, July 2001

Turbine blade with preferentially-cooled trailing edge pressure wall
patent, August 2001

Air-cooled turbine blade
patent, August 2002

Crossover cooled airfoil trailing edge
patent, August 2003

Multiple impingement cooled structure
patent, August 2004

Impingement cooling of gas turbine blades or vanes
patent, June 2006

Vortex cooling system for a turbine blade
patent, October 2006

Turbine blade cooling system
patent, February 2008

Turbine blade with cooling and with improved service life
patent, March 2010

Turbine airfoil with multiple impingement cooling circuit
patent, April 2010

Two piece hollow turbine blade with serpentine cooling circuits
patent, January 2011

Film-cooling augmentation device and turbine airfoil incorporating the same
patent, November 2011

Turbine blade with serpentine cooling circuit formed within the tip shroud
patent, January 2012

Turbine blade with multi-impingement cooling
patent, March 2013

Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method
patent-application, April 2009

Turbine Blade Incorporating Trailing Edge Cooling Design
patent-application, June 2013

Designing a Turbine Blade Cooling System Using a Generalised Regression Genetic Algorithm
journal, January 2003