Film cooling for a closed loop cooled airfoil

Burdgick, Steven Sebastian; Yu, Yufeng Phillip; Itzel, Gary Michael

Title: Film cooling for a closed loop cooled airfoil

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Abstract

Turbine stator vane segments have radially inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. At least one film cooling hole is defined through a wall of at least one of the cavities for flow communication between an interior of the cavity and an exterior of the vane. The film cooling hole(s) are defined adjacent a potential low LCF life region, so that cooling medium that bleeds out through the film cooling hole(s) reduces a thermal gradient in a vicinity thereof, thereby the increase the LCF life of that region.

Inventors:

Burdgick, Steven Sebastian ^[1]; Yu, Yufeng Phillip ^[2]; Itzel, Gary Michael ^[2]

Schenectady, NY
Simpsonville, SC

Issue Date:: 2003-01-01

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

OSTI Identifier:: 874986

Patent Number(s):: 6506013

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

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/186 - {Film cooling
F01D5/188 - {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall}

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
F05D2260/201 - by impingement of a fluid
F05D2260/202 - by film cooling
F05D2260/205 - Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
F05D2260/2322 - steam

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DOE Contract Number:: FC21-95MC31176

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: film; cooling; closed; loop; cooled; airfoil; turbine; stator; vane; segments; radially; inner; outer; walls; vanes; extending; therebetween; compartmentalized; impingement; plates; steam; flowing; wall; plenum; passes; plate; upper; surface; spent; flows; cavities; inserts; return; surfaces; hole; defined; flow; communication; interior; cavity; exterior; holes; adjacent; potential; lcf; life; region; medium; bleeds; reduces; thermal; gradient; vicinity; increase; upper surface; steam flow; radially inner; cooled air; vanes extend; /415/416/

Citation Formats


                    Burdgick, Steven Sebastian, Yu, Yufeng Phillip, and Itzel, Gary Michael. Film cooling for a closed loop cooled airfoil.  United States: N. p., 2003. 
        Web.

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                    Burdgick, Steven Sebastian, Yu, Yufeng Phillip, & Itzel, Gary Michael. Film cooling for a closed loop cooled airfoil.  United States.

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                    Burdgick, Steven Sebastian, Yu, Yufeng Phillip, and Itzel, Gary Michael. Wed .  
        "Film cooling for a closed loop cooled airfoil".  United States.  https://www.osti.gov/servlets/purl/874986.

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@article{osti_874986,

  title        = {Film cooling for a closed loop cooled airfoil},

  author       = {Burdgick, Steven Sebastian and Yu, Yufeng Phillip and Itzel, Gary Michael},

  abstractNote = {Turbine stator vane segments have radially inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. At least one film cooling hole is defined through a wall of at least one of the cavities for flow communication between an interior of the cavity and an exterior of the vane. The film cooling hole(s) are defined adjacent a potential low LCF life region, so that cooling medium that bleeds out through the film cooling hole(s) reduces a thermal gradient in a vicinity thereof, thereby the increase the LCF life of that region.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2003},

  month        = {1}

}

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