Cooling supply system for stage 3 bucket of a gas turbine

Eldrid, Sacheverel Quentin; Burns, James Lee; Palmer, Gene David; Leone, Sal Albert; Drlik, Gary Joseph; Gibler, Edward Eugene

Title: Cooling supply system for stage 3 bucket of a gas turbine

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Abstract

In a land based gas turbine including a compressor, a combustor and turbine section including at least three stages, an improvement comprising an inlet into a third stage nozzle from the compressor for feeding cooling air from the compressor to the third stage nozzle; at least one passageway running substantially radially through each airfoil of the third stage nozzle and an associated diaphragm, into an annular space between the rotor and the diaphragm; and passageways communicating between the annular space and individual buckets of the third stage.

Inventors:

Eldrid, Sacheverel Quentin ^[1]; Burns, James Lee ^[2]; Palmer, Gene David ^[3]; Leone, Sal Albert ^[4]; Drlik, Gary Joseph ^[5]; Gibler, Edward Eugene ^[6]

Saratoga Springs, NY
Schenectady, NY
Clifton Park, NY
Scotia, NY
Fairfield, OH
Cincinnati, OH

Issue Date:: 2002-01-01

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

OSTI Identifier:: 874472

Patent Number(s):: 6397604

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

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

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F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/088 - {in a closed cavity}
F01D9/065 - {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

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

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DOE Contract Number:: FC21-95MC31176

Resource Type:: Patent

Country of Publication:: United States

Language:: English

Subject:: cooling; supply; stage; bucket; gas; turbine; land; based; including; compressor; combustor; section; stages; improvement; comprising; inlet; third; nozzle; feeding; air; passageway; running; substantially; radially; airfoil; associated; diaphragm; annular; space; rotor; passageways; communicating; individual; buckets; gas turbine; cooling air; turbine section; third stage; /60/415/

Citation Formats


                    Eldrid, Sacheverel Quentin, Burns, James Lee, Palmer, Gene David, Leone, Sal Albert, Drlik, Gary Joseph, and Gibler, Edward Eugene. Cooling supply system for stage 3 bucket of a gas turbine.  United States: N. p., 2002. 
        Web.

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                    Eldrid, Sacheverel Quentin, Burns, James Lee, Palmer, Gene David, Leone, Sal Albert, Drlik, Gary Joseph, & Gibler, Edward Eugene. Cooling supply system for stage 3 bucket of a gas turbine.  United States.

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                    Eldrid, Sacheverel Quentin, Burns, James Lee, Palmer, Gene David, Leone, Sal Albert, Drlik, Gary Joseph, and Gibler, Edward Eugene. Tue .  
        "Cooling supply system for stage 3 bucket of a gas turbine".  United States.  https://www.osti.gov/servlets/purl/874472.

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@article{osti_874472,

  title        = {Cooling supply system for stage 3 bucket of a gas turbine},

  author       = {Eldrid, Sacheverel Quentin and Burns, James Lee and Palmer, Gene David and Leone, Sal Albert and Drlik, Gary Joseph and Gibler, Edward Eugene},

  abstractNote = {In a land based gas turbine including a compressor, a combustor and turbine section including at least three stages, an improvement comprising an inlet into a third stage nozzle from the compressor for feeding cooling air from the compressor to the third stage nozzle; at least one passageway running substantially radially through each airfoil of the third stage nozzle and an associated diaphragm, into an annular space between the rotor and the diaphragm; and passageways communicating between the annular space and individual buckets of the third stage.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2002},

  month        = {1}

}

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