Ducting arrangement for cooling a gas turbine structure

Lee, Ching-Pang; Morrison, Jay A.

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Title: Ducting arrangement for cooling a gas turbine structure

Abstract

A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).

Inventors:: Lee, Ching-Pang; Morrison, Jay A.

Issue Date:: 2015-07-21

Research Org.:: Siemens Energy, Inc., Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1195939

Patent Number(s):: 9085981

Application Number:: 13/655,675

Assignee:: Siemens Energy, Inc. (Orlando, FL)

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
F01D9/023 - {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines

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
F05D2260/20 - Heat transfer, e.g. cooling
F05D2260/202 - by film cooling

F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F23R2900/03045 - Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
F23R3/002 - {Wall structures
F23R3/06 - Arrangement of apertures along the flame tube
F23R3/54 - Reverse-flow combustion chambers

Show less

DOE Contract Number:: FC26-05NT42644

Resource Type:: Patent

Resource Relation:: Patent File Date: 2012 Oct 19

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats


                    Lee, Ching-Pang, and Morrison, Jay A. Ducting arrangement for cooling a gas turbine structure.  United States: N. p., 2015. 
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                    Lee, Ching-Pang, & Morrison, Jay A. Ducting arrangement for cooling a gas turbine structure.  United States.

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                    Lee, Ching-Pang, and Morrison, Jay A. Tue .  
        "Ducting arrangement for cooling a gas turbine structure".  United States.  https://www.osti.gov/servlets/purl/1195939.

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@article{osti_1195939,

  title        = {Ducting arrangement for cooling a gas turbine structure},

  author       = {Lee, Ching-Pang and Morrison, Jay A.},

  abstractNote = {A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2015},

  month        = {7}

}

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