Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

Little, David A.; McQuiggan, Gerard; Wasdell, David L.

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Title: Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

Abstract

A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).

Inventors:: Little, David A.; McQuiggan, Gerard; Wasdell, David L.

Issue Date:: 2016-10-25

Research Org.:: SIEMENS ENERGY, INC., Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1330364

Patent Number(s):: 9476355

Application Number:: 13/408,147

Assignee:: SIEMENS ENERGY, INC. (Orlando, FL)

Patent Classifications (CPCs):: F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS

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F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
F02C3/14 - characterised by the arrangement of the combustion chamber in the plant

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DOE Contract Number:: FC26-05NT42644

Resource Type:: Patent

Resource Relation:: Patent File Date: 2012 Feb 29

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats


                    Little, David A., McQuiggan, Gerard, and Wasdell, David L. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section.  United States: N. p., 2016. 
        Web.

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                    Little, David A., McQuiggan, Gerard, & Wasdell, David L. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section.  United States.

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                    Little, David A., McQuiggan, Gerard, and Wasdell, David L. Tue .  
        "Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section".  United States.  https://www.osti.gov/servlets/purl/1330364.

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@article{osti_1330364,

  title        = {Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section},

  author       = {Little, David A. and McQuiggan, Gerard and Wasdell, David L.},

  abstractNote = {A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2016},

  month        = {10}

}

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Works referenced in this record:

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patent, March 1946

Youngash, Reginald William
US Patent Document 2396068
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Gas Turbine
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Similar Records

Title: Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

Abstract

Citation Formats

Turbine patent, March 1946

Arrangement of Jet Propulsion Engine Elements patent, July 1948

Combustion Gas Turbine Arrangement patent, June 1949

Combustion Apparatus patent, July 1949

Gas turbine power plant patent, September 1951

Gas Turbine Engine with Resonating Combustion Chambers patent, April 1952

Combustion Means for Jet Propulsion Units patent, February 1953

Gas Turbine patent, December 1953

Toroidal combustion chamber patent, November 1961

Diffuser construction patent, January 1969

Compressors for Gas Turbine Engines patent, December 1970

Gas turbine engine structure patent, June 1973

Diffuser including a rotary stage patent, March 1976

Premixed combustor patent, April 1978

Rotating turbine stator patent, June 1984

System for adjusting radial clearance between rotor and stator elements patent, July 1989

Gas generating apparatus patent, June 1994

Part load blade tip clearance control patent, November 2005

Blade tip clearance control patent, August 2006

Blade tip clearance control patent, August 2006

Turbine engine sequenced combustion patent, September 2006

Combustion transition duct providing stage 1 tangential turning for turbine engines patent, May 2010

Diffuser for Gas Turbine System patent-application, November 2011

Turbine
patent, March 1946

Arrangement of Jet Propulsion Engine Elements
patent, July 1948

Combustion Gas Turbine Arrangement
patent, June 1949

Combustion Apparatus
patent, July 1949

Gas turbine power plant
patent, September 1951

Gas Turbine Engine with Resonating Combustion Chambers
patent, April 1952

Combustion Means for Jet Propulsion Units
patent, February 1953

Gas Turbine
patent, December 1953

Toroidal combustion chamber
patent, November 1961

Diffuser construction
patent, January 1969

Compressors for Gas Turbine Engines
patent, December 1970

Gas turbine engine structure
patent, June 1973

Diffuser including a rotary stage
patent, March 1976

Premixed combustor
patent, April 1978

Rotating turbine stator
patent, June 1984

System for adjusting radial clearance between rotor and stator elements
patent, July 1989

Gas generating apparatus
patent, June 1994

Part load blade tip clearance control
patent, November 2005

Blade tip clearance control
patent, August 2006

Blade tip clearance control
patent, August 2006

Turbine engine sequenced combustion
patent, September 2006

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010

Diffuser for Gas Turbine System
patent-application, November 2011