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

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:

Combustion Apparatus
patent, July 1949

Nathan, Matthew
US Patent Document 2,475,911
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/2475911

Gas Turbine Power Plant
patent, September 1951

Owner, F.; Marchant, F.
US Patent Document 2,567,079
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/2567079

Turbine engine sequenced combustion
patent, September 2006

Little, David
US Patent Document 7,107,773
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/7107773

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

Bancalari, Eduardo; Wilson, Jody; Little, David A.
US Patent Document 7,721,547
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/7721547

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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

Combustion Apparatus patent, July 1949

Gas Turbine Power Plant patent, September 1951

Turbine engine sequenced combustion patent, September 2006

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

Combustion Apparatus
patent, July 1949

Gas Turbine Power Plant
patent, September 1951

Turbine engine sequenced combustion
patent, September 2006

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