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

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

OSTI Identifier:: 1330364

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

Patent Number(s):: 9,476,355

Application Number:: 13/408,147

Contract Number:: FC26-05NT42644

Resource Relation:: Patent File Date: 2012 Feb 29

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

Sponsoring Org:: USDOE

Country of Publication:: United States

Language:: English

Subject:: 42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

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Other works cited 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
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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
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