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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Works referenced in this record:

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Nathan, Matthew
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Combustion transition duct providing stage 1 tangential turning for turbine engines
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