Gas flow path for a gas turbine engine

Title: Gas flow path for a gas turbine engine

A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.

Inventors:: Montgomery, Matthew D.; Charron, Richard C.; Snyder, Gary D.; Pankey, William W.; Mayer, Clinton A.; Hettinger, Benjamin G.

Issue Date:: 2017-03-14

OSTI Identifier:: 1346959

Assignee:: SIEMENS ENERGY, INC. NETL

Patent Number(s):: 9,593,853

Application Number:: 14/185,352

Contract Number:: FC26-05NT42644

Resource Relation:: Patent File Date: 2014 Feb 20

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

Sponsoring Org:: USDOE

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

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Works referenced in this record:

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Assembly for directing combustion gas
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Charron, Richard C.; Little, David A.; Snyder, Gary D.
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