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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:
; ; ; ; ;
Issue Date:
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

Other works cited in this record:

Diffuser for Centrifugal Compressor
patent, August 1967

Tail pipe of gas turbine combustor and gas turbine combustor having the same tail pipe
patent, November 1999

Combustion chamber intermediate part for a gas turbine
patent, November 2007

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

Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
patent, November 2011

Transition with a linear flow path for use in a gas turbine engine
patent, February 2012

Modular transvane assembly
patent, July 2012

Assembly for directing combustion gas
patent, October 2012

Assembly for directing combustion gas
patent, April 2016

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