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Title: Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine

A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straight path segment (26) for receiving a gas flow from a respective combustor. A straight ceramic liner (40) may be inwardly disposed onto a metal outer shell (38) along the straight path segment of the exit piece. Structural arrangements are provided to securely attach the ceramic liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.
Inventors:
Issue Date:
OSTI Identifier:
1357523
Assignee:
SIEMENS ENERGY, INC. NETL
Patent Number(s):
9,650,904
Application Number:
15/002,429
Contract Number:
FE0023955
Resource Relation:
Patent File Date: 2016 Jan 21
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

Other works cited in this record:

Integrated ceramic-metal combustor
patent, June 1977

Annular combustor having ceramic liner
patent, April 1983

Gas turbine gas duct arrangement
patent, January 1998

Conbustor having a ceramic matrix composite liner
patent, June 2002

Cooling air recycling for gas turbine transition duct end frame and related method
patent, July 2002

Bolting configuration for joining ceramic combustor liner to metal mounting attachments
patent, June 2009

Assembly for directing combustion gas
patent, October 2012

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patent, March 2014

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patent, September 2015

Apparatus Comprising a CMC-Comprising Body and Compliant Porous Element Preloaded Within an Outer Metal Shell
patent-application, October 2009

Cooling Structure For Gas Turbine Transition Duct
patent-application, December 2010

Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine
patent-application, May 2012

Method of forming a multi-panel outer wall of a component for use in a gas turbine engine
patent-application, November 2012

Combustor transition duct assembly with inner liner
patent-application, January 2014

Air Regulation For Film Cooling And Emission Control Of Combustion Gas Structure
patent-application, November 2014

Assembly for directing combustion gas
patent-application, July 2015

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