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

Abstract

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:
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1357523
Patent Number(s):
9,650,904
Application Number:
15/002,429
Assignee:
SIEMENS ENERGY, INC. NETL
DOE Contract Number:  
FE0023955
Resource Type:
Patent
Resource Relation:
Patent File Date: 2016 Jan 21
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Wiebe, David J. Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine. United States: N. p., 2017. Web.
Wiebe, David J. Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine. United States.
Wiebe, David J. Tue . "Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine". United States. https://www.osti.gov/servlets/purl/1357523.
@article{osti_1357523,
title = {Transition duct system with straight ceramic liner for delivering hot-temperature gases in a combustion turbine engine},
author = {Wiebe, David J.},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2017},
month = {5}
}

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