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Title: Transition duct system with arcuate 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 an arcuate connecting segment (36). An arcuate ceramic liner (60) may be inwardly disposed onto a metal outer shell (38) along the arcuate connecting 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:
1407947
Patent Number(s):
9,810,434
Application Number:
15/002,437
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

Citation Formats

Wiebe, David J. Transition duct system with arcuate 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 arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine. United States.
Wiebe, David J. Tue . "Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine". United States. doi:. https://www.osti.gov/servlets/purl/1407947.
@article{osti_1407947,
title = {Transition duct system with arcuate 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 an arcuate connecting segment (36). An arcuate ceramic liner (60) may be inwardly disposed onto a metal outer shell (38) along the arcuate connecting 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 = {Tue Nov 07 00:00:00 EST 2017},
month = {Tue Nov 07 00:00:00 EST 2017}
}

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Works referenced in this record:

Thermal Machine
patent-application, May 2011