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Title: Gas turbine combustor exit piece with hinged connections

Abstract

An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.

Inventors:
;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1248880
Patent Number(s):
9,322,335
Application Number:
13/834,185
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Mar 15
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION

Citation Formats

Charron, Richard C., and Pankey, William W.. Gas turbine combustor exit piece with hinged connections. United States: N. p., 2016. Web.
Charron, Richard C., & Pankey, William W.. Gas turbine combustor exit piece with hinged connections. United States.
Charron, Richard C., and Pankey, William W.. Tue . "Gas turbine combustor exit piece with hinged connections". United States. doi:. https://www.osti.gov/servlets/purl/1248880.
@article{osti_1248880,
title = {Gas turbine combustor exit piece with hinged connections},
author = {Charron, Richard C. and Pankey, William W.},
abstractNote = {An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Apr 26 00:00:00 EDT 2016},
month = {Tue Apr 26 00:00:00 EDT 2016}
}

Patent:

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