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Title: Combustor with two stage primary fuel tube with concentric members and flow regulating

Abstract

A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication withmore » the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.« less

Authors:
; ;
Publication Date:
Sponsoring Org.:
USDOE
OSTI Identifier:
20014161
DOE Contract Number:  
FC21-95MC32267
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 16 Nov 1999
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; GAS TURBINES; COMBUSTORS; STAGED COMBUSTION; NOZZLES; FUEL INJECTION SYSTEMS

Citation Formats

Parker, D M, Whidden, G L, and Zolyomi, W. Combustor with two stage primary fuel tube with concentric members and flow regulating. United States: N. p., 1999. Web.
Parker, D M, Whidden, G L, & Zolyomi, W. Combustor with two stage primary fuel tube with concentric members and flow regulating. United States.
Parker, D M, Whidden, G L, and Zolyomi, W. 1999. "Combustor with two stage primary fuel tube with concentric members and flow regulating". United States.
@article{osti_20014161,
title = {Combustor with two stage primary fuel tube with concentric members and flow regulating},
author = {Parker, D M and Whidden, G L and Zolyomi, W},
abstractNote = {A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication with the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.},
doi = {},
url = {https://www.osti.gov/biblio/20014161}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1999},
month = {11}
}