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Title: Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine

Abstract

A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone (43) upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture (24) into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas (44) such that a peak temperature (46) of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature (50) of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle (118).

Inventors:
; ; ; ;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1495322
Patent Number(s):
10,139,111
Application Number:
14/228,883
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2014 Mar 28
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Laster, Walter R., Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob, and Fox, Timothy A. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine. United States: N. p., 2018. Web.
Laster, Walter R., Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob, & Fox, Timothy A. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine. United States.
Laster, Walter R., Martin, Scott M., Portillo Bilbao, Juan Enrique, Hardes, Jacob, and Fox, Timothy A. Tue . "Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1495322.
@article{osti_1495322,
title = {Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine},
author = {Laster, Walter R. and Martin, Scott M. and Portillo Bilbao, Juan Enrique and Hardes, Jacob and Fox, Timothy A.},
abstractNote = {A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone (43) upstream of the secondary fuel stage to ignite working gas The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture (24) into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas (44) such that a peak temperature (46) of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature (50) of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle (118).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2018},
month = {11}
}

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