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Title: Combustor nozzles in gas turbine engines

A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall.
Inventors:
; ; ;
Issue Date:
OSTI Identifier:
1390169
Assignee:
General Electric Company NETL
Patent Number(s):
9,759,426
Application Number:
14/448,321
Contract Number:
FC26-05NT42643
Resource Relation:
Patent File Date: 2014 Jul 31
Research Org:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Other works cited in this record:

Premix combustor
patent, July 1978

Impingement cooled transition duct
patent, January 1988

Method and apparatus for injecting a fuel into a combustor assembly
patent, December 2008

Combustor
patent, May 2015

Staged Multi-Tube Premixing Injector
patent-application, April 2011

Fuel Nozzle With Air Admission Shroud
patent-application, February 2012

Apparatus And Method For Cooling A Combustor Cap
patent-application, March 2012

Turbomachine Combustor Assembly
patent-application, February 2013

Combustor
patent-application, May 2013

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