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Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissionsA fuel-air mixer for use in a combustion chamber of a gas turbine engine is provided. The fuel air mixing apparatus comprises an annular fuel injector having a plurality of discrete plain jet orifices, a first swirler wherein the first swirler is located upstream from the fuel injector and a second swirler wherein the second swirler is located downstream from the fuel injector. The plurality of discrete plain jet orifices are situated between the highly swirling airstreams generated by the two radial swirlers. The distributed injection of the fuel between two highly swirling airstreams results in rapid and effective mixing to the desired fuel-air ratio and prevents the formation of local hot spots in the combustor primary zone. A combustor and a gas turbine engine comprising the fuel-air mixer of the present invention are also provided as well as a method using the fuel-air mixer of the present invention.
Document ID
20080008673
Acquisition Source
Glenn Research Center
Document Type
Other - Patent
Authors
Zupanc, Frank J.
Yankowich, Paul R.
Date Acquired
August 24, 2013
Publication Date
June 27, 2006
Subject Category
Mechanical Engineering
Funding Number(s)
CONTRACT_GRANT: NAS3-01136
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-7,065,972
Patent Application
US-Patent-Appl-SN-10/850,871
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