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Mixer Assembly for a Gas Turbine EngineA mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
Document ID
20180002533
Acquisition Source
Glenn Research Center
Document Type
Other - Patent
Authors
Dai, Zhongtao
Cohen, Jeffrey M.
Fotache, Catalin G.
Smith, Lance L.
Hautman, Donald J.
Date Acquired
April 24, 2018
Publication Date
March 20, 2018
Subject Category
Aircraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NNC08CA92C
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-9,920,932
Patent Application
US-Patent-Appl-SN-14/593,877

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