Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines
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United States of America Patent
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Jul 27, 2010
Grant Date -
Dec 11, 2008
app pub date -
Jun 5, 2007
filing date -
Jun 5, 2007
priority date (Note) -
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Abstract
An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is positioned substantially coaxial with the engine shroud and extends forwardly into the fan duct to provide an interstitial mixer duct between the mixer duct shell and the core engine shroud. The aft portion of the mixer duct shell extends over a turbine exhaust frame, an attached mixer (if included), and a tail cone exhaust plug. The mixer duct shell can reduce noise and plume exhaust heat radiated from aircraft turbofan engines.
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