Exhaust mixer with offset lobes
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United States of America Patent
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Aug 10, 2021
Grant Date -
Jan 15, 2015
app pub date -
Jul 9, 2013
filing date -
Jul 9, 2013
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Abstract
An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.
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