Convergent divergent exit nozzle for a gas turbine engine

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United States of America Patent

PATENT NO 10371092
APP PUB NO 20160195038A1
SERIAL NO

14817611

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

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Patent Owner(s)

  • UNITED TECHNOLOGIES CORPORATION

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Malecki, Robert E Storrs, US 32 275
Petrenko, Oleg Danbury, US 10 67
Sidelkovskiy, Dmitriy B Ellington, US 21 93
Zysman, Steven H Amston, US 41 600

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