Integrated engine shroud for gas turbine engines
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United States of America Patent
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Jan 28, 1992
Grant Date -
N/A
app pub date -
Oct 2, 1989
filing date -
Oct 2, 1989
priority date (Note) -
Expired
status (Latency Note)
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Abstract
An integral 'C' duct for the thrust reverser region of ducted fan gas turbine engines. The integral duct is useful in a turbine engine having a core engine surrounded by an engine casing and nacelle, with a fan at the inlet directing air flow into the bypass duct between core engine and engine nacelle. The 'C' duct basically consists of right and left 'C' shaped ducts with bifurcations (radial flanges) permitting the halves to be fastened together to produce a tubular duct adapted to surround a gas turbine engine and form the inner wall of a bypass duct. The disclosed duct eliminates the prior complex corner fittings connecting the 'C' shaped portion of the duct and the bifurcations and provides simple, integral corners.
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