The Boeing Company

Michael W Su

Michael L Sangwin

Thomas J Connelly

Leonard J Hebert

Ronald L Balzer

Jerry Piro

Jeff P Lewis

Steve D Podleski

Robert E Moody

Thomas A Gally

Sean A Newsum

The present invention is a hybrid engine exhaust heat shield assembly that includes a plurality of sections. The plurality of sections include one or more sections formed of titanium (or other high heat resistant material) by a casting process, and one or more sections formed of another heat resistant material produced in a manner other than a casting process. The plurality of sections are aerodynamically shaped for thermal protection of the aft pylon. The other heat resistant material is titanium (or other high heat resistant material) that is formed by a hot formed process, or by a super plastically-formed process. The one or more sections formed by the casting process includes heat (plume) deflector flanges.

Hybrid exhaust heat shield for pylon mounted gas turbine engines

A turbo fan engine nacelle houses an engine which forces engine exhaust through a primary nozzle and a fan nozzle positioned along a common central axis. The primary nozzle is bordered interiorly by a primary nozzle plug and bordered exteriorly by a primary nozzle sleeve. The fan nozzle is bordered interiorly by a core cowl and bordered exteriorly by a fan nozzle sleeve. The primary nozzle plug includes a generally cone shaped outer surface which is concave when viewed in side elevation. The concave outer surface has a radius of curvature (R,). The core cowl has a distal end which is radially spaced from the outer surface of the primary plug by a distance (&Dgr;H) in a direction perpendicular to the central axis. The primary nozzle plug and core cowl define a ratio R,/&Dgr;H between approximately 14 and 18. The distal end of the core cowl has a core cowl radius R,with respect to the central axis. A discharge end of the fan nozzle sleeve has a fan nozzle sleeve radius R,, wherein a ratio R,/R,is between approximately 0.4 and 0.6. The outer surface of the primary plug forms a primary plug angle &phgr;,between approximately 13&deg; and 19&deg; with respect to the central axis at the primary nozzle exit. The proper scaling of these key dimensions thereby defines a primary nozzle which reduces the shock associated noise of the turbo fan engine.

Turbo fan engine nacelle exhaust system with concave primary nozzle plug

A fencing assembly (66) for prohibiting circulation of primary and/or fan airflows (52), (54) into a bounded low pressure region of a jet engine installation. The fencing assembly includes one or more flow control fences. In an exemplary application, the fencing assembly includes a number of fences positioned around the sides of a batcave (48) bounded low pressure region that is located between a primary exhaust nozzle (20) and strut fairings (30). The fencing assembly includes five fences, each fence being connected to either the primary exhaust nozzle or the strut fairings. The five fences include single fences (70), (72) positioned along each lateral side of the batcave; two rear fences (74), (74') positioned circumferentially about rear regions of the batcave; and an arcuate fence (76) positioned near the two rear fences to form a half circle. The fences include a foot portion (78) and an upright portion (80).

Engine flow control device

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Bellevue, WA, United States of America

Michael W Su