F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
F02K 1/46 (2006.01) B64D 33/04 (2006.01) F02K 1/40 (2006.01)
Patent
CA 2648765
Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.
Cette invention concerne des configurations de sortie de tuyère ainsi que des systèmes et procédés relatifs. Un système aéronautique selon un mode de réalisation comprend une tuyère d'échappement de moteur à réaction, présentant une surface d'écoulement interne et une ouverture de sortie. L'ouverture de sortie a un périmètre qui comprend des saillies multiples s'étendant dans un sens arrière. Les parties arrière des saillies individuelles avoisinantes sont mutuellement séparées par un espace. Une caractéristique géométrique des saillies multiples peut changer de manière monotone le long d'une partie au moins du périmètre. Les saillies proches d'un pylône de support et/ou d'une chemise thermique associée peuvent adopter des configurations particulières comprenant une profondeur d'immersion supérieure à celle des autres saillies.
Mengle Vinod G.
Thomas Russell H.
Smart & Biggar
The Boeing Company
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