Abstract: A compressor bleed air passageway includes a duct having an upstream section (48) which terminates in a baffle (44) and a downstream duct section (54) having a forward portion (56) which surrounds the baffle (44). Bleed air flow through openings (58) in the baffle wall (52). This reduces velocity of the bleed air stream at the duct discharge port to a value equal to or less than Mach 1.0. The baffle (44) has virtually no effect on a low-velocity, low-pressure air stream. The downstream duct section (54) may be perforated and surrounded by outer wall (64) to form sound-absorbing chambers (66).

Abstract: Wall deflections of a multi-lobe type noise suppressing nozzle are minimized without the use of external struts and by the use of only a single internal strut per lobe. The lobes have either a substantially elliptical or substantially circular shape in cross section and they merge into valley regions of substantially circular curvature in cross section. The internal struts and thickened sidewall portions of the lobes define a structural ring providing hoop and bending strength at the center of the nozzle. The thickened sidewall sections of the lobes are welded to shaped sheet metal crown and forward valley sections to form the nozzle. Wall portions of the nozzle are thinned by the chemical milling for the purpose of weight reduction.

Abstract: A thrust reverser suitable for reversing the flow direction of the fan air of a fan jet engine is disclosed. The thrust reverser comprises a cascade section and a fan duct blocker section. The cascade section includes a series of cascade elements mounted in a side-by-side manner about a portion of the engine nacelle for rotation through an arc of 90.degree. about longitudinal axes lying generally parallel to the direction of fan air flow. Each cascade element includes an inner panel, an outer panel, and a series of vanes located between the inner and outer panels. Rotation is between a closed position whereat the inner panel forms a portion of the fan air duct and the outer panel forms a portion of the outer surface of the nacelle, and an open position whereat the vanes define passageways adapted to reverse fan air flow i.e., direct fan air flow back toward the front of the engine.