Abstract: A pylon (14) for supporting a turbo-fan jet engine, in particular, an ultra-high by-pass turbo-fan jet engine (12) is disclosed. The pylon (14) attaches to the forward and aft parts of the engine core (22) and supports the engine (12) from an airplane wing (10) while resisting static and dynamic forces applied by the engine and the nacelle of the engine to the pylon. The pylon (14) includes a pylon bifurcation portion(16), having an upper end (23) and a lower end. The upper end (23) is positioned exterior to the fan duct (8) of the engine and is attached to the wing (10). The lower end is positioned inside of the fan duct (8). The lower end further includes an aft section that is attached by lugs (38) to the aft part of the engine core (22), and a forward section that is attached to the forward part of the engine core.

Abstract: A fire-resistant seal formed of an inner layer (20) of elastomer material that is compressible and flexible, a middle layer (22) of ceramic fiber that is fire resistant, and an outer layer (24) of elastic fabric. In the preferred embodiment, the ceramic fiber middle layer (22) totally encloses the elastomer inner layer (20), and the wear-resistant outer layer (24) totally encloses the middle layer (22) and the inner layer (20). In this particular application, the fire-resistant seal (10) has a toroidal-shaped compressible portion (12) and an integrally formed flange portion (14).

Abstract: An engine mounting system where an aft body mounted counter-rotation prop fan engine is mounted to aircraft structure. The engine is connected through a longitudinally extending beam to a mounting strut structure comprising a fore spar, a mid spar and a rear spar. Vertical loads and lateral loads are transmitted from the engine to the beam at forward and rear locations, and these vertical and lateral loads are in turn transmitted to the spars at forward and rear locations. The torque loads from the engine are transmitted at a selected location into the beam, and then transmitted through the beam to the spar or spars at a selected location or locations. The beam can initially be mounted to either the engine or to the spars of the aircraft.

Abstract: An engine mounting system where an aft body mounted counter-rotation prop fan engine is mounted to aircraft structure. The engine is connected through a longitudinally extending beam to a mounting strut structure comprising a fore spar, a mid spar and a rear spar. Vertical loads and lateral loads are transmitted from the engine to the beam at forward and rear locations, and these vertical and lateral loads are in turn transmitted to the spars at forward and rear locations. The torque loads from the engine are transmitted at a selected location into the beam, and then transmitted through the beam to the spar or spars at a selected location or locations. The beam can initially be mounted to either the engine or to the spars of the aircraft.

Abstract: A strut for mounting an engine and isolating the vibration of the engine from the framework of an aircraft to which it is attached. An engine mounting strut (32) includes a forward spar (40), which extends outwardly from a rib (34) of an aircraft (20). An aft spar (62) similarly extends outward from a rib (38) and is pivotally connected to a box beam (42) in a vibration isolation mount (78). The pivotal axis of mount (78) is generally aligned with the longitudinal axis of the box beam. A vibration isolation arm (44) extends from a pivotal connection (82) having an axis generally orthogonal to the longitudinal axis of the box beam and is connected to the forward spar at two spaced-apart vibration isolation mounts (46 and 84). The spars are enclosed with an aerodynamic skin (56) forming a torque box 48, to which are attached forward and aft fairings (58).

Abstract: A load-bearing composite material structure (2, 2') has a plurality of layers of composite material. Each layer includes a matrix material (4) that maintains its structural integrity at 1200.degree. F. for at least five minutes. Preferred matrix materials are polyimide resins. Outer layers that will be directly exposed to a fire are reinforced with a woven fabric (8) that is sufficiently flame resistant and has a sufficiently fine weave to prevent flame penetration at 2000.degree. F. for at least fifteen minutes. The woven fabric (8) is preferably ceramic. The rest of the layers are reinforced with a fibrous material (6) to provide the necessary structural strength. The layers may be laminate cured together to form a single, integral structure (2) or such laminates adhesively bonded to a honeycomb (12).

Abstract: A laterally extending shaft (42) pivotably connects an aft engine mount (20) to a wing strut (4). Vertical isolators (52) are positioned around opposite ends (44) of the shaft (42). Each isolator (52) includes a housing (56) which moves vertically with the shaft (42). Upper and lower shock absorbing members (62, 64) are received into recesses (60) in the housing (56) and abut upper and lower portions of the strut (4). Each of two laterally spaced lateral isolators (72) has an annular isolator member (92) and a hat-shaped housing (78) with a cylindrical wall (80) that is closely received into a passageway (74) in the strut (4). The shaft (42) extends concentrically through and is spaced from the isolators (72). Opposite ends (96, 94) of each isolator member (92) abut a flange (82) on the housing (78) and the engine mount (20). Isolator members (62, 64, 92) include alternating elastomeric and metal layers.

Abstract: An aft engine mount, for use in supporting a jet engine from a wing of an aircraft occupies a minimum amount of the space between the wind and the engine, permitting a maximum vertical dimension (depth) of the engine-mounting strut. The mount includes a yoke, the arms of which are pivotally attached to the engine. The yoke is in turn attached to a vibration isolator mounted within an isolator housing that is affixed to the engine-mounting strut. The isolator housing is preferably mounted in a recess in a lower surface of the strut to provide for maximum effective strut height. The vibration isolator includes a pair of support fittings, each of which is contained within an associated compartment formed in the isolator housing. Each support fitting includes first and second ends surrounded by a resilient material to provide a close fit of the support fitting within the housing. The resilient material surrounding the ends of the support fitting provides damping of vertical vibration.

Abstract: In an aircraft having a jet engine mounted to and beneath a wing thereof wherein the engine is a predetermined distance from the wing and wherein further the engine is mounted on a strut affixed to the wing, a low-profile engine mount assembly is attachable to the strut and the engine to hold the engine on the strut. The engine mount assembly is constructed and arranged to occupy a minimum portion of the distance between the engine and the wing so as to provide the maximum strut vertical dimension (depth), thereby providing significant benefit in length-to-stiffness ratio in the strut. The engine mount is further constructed and arranged to accommodate longitudinal growth of the engine due to thermal expansion and includes a yoke assembly having a first arm and a second arm, the yoke being mounted to the strut so as to permit pivotal movement of the yoke about an axis substantially orthogonal to the engine axis.

Abstract: An engine inlet sound diffusion structure for use with a turbofan engine is constructed of nonmetallic composite materials. An inner perforated skin of the diffuser is made up of continuously wound composite material filaments. A honeycomb core is sandwiched between the inner porous skin and a nonporous outer skin also comprised of continuously wound filaments. The perforations in the inner skin are formed directly in the skin by programmed placement of the filaments during the winding process. The formation of the perforations can be assisted by the use of a mandrel having spikes formed on its outer surface.

Abstract: In a jet engine in which the engine cowling includes an inlet cowl and an engine containment case and in which at least a portion of the interior surface of the inlet cowl is covered by an acoustic treatment material, a system for attaching the inlet cowl to the engine containment case icludes an attachment ring that is substantially U-shaped in cross section having a web and first and second legs extending orthogonally from the web. The first leg abuts an engine flange that is a part of the engine containment case. The first leg and engine flange are secured to one another by threaded fasteners. The web is attached to the acoustic treatment material by fasteners that pass through the web and the acoustic treatment material. The acoustic treatment material is effective up to the interface between the inlet cowl and the engine containment case.