The Boeing Company

Wan T Chee

Warren E Schmidt

Douglas McLaren

Keith E Therrien

Eric L Aspinall

George W Quigley

Charles C Clausen

Ronald C Johnson

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. Left and right cowl beams (18, 20) extend forward from opposite sides of the forward section of the lower portion of the pylon bifurcation portion (16) and attach to different locations on the forward part of the engine core (22). The cowl beams (18, 20) resist the majority portion of torque forces applied by the engine (12) to the pylon (14).

Pylon and engine installation for ultra-high by-pass turbo-fan engines

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).

Fire-resistant seal

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.

Engine mounting assembly

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).

Vibration isolating engine mount

Composite material structure with integral fire protection

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. The engine mount (20) is dimensioned and the isolators (52, 72) are positioned to locate the elastomeric layers away from the heat of the engine (6).

Aircraft engine mount system with vibration isolators

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. Plugs of resilient material are placed adjacent each end of the support fittings between such ends and the adjacent end walls of their associated compartment. The plugs damp out sideways vibration. Preferably, the resilient material used for vibration damping is resistant to the high temperature that are present in the area of the engine.

Aft engine mount with vibration isolators

Aft engine mount

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.

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Bellevue, WA, United States of America

Wan T Chee