Rohr Industries, Inc.

Rohr, Inc.

Dale W Lawson

Frank J Riel

Stanley L Beggs

A thrust reverser for use with turbo-fan aircraftt engines; in particular engines mounted on an aircraft fuselage. Four radially spaced openings around the engine each is closed by a stowed door. An actuator is provided to move each door to a deployed position extending through the opening, near the aft end of the opening. The aft end of each door extends into the tailpipe and directs air flow out through the opening, where the forward end of the door further directs the flow in an outwardly and forwardly direction. Doors adjacent to the aircraft fuselage are shaped to guide reverse airflow away from direct impingement on the fuselage. Deployable strakes are mounted on doors adjacent to the fuselage. The strakes are typically spring biased toward a stowed position flat against the inside of the door and are moved to a deployed position by aerodynamic forces when the doors are deployed. In the deployed position, they are located so as to deflect air flow away from the fuselage or other structures.

Aircraft turbine engine thrust reverser

Broad band noise attenuation sandwich panels utilizing a cellular core positioned between and bonded to two facing sheets by an adhesive bonding system. One facing sheet is perforated and the other imperforate. A thin sheet of porous fibrous felt or fabric is bonded to the outer surface of the perforate sheet. The adhesive layer, at least between the perforate sheet and the porous fibrous material, is sufficiently thick to isolate the two components and form a funnel shaped opening necked down at the entrance to each perforation.

Honeycomb noise attenuation structure

A thrust reverser for the gas stream of a fan jet engine. The engine having a surrounding cowl which forms a fan duct therewith that is divided into a forward fixed and an aft translatable section. The thrust reverser mechanism comprises the plurality of blocker doors rotatable in and out of the fan duct. The rotation mechanism of each of the blocker doors comprises a pinion gear rotatable about a central axle which engages the teeth of a pair of opposing gear racks, one gear rack is attached to the forward cowl section and the other is attached to and carried by the aft cowl section and at least one link member pivotably connected at one end to the axle and at the other end to one of the blocker doors. The translation of the aft cowl section causes said blocker doors to rotate in and out of the fan duct and expose and cover gas reversing cascades.

Thrust reverser geared linkage

A thrust reverser for a fan jet engine. The engine has a primary nozzle for the rearward passage of primary gases and a fan associated therewith. An aerodynamically streamlined cowl surrounds the fan and is spaced from the primary nozzle. Space therebetween forming a fan nozzle for the passage of fan gases. The cowl has a fixed forward section and a translatable aft portion. Stowed the aft section abuts the forward section and forms a continuous inner and outer flow surface and when translated rearward to a deployed position an opening is formed between the sections. A pair of blocker doors are each rotatably connected to the forward cowl section through a pair of longitudinally translatable pivots. The pivots are normally biased in a forward position by a biasing spring. Links are pivotably attached between the blocker doors and the aft cowl section. When the after section is translated aft the links allow the pivots to travel rearward under the influence of the spring and then rotate the blocker doors into the gas streams for redirecting the flow of the gas streams through the opening. When the aft cowl section returns to its forward stowed position the pivots translate forward against the spring bias by the link action until they reach the forwardmost position then the blocker doors are rotated out of the gas streams. Actuators are provided for translating the aft cowl section.

Thrust reverser - cascade type

Method of manufacturing broad band noise attenuation sandwich panels utilizing a cellular core positioned between and bonded to two facing sheets by an adhesive bonding system. One facing sheet is perforated and the other imperforate. A thin sheet of porous fibrous felt or fabric is bonded to the outer surface of the perforate sheet. The adhesive layer, at least between the perforate sheet and the porous fibrous material, is sufficiently thick to isolate the two components and form a funnel shaped opening necked down at the entrance to each perforation. In one embodiment a thin layer of non-metallic cloth is positioned between the perforated and porous fibrous material in those areas where cutting, trimming or drilling of the completed structure is required to maintain isolation.

Method of manufacture of honeycomb noise attenuation structure and the

A three link system in combination with the linear translation of a rear cowl section for non-linear rotation of each of a plurality of blocker doors for providing constant engine pressure characteristics during all positions of blocker door rotation between stowed and fully deployed. A first link is pivotally attached at one end to the engine and pivotally attached at its other end to a second link member which in turn is pivotally attached at its other end to the blocker door. A third link member is pivotally attached to the engine rearward of the first link connection and pivotally connected at its other end to the second link intermediate the end of the first link and blocker door. Actuators are provided for linear translation of the rear cowl section.

Growing community of inventors

Bonita, CA, United States of America

Dale W Lawson