Cascade type aircraft engine thrust reverser with hidden link ac

Details Cascade type aircraft engine thrust reverser with hidden link ac Cascade type aircraft engine thrust reverser with hidden link ac

1991-08-15

1993-07-20

Peters, Jr., Joseph F.

Aeronautics and astronautics

Retarding and restraining devices

Friction brakes

23926531, 602262, B64C 2568

Patent

active

052286410

ABSTRACT:
A thrust reverser for use with fan jet type aircraft gas turbine engines. A ring around the aft edge of the nacelle is translatable aft to uncover a series of cascade sets, each of which includes a plurality of turning vanes that direct air passing through the cascades in a reverse direction. The actuation system includes a hydraulic cylinder or the like in islands between cascade sets. A blocker door assembly is positioned within the nacelle adjacent to each cascade set during normal engine operation, with the blocker door forming a portion of the inner streamlined wall of the nacelle. The forward end of the door is hingedly secured to a cascade door support and does not move during deployment of the ring. The aft end of the door is hingedly secured to a link, the other end of which is secured to the moving ring. As the ring is translated aft, the door pivots to a position blocking at least part of the air flow through the duct between nacelle and engine core and directs it outwardly though the cascade set. The actuation system is entirely outside the air flow stream both during normal flight operations and reverse thrust operations, avoiding any undesirable interference or drag during these operations.

REFERENCES:
patent: 3262268 (1966-07-01), Beavers
patent: 3511055 (1970-05-01), Timms
patent: 4005822 (1977-02-01), Timms
patent: 4073440 (1978-02-01), Hapke
patent: 4731991 (1988-03-01), Newton
patent: 4807434 (1989-02-01), Jurich
patent: 4827248 (1989-05-01), Crudden
patent: 4909442 (1990-03-01), Fernz
patent: 4998409 (1991-03-01), Mutch

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