United Technologies Corporation

United States of America As Represented by the Secretary of the Air Force

Roy R Starke

Harvey L Klein

Thomas A Roach

A non-integral rotor blade platform for a rotary machine is disclosed. Various construction details are developed which disclose a one-piece, non-integral rotor blade platform retained to a live rim area of a disk. In one embodiment, a rotor blade assembly (48) is comprised of a plurality of rotor blades (54) disposed on a disk (44), a plurality of platforms (60), each platform disposed between adjacent rotor blades, and a front cover plate (56) and rear cover plate (58) which, in conjunction, retain the platforms to the disk. In an alternative embodiment, each platform (102) has a supplemental mechanical fastener means (100) to provide additional retention of the platforms to a disk (104).

Non-integral rotor blade platform

A convergent/divergent gas turbine engine exhaust nozzle having reverse thrust capability includes a door which blocks a reverse flow outlet port when the nozzle convergent flap is in any forward thrust operating mode. The door is coupled to the convergent nozzle flap such that it opens as the convergent nozzle flap moves to a reverse thrust position and the flap directs the exhaust gases through the reverser outlet. Coupling is accomplished by a cam track connected to the blocker door and a cam track connected to the convergent flap, with a cam follower interconnecting the two cam tracks. As the convergent flap is rotated, the cams and cam follower cause appropriate movement of the blocker door.

Exhaust nozzle with reverser exhaust door mechanism

A seal assembly (28) is provided for sealing between a static sidewall (12), a rotating first member having a flat and annular surface (22) disposed therein, and a concentric rim (34) disposed between the sidewall (12) and first member (22). The rim (34) is supportably secured to an arcuate hood (18) which extends axially from the rim (34).

Annular seal assembly

A cooling air diverter (8) is responsive to exhaust nozzle configuration, directing cooling air (2) to a reverser vane isolation valve (9) during forward thrust operation, and to a conduit (10), which forms part of a reverser vane access passage (17), during reverse thrust operation. The cooling air diverter includes a pivotal arm assembly (18) with inner (22) and outer (23) flaps independently movable about a first common hinge (19), and a floating flap (24) pivotable about a second hinge (25) fastened at the outward end of the inner flap. Flap movement and position is determined by contact with the isolation valve, which moves in response to thrust redirection. By utilizing an existing movable nozzle member to actuate the diverter, directional control of the cooling airflow is achieved without requiring additional actuators or complex mechanical control devices, minimizing complexity and optimizing nozzle weight.

Exhaust gas nozzle including a cooling air diverter

A hinge assembly wherein the hinge pin and the first two of the interleaved hinge fingers are configured such that, once the pin has been installed and the hinge is in an operating position, the hinge pin is positively retained without the need for additional securing hardware.

Separable hinge with self retaining hinge pin

A two-way flow valve includes a valve body having a cavity and a stem longitudinally moveable therein which establishes two separate fluid flow paths through the cavity in the body from first and second inlet ports to a common outlet port. A spring biases the stem to a first position in which fluid flow is allowed along a first one of the paths and obstructed along the other. When a closure is applied to the valve, the stem is moved against the spring bias to a second position in which fluid flow is allowed along a second one of the paths and obstructed along the first path.

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Lake Park, FL, United States of America

Roy R Starke