United Technologies Corporation

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

Douglas L Kisling

Edward C Hill

George A Bonner

Ronald D Delahoussaye

John C Jones

Milo R Rodriguez

A variable guide vane 12 bushing assembly 10 which features means that prevents bushing rotation. A bushing 16 comprises flats 16b on its outer sleeve, the flats interlock with race track shaped holes 20a on a tab-lock washer 20. The tab-lock washer spans two or more adjacent vane stems (12,14) and thus is not susceptible to rotation. A retainer 24 and the vane arm 26 assemble on top of the tab-lock washer to complete the assembly.

Anti-rotation guide vane bushing

A vane lever arm for the variable stator/vane assembly of a gas turbine engine that is fabricated from sheet metal and has a flexible thin section to allow out of plane movement and a rigid thicker end for supporting the pin attached to the synchronous ring.

Vane lever arm construction

A spacer extends between and engages the rear face of a first disk and front face of a second disk of co-rotating rotors of a two stage turbine. The spacer engages the disks radially inwardly of the blade root slots of each disk and defines an intermediate cooling air compartment between the disks, radially inward of the spacer. Each disk includes blade root slots, each having a blade root disposed therein and defining a cooling air passageway across each slot from the front to rear face of each disk. Cooling air from a compartment upstream of the first disk is directed downstream through the passageways across the slots and thence radially inwardly into the intermediate compartment between the disks. From the intermediate compartment the cooling air travels radially outwardly and then axially through the cooling air passageways across the second disk blade root slots. Thus, the same mass of cooling air from upstream of the first disk is used to cool the rims of both disks and the blade roots disposed in the slots of both disks without the air having to pass through axial holes through the first disk, thereby eliminating the need for such holes and increasing the strength of the disk. In a preferred embodiment a portion of the cooling air passing through the slots of each disk is directed radially outwardly into hollow airfoils which are integral with the blade roots.

Two stage rotor assembly with improved coolant flow

A device for securing an annular blade retaining plate to a rotor disk includes an annular groove around the disk for receiving an off-set annular flange on the inner end of said blade retaining plate. A split retainer ring extends from a second groove intersecting said first groove to fix the blade retainer ring to the disk. A locking ring is positioned between said split retainer ring and said blade retaining plate to maintain said split retainer ring in its groove.

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Palm Beach Gardens, FL, United States of America

Douglas L Kisling