United Technologies Corporation

Roger D Breunig

Stephen M Antonellis

Wallace N Kelly

A rotor assembly 20 for a gas turbine engine 10 is disclosed. The rotor assembly includes a pair of axially spaced apart rotor disks such as the rotor disks 32 and 34. An inner air seal 50 extends axially between the adjacent rotor disks. A member 56 extends axially between the disks to join the disks together and is attached to the inner air seal at a mid span location to restrain the seal against outward movement.

Rotor assembly for a gas turbine engine

A rotor disk adapted to receive a plurality of coolable rotor blades of a gas turbine engine is disclosed. Various construction details for cooling air holes in rotor disks are developed. In structures embodying the present invention tangential stress concentration factors are reduced. The elongated axis of each cooling air hole lies in a plane perpendicular to the axis of symmetry of the disk.

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Meriden, CT, United States of America

Roger D Breunig