United Technologies Corporation

Rtx Corporation

Brad Powell

Anthony R Bifulco

John P Virtue

Paul E Coderre

Brian E Lucker

Chong H Park

A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

Movable air seal for gas turbine engine

An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.

Fluid injector for cooling a gas turbine engine component

In various embodiments, a high pressure compressor may comprise a thermal shield. The thermal shield may be installed between a first rotor and a second rotor. The thermal shield may also be installed radially inward of a stator. The stator may be a shrouded stator. Moreover, the thermal shield may be configured to thermally isolate and/or reduce the thermal load associated with windage on a rotor hub.

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Guilford, CT, United States of America

Brad Powell