United Technologies Corporation

Raytheon Technologies Corporation

Allison Zywiak

Graham Ryan Philbrick

The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a rotary seal element, the rotary seal element configured to rotate during operation of a gas turbine engine, and a stationary seal element having an annular seal surface. The stationary seal element includes a first area of the annular seal surface configured to engage with the rotary seal element, and the stationary seal element includes a second area of the annular seal surface configured to provide reduced resistance to the rotary seal element during a flight windmilling event.

Seal configuration to prevent rotor lock

A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.

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Durham, CT, United States of America

Allison Zywiak