Honeywell International Inc.

Timothy Ray O'Brien

Harold Riley

Victor Reyes

Scott J Marshall

Paul Topper

Huy Tran

Brian Petterson

Andrew F Szuromi

A system and method provide aircraft-specific customization of gas turbine engine operation. The system includes a gas turbine engine, a first processing unit, and an engine controller. The first processing unit is configured to selectively transmit an activation key. The engine controller is in operable communication with the first processing unit and the gas turbine engine. The engine controller is configured to receive the activation key transmitted by the first processing unit and is operable, upon receipt of the activation key, to: verify the received activation key is correct, enable operational parameters in the gas turbine engine and the engine controller when the received activation key is correct, and control the gas turbine engine using the enabled operational parameters.

System and method for providing end-use specific customization of gas turbine engine operation

A first-stage turbine that is adapted for receiving high energy air directly from a combustion chamber in a gas turbine engine auxiliary power unit includes a disk formed from a first alloy and having an outer surface, and a unitary blade wheel formed from a second alloy that is different than the first alloy. The unitary blade wheel includes an annular member having an inner surface that is joined to the disk, and blades that are integrally formed with the annular member.

First stage dual-alloy turbine wheel

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Chandler, AZ, United States of America

Timothy Ray O'Brien