Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Donald G Chouinard

Daniel Kent Vetters

Eric Sean Donovan

Michael Karam

Michael Stephen Krautheim

An engine assembly for use with a gas turbine engine includes a first component, a second component, and a retention locking plug. The first component is formed to define a passage that extends into the first component. The second component is received in the passage defined in the first component. The retention locking plug extends into the first component and the second component to couple the second component with the first component.

Expanding retention locking plug

One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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Westfield, IN, United States of America

Donald G Chouinard