General Electric Company

Malcolm Kenneth MacLean

David Perveiler

Ross Michael Leon

Ross Michael Lcon

Mark E Daniels

A method of assembling a gas turbine engine is provided. The method includes providing at least one heat exchanger assembly including a heat exchanger and a mixer extending downstream from the heat exchanger. The mixer includes a plurality of windows formed therein. The method also includes coupling the at least one heat exchanger assembly within a bypass duct of the engine such that the at least one heat exchanger assembly is coupled to at least one of an outer engine casing and an inner engine casing of the turbine engine.

Methods and apparatus for mixing fluid in turbine engines

A method of assembling a gas turbine engine includes providing at least one heat exchanger assembly including a heat exchanger and a lobed mixer extending downstream from the heat exchanger, wherein the mixer includes a plurality of lobes that each define a first chute and at least one second chute that extends between each pair of adjacent spaced-apart lobes, and coupling the at least one heat exchanger assembly within a bypass duct of the engine such that the at least one heat exchanger assembly is coupled to at least one of an outer engine casing and an inner engine casing of the turbine engine.

A vectorable gas turbine engine exhaust nozzle including deployable angled flow deflectors for providing thrust vectoring in the yaw direction. In one embodiment the deflectors are pivotally deployed in the diverging section of a two dimensional nozzle with the use of either electromechanical or pneumatic rotary actuators. The deflectors are preferably employed in a two dimensional convergent divergent exhaust nozzle which includes a means for varying the size of the throat and a means for providing pitch thrust vectoring.

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Mason, OH, United States of America

Malcolm Kenneth MacLean