Rohr, Inc.

Goodrich Actuation Systems Limited

Daniel J Shetzer

Jihad I Ramlaoui

John Herbert Harvey

Andrew Robert Hawksworth

Geoffrey Pinto

Daniel M Amkraut

Roger Moorhouse

Alan K Evans

Vikram Chandarana

Michael Sean Pretty

Martin Channell

Kevin Woolworth

Thomas Holt

An aircraft anti-icing system is disclosed. A tube having a plurality of outlet ports is disposed within an interior of an outer housing in spaced relation to a closed end of this outer housing. The exterior of the outer housing includes a leading edge at its closed end. The tube is anchored relative to the outer housing by one or more brackets that extend from the tube to the outer housing. An open end of the outer housing may be closed by an aft wall that encloses the tube within an interior compartment of the outer housing.

Aircraft anti-icing system

A nacelle for a gas turbine engine includes at least one hinge axis extending along the nacelle. At least one cowl is mounted to the nacelle, along the at least one hinge axis, by a plurality of hinges. The plurality of hinges includes at least one latch. The at least one latch includes a clevis and a tang. The clevis and the tang of the at least one latch are configured to receive a hinge pin, through a pin aperture, when the at least one cowl is in a closed condition.

Nacelle cowl hinge

An assembly is provided for a turbofan engine. This turbofan engine assembly includes a cowling, a door and an actuation mechanism configured to actuate movement of the door in response to receiving a control signal. The cowling is configured to form a compartment at least partially around a case of the turbofan engine. The cowling includes an exhaust port that is fluidly coupled with the compartment. The door is configured to at least partially open and close the exhaust port. This variable exhaust port may be opened in case increased airflow is needed through the compartment, such as when increased cooling airflow is needed through an environmental air precooler that cools compressed air for the aircraft cabin and the precooler exhausts its cooling air into the compartment.

Actively controlled cooling air exhaust door on an aircraft engine nacelle

A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

Actuation system for a translating variable area fan nozzle

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San Diego, CA, United States of America

Daniel J Shetzer