United Technologies Corporation

Claude Mercier

Thomas G Cloft

Robert L Gukeisen

Robert E Malecki

Gary Collopy

An example gas turbine engine includes, among other things, a nacelle having an inner wall providing a bypass duct of a gas turbine engine, and an outer wall; an accessory gearbox is received between the inner wall and the outer wall of the nacelle; and an accessory drive of the accessory gearbox is configured to rotate about an accessory drive axis that is transverse to a central axis of the gas turbine engine.

Gas turbine engine accessory gearbox

An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position.

Turbomachine thrust reverser

A latch assembly for securing a nacelle portion of a gas turbine engine includes an engine case structure that includes a core compartment. An inner flow structure has closed and opened positions with respect to the engine case structure. The inner flow structure encloses the core compartment in the closed position and provides access to the core compartment in the opened position. A bypass flowpath is provided by a portion of the engine case structure and the inner flow structure. A seal is engaged with the engine case structure and the inner flow structure in the closed position. A latch has a latched position in which radial movement of the inner flow structure relative to the engine case structure is impeded and maintained in the closed position and an unlatched position in which the inner flow structure is permitted to move radially outward to the opened position.

Nacelle inner flow structure leading edge latching system

An assembly for a gas turbine engine includes a first fan cowl pivotable on a hinge from a first position to a second position. A latching actuation mechanism is disposed under the nacelle, engages the hinge, and is actuated by movement of the hinge between the first position and the second position.

Latching actuation mechanism for nacelle mounted latching system

A gas turbine engine has a compressor section received within an inner housing. An is an outer housing is spaced radially outwardly of the inner core housing. A nacelle has an anti-icing system which taps compressed air from the compressor section through an anti-ice valve and to the nacelle. The anti-ice valve is opened at startup of the gas turbine engine to assist compressor stability.

Nacelle anti-ice valve utilized as compressor stability bleed valve during starting

An engine installation system includes two aftward members and two forward members. Each member is connected to a different bootstrap on one end and has a pivotable connection to a pylon on the other end. There is a link that connects one forward member with one aftward member, and another link that connects the other forward member with the other aftward member. There is a variable-length member connected to the bootstrap-end of each of the two aftward members, with each of the variable-length members having a pivotable connection to the pylon.

Engine installation system

A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall. At least one drive shaft extends through the inner wall. The at least one drive shaft is connected to a gas turbine engine receiving the nacelle. The at least one drive shaft is connected to drive at least two accessory gear boxes, with the at least two accessory gear boxes being received between the inner and outer walls of the nacelle. A gas turbine engine is also disclosed.

Gas turbine engine with accessory gear box

A nacelle structure for a gas turbine engine includes an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage and an inner nacelle surrounding a core engine section and defining an inner boundary of the bypass flow passage. A panel of the inner nacelle is moveable between an open position providing access to the core engine section and a closed position. A lock is supported within the inner nacelle proximate the panel. The lock includes an electric actuator for moving a locking pin between a locked position and an unlocked position. The lock prevents opening and limits deflection of the panel when in the locked position.

Nacelle electrical locking system for leading edge of openable panel

A latch assembly for securing a nacelle portion of a gas turbine engine includes first and second nacelle flow structures that define a portion of a bypass flowpath. A seal is engageable between the first and second nacelle flow structures. A latch is rotatable about a pivot between latched and unlatched positions. The latch maintains the seal in engagement with the first and second nacelle flow structures in the latched position. A method of opening a nacelle flow structure includes the steps of pivoting a latch from a latched position to an unlatched position, and unlatching a first nacelle flow structure relative to a second nacelle flow structure in response to the latch pivoting step.

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South Windsor, CT, United States of America

Claude Mercier