United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Thomas G Cloft

Robert L Gukeisen

Claude Mercier

Richard H Wiley

Darin S Lussier

Ashok K Jain

Ron I Prihar

Sarah M Wall

Sara M Wall

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

A gas turbine engine includes a gearbox. The gearbox includes a housing at a forward part of a core compartment of a gas turbine engine. A plurality of accessory drives are each configured to rotatably couple the gas turbine engine accessory gearbox to one of a plurality of accessory components.

Geared gas turbine engine accessory gearbox

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

A nacelle assembly for a gas turbine engine includes an integrated afterbody mount case. The integrated afterbody mount case includes an outer ring and a plurality of spokes that extend radially inwardly from the outer ring. The outer ring includes a radially outer surface and a radially inner surface. The plurality of spokes are circumferentially disposed about the radially inner surface and extend radially inwardly from the radially inner surface.

Nacelle assembly having integrated afterbody mount case

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

An access door is provided in a housing for a gas turbine engine, with the access door being movable to an access position independent of any required movement of any cowl door or a fan duct door.

Access door for gas turbine engine components

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.

An accessory system for use in a gas turbine engine, which system includes a gearbox adapted to be arranged radially outward of a main axis of the gas turbine engine and inside a nacelle, one or more engine accessories respectively connected to and driven by the gearbox, and a gas turbine engine oil system driven by a source other than the gearbox.

Reduced gearbox size by separate electrically powered engine oil system

A mounting arrangement for a gas turbine engine includes a pylon mount structure that has a fore mount portion and an aft mount portion. A first engine mount beam is integrally formed with the fore mount portion as a single-piece component, and a second engine mount beam is integrally formed with the aft mount portion as a single-piece component. The first engine mount beam is attachable to the engine case at a fore attachment interface, and the second engine mount beam is attached to the engine case at an aft attachment interface.

Pylon and engine mount configuration

A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section.

Translatable cascade thrust reverser

A gas turbine engine assembly includes an inlet lip assembly, a fan containment case, and a front flange. The fan containment case surrounds a fan section and is positioned downstream from the inlet lip assembly. The front flange is mounted between the inlet lip assembly and the fan containment case and is positioned upstream from the fan section.

Gas turbine engine assembly including accessory components within the nacelle

A gas turbine engine is provided with a nacelle having a hollow inner space. The inner space is utilized as a plenum for directing air from an inlet to an outlet at the upstream end of the nacelle to allow control of an effective lip width of the nacelle under certain flight conditions.

Nacelle compartment plenum for bleed air flow delivery system

An inlet flow control system disposed within a nacelle includes a panel on an inner surface of that nacelle. The panel includes a noise attenuation layer that dissipates noise energy. A vacuum source generates a pressure differential across the noise attenuation layer for drawing airflow through the panel and away from an inner surface of the nacelle.

Integral suction device with acoustic panel

An electrical generator assembly for use in a gas turbine engine, which assembly includes an electrical motor configured to connect to an accessory gearbox arranged radially outward of a main axis of the gas turbine engine and inside a nacelle, and fluid connections between the electrical motor and a generator oil system. The generator oil system is offset from the electrical motor such that the generator oil system is not located radially outward of the electrical motor and inside the nacelle.

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Glastonbury, CT, United States of America

Thomas G Cloft