Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: Systems and methods involving multiplexed engine control signals are provided. In this regard, a representative engine control system for a gas turbine engine includes: a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of multiple control devices of the engine.

Abstract: A fan section of a gas turbine engine includes nacelle inlet and a fan containment case that are integrally formed together as a single-piece component.

Abstract: A turbofan flow delivery system includes a fan case housing a fan. Flow exit guide vanes are arranged downstream from the fan and extend radially inwardly from the fan case toward a bypass flow path. A supply passage includes an opening provided in the fan case between the fan and flow exit guide vanes configured to selectively provide pressurized air to a component using air from the bypass flow path. Swirling air from the bypass flow path enters the supply passage and is converted to a static pressure.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A nacelle structure for a gas turbine engine includes an inlet aft of an exit guide vane for supplying air flow to a forward plenum. Air is exhausted from the plenum into an air intake opening and over an inner surface of the nacelle for controlling air flow characteristics within the nacelle.

Abstract: A fan section of a gas turbine engine includes nacelle inlet and a fan containment case that are integrally formed together as a single-piece component.

Abstract: 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.

Abstract: Systems and methods involving multiplexed engine control signals are provided. In this regard, a representative engine control system for a gas turbine engine includes: a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of multiple control devices of the engine.

Abstract: 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.

Abstract: 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.

Abstract: Systems involving inlet-mounted engine control components are provided. A representative system includes: a forward keep out zone defined by converging inner and outer walls of a nacelle; an aft keep out zone defined by a containment zone; and an engine control component, at least a portion of which is located between the forward keep out zone and the aft keep out zone, and between the inner and outer walls of the nacelle.

Abstract: 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.

Abstract: 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.

Abstract: A turbofan flow delivery system includes a fan case housing a fan. Flow exit guide vanes are arranged downstream from the fan and extend radially inwardly from the fan case toward a bypass flow path. A supply passage includes an opening provided in the fan case between the fan and flow exit guide vanes configured to selectively provide pressurized air to a component using air from the bypass flow path. Swirling air from the bypass flow path enters the supply passage and is converted to a static pressure.