Abstract: A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.

Abstract: A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.

Abstract: 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.

Abstract: A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.

Abstract: A linkage comprises a drive ring, a flap linkage mounted to each of a multiple of flaps and the drive ring, and an actuator system which drives the drive ring to cause the multiple of flaps to pivot. A method of driving a multiple of flaps is also disclosed.

Abstract: A gas turbine engine assembly has a pylon with a first side and a second side. A first rail is mounted to the first side and a second rail is mounted to the second side. The assembly also has a thrust reverser with a first door assembly with a first upper portion and a first lower portion, and a second door assembly with a second upper portion and a second lower portion. A plurality of fasteners is part of the assembly. The first upper portion is connected with at least one of the plurality of fasteners to the first rail, and the second upper portion is connected with at least one of the plurality of fasteners to the second rail such that the thrust reverser is positionable between an engaged position and a disengaged position.

Abstract: 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.

Abstract: A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.

Abstract: 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.

Abstract: A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section.

Abstract: A cascade set for creating sufficient drag to slow an aircraft is disclosed. The cascade set includes one or more supporting vanes. A plurality of turning vanes are connected to the supporting vanes, and the turning vanes include forward and aft turning vanes. The forward turning vanes have a larger surface area than the aft turning vanes.

Abstract: A gas turbine engine assembly has a pylon with a first side and a second side. A first rail is mounted to the first side and a second rail is mounted to the second side. The assembly also has a thrust reverser with a first door assembly with a first upper portion and a first lower portion, and a second door assembly with a second upper portion and a second lower portion. A plurality of fasteners is part of the assembly. The first upper portion is connected with at least one of the plurality of fasteners to the first rail, and the second upper portion is connected with at least one of the plurality of fasteners to the second rail such that the thrust reverser is positionable between an engaged position and a disengaged position.

Abstract: 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 extending through said inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle. A gas turbine engine is also disclosed.

Abstract: 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.

Abstract: 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.

Abstract: A linkage comprises a drive ring, a flap linkage mounted to each of a multiple of flaps and the drive ring, and an actuator system which drives the drive ring to cause the multiple of flaps to pivot. A method of driving a multiple of flaps is also disclosed.

Abstract: A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area.

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: A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.

Abstract: 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.