Abstract: A turbine engine emergency power system includes low and high pressure spools, the lower pressure spool including a low pressure compressor. A turbofan is coupled to the low pressure spool. The turbofan drives the low pressure spool in a windmill condition in which the low pressure turbine fails to provide rotational drive to the turbofan. A generator is rotationally driven by the low pressure spool in the windmill condition. A gear train is used to increase the speed of the generator in one example. In one example embodiment, a centrifugal clutch is used to selectively decouple the generator from the low pressure spool at a predetermined engine speed, which corresponds to normal operating speeds when the turbine engine is under power.

Abstract: A turbine engine emergency power system includes low and high pressure spools, the lower pressure spool including a low pressure compressor. A turbofan is coupled to the low pressure spool. The turbofan drives the low pressure spool in a windmill condition in which the low pressure turbine fails to provide rotational drive to the turbofan. A generator is rotationally driven by the low pressure spool in the windmill condition. A gear train is used to increase the speed of the generator in one example. In one example embodiment, a centrifugal clutch is used to selectively decouple the generator from the low pressure spool at a predetermined engine speed, which corresponds to normal operating speeds when the turbine engine is under power.

Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system.

Abstract: The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system.

Abstract: An integrated drive generator (40) for generating constant frequency alternating current which is driven by a drive shaft (12) at variable rotational speeds includes a constant speed drive having an input coupled to the drive shaft and at least one output which rotates at a fixed rotational velocity in response to the drive shaft rotating at a variable velocity and which drives a first drive shaft at a fixed rotational velocity and a second drive shaft at a fixed rotational velocity, an alternating current generator (23), having a rotor (37) mounted on a first shaft (42), with an outside periphery having a second radius farthest from an axis of rotation of the first shaft; an exciter (20) having a rotor (32) mounted on the first shaft, electrically coupled to a field winding of the generator, for supplying electrical power to the field winding of the alternating current generator; a permanent magnet generator (18), having a rotor (24) mounted on the second shaft, electrically coupled to the exciter, for suppl

Abstract: A device (1) for use in conjunction with an engine (25) is adapted to contain a predetermined level (A) of a liquid such as oil therein. A fill passage (4) is provided for adding liquid to the device and a drain passage (7) is provided for draining liquid from the device when the liquid is above the predetermined level. A movable valve (12) is provided for opening and closing the fill passage and the drain passage. The valve is automatically positioned so as to close both passages in response to start up of the engine whereby liquid will not be lost through the passage during operation of the engine. When the engine is not operating, the fill passage and drain passage are automatically opened in response to the application of pressure filling pressure to the fill passage as a result of an axial vent hole (31) which communicates the filling pressure to an end (32) the movable valve.

Abstract: A device (1) for use in conjunction with an engine (25) is adapted to contain a predetermined level (A) of a liquid such as oil therein. A fill passage (4) is provided for adding liquid to the device and a drain passage (7) is provided for draining liquid from the device when the liquid is above the predetermined level. A movable valve (12) is provided for opening and closing the fill passage and the drain passage. The valve is automatically positioned so as to close both passages in response to start up of the engine whereby liquid will not be lost through the passage during operation of the engine. The device may be an integrated drive generator in an aircraft which is designed to operate successfully in any aircraft attitude.