Hamilton Sundstrand Corporation

Sundstrand Corporation

Pratt-whitney Canada Corp

Richard C Welch

Charles E Lents

Michael K Sahm

Jules Ricardo Munoz

Luca Bertuccioli

Jay Fletcher

Jose Albero

Arthur Curtis Becker

Steve Squier

Wayne A Flygare

Steven E Squier

Jerzy Makuszewski

Gerard Howard Bueche

William T DeGroff

Thomas A Bolgert

Arthur Chris Becker

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.

Turbofan emergency generator

The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Integrated system for providing aircraft environmental control

The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

Integrated air turbine driven system for providing aircraft environmental control

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. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.

Aircraft architecture with a reduced bleed aircraft secondary power system

The present invention relates to a vapor compression cycle environmental control system for use on aircraft. The system includes an environmental control subsystem which supplies pressurized ram air at a desired temperature to the aircraft's flight deck and/or cabin. The environmental control subsystem uses a vapor compression cycle subsystem to provide the ram air at the desired temperature. The system further includes an air turbine driven by engine bleed air to provide power to an aircraft mounted accessory drive and to provide heated air to an anti-ice system. The aircraft mounted accessory drive provides power to an air compressor which forms part of the environmental control subsystem and to a working fluid compressor which forms part of the vapor compression cycle subsystem.

Vapor compression cycle environmental control system

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 supplying electrical power to a field winding of the exciter, with an outside periphery having a second radius farthest from an axis of rotation of the second shaft and wherein a sum of the first and second radii is greater than a distance between axes of rotation of the shafts.

Integrated drive generator having magnet generator on second shaft

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. The device may be an integrated drive generator in an aircraft which is designed to operate successfully in any aircraft attitude.

Fill valve for liquid containing device

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.

Growing community of inventors

Rockford, IL, United States of America

Richard C Welch