[특허]Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system

Hamilton Sundstrand Corporation

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Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02N-01104 F02N-01108 F02N-00708 F02N-01700
미국특허분류(USC)	290/031; 290/027; 290/036.R; 290/038.R; 290/046
출원번호	US-0154942 (2002-05-24)
발명자 / 주소	Kandil, Magdy A. Vanek, Laurence D. Abbot, James L.
출원인 / 주소	Hamilton Sundstrand Corporation
대리인 / 주소	Carlson, Gaskey &
인용정보	피인용 횟수 : 34 인용 특허 : 100

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A starter-generator for an aircraft engine comprises a dynamoelectric machine alternatively operable as a motor or as a generator, having a rotor. A support motor is coupled to the dynamoelectric machine to assist the machine. A torque converter selectively couples and decouples the rotor to the engine, coupling the rotor to the engine at some point when dynamoelectric machine is operated as a motor. A constant speed transmission has an input adapted to be connected to the engine and an output to be connected to the rotor. The unit provides a desired speed relation between input and output. The engine may be started by the dynamoelectric machine when operated as a motor through a first power train including the torque converter and may drive the dynamoelectric machine as a generator through a second power train including the constant speed transmission.

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1. A starter-generator for an aircraft engine comprising;a dynamoelectric machine alternatively operable as a motor or as a generator, said dynamoelectric machine having a rotor; a torque converter for selectively coupling and decoupling said rotor to an engine, said torque converter coupling said rotor to the engine when said dynamoelectric machine is operated as a motor; a support motor coupled to said dynamoelectric machine for assisting in driving said dynamoelectric machine; a constant speed transmission having an input adapted to be connected to the engine and an output adapted to be connected to said rotor; and wherein the engine (a) may be started by said dynamoelectric machine when operated as a motor through a first power train including said torque converter and (b) may drive the dynamoelectric machine as a generator through a second power train including said constant speed transmission. 2. The starter-generator of claim 1 wherein said torque converter decouples said rotor from said engine until said dynamoelectric machine reaches a predetermined speed and couples said rotor to said engine after reaching said predetermined speed.3. The starter-generator of claim 2 wherein said support motor assists said dynamoelectric machine in reaching said predetermined speed.4. The starter-generator of claim 1 wherein said support motor comprises an permanent magnet motor.5. The starter-generator of claim 4 wherein said permanent magnet motor comprises a generator.6. The starter-generator of claim 1 including a control unit for controlling said torque converter.7. The starter-generator of claim 1 including a first source of power for powering said support motor and a second source of power for powering said dynamoelectric machine wherein said second source of power powers said dynamoelectric machine when said dynamoelectric machine reaches a predetermined speed.8. An aircraft engine comprising;a dynamoelectric machine alternatively operable as a motor or as a generator, said dynamoelectric machine having a rotor; a torque converter for selectively coupling and decoupling said rotor to an aircraft engine, said torque converter coupling said rotor to said engine when said dynamoelectric machine is operated as a motor; a support motor coupled to said dynamoelectric machine for assisting in driving said dynamoelectric machine when operated as a motor; a constant speed transmission having an input adapted to be connected to said engine and an output adapted to be connected to said rotor; a first coupling interconnecting said engine and said torque converter and operable to decouple said engine from said torque converter for engine speeds greater than the speed of said torque converter; a second coupling interconnecting said rotor and said output of said constant speed transmission and operable to decouple said rotor from said output for speeds of said rotor greater than the speed of said output; wherein said engine (a) may be started by said dynamoelectric machine, with assistance from said support motor, when operated as a motor through a first power train including said torque converter and said first coupling and (b) may drive the dynamoelectric machine as a generator through a second power train including said constant speed transmission and said second coupling, said torque converter for maintaining said rotor decoupled from said engine until said dynamoelectric machine reaches a predetermined speed, said support motor assisting said dynamoelectric machine in reaching said predetermined speed, and said torque converter coupling said rotor to said engine once a predetermined speed is reached. 9. The aircraft engine of claim 8 wherein said support motor comprises a permanent magnet motor.10. The aircraft engine of claim 8 including a first source of power for powering said support motor and a second source of power for powering said dynamoelectric machine wherein said second source of power powers said dynamoelectric machine when said dynamoelectric machine reaches a predetermined speed.11. The aircraft engine of claim 8 including a flow control valve for controlling a flow of hydraulic fluid from a hydraulic source to said torque converter.12. The aircraft engine of claim 8 wherein at least one of said first coupling and said second coupling is an overrunning clutch.13. The starter-generator of claim 1 wherein said torque converter has a hydraulically charged condition and a hydraulically discharged condition, said torque converter coupling said rotor to the engine when in said hydraulically charged condition and decoupling said rotor to the engine when in said hydraulically discharged condition.14. The starter-generator of claim 13 wherein said torque converter is controlled by a control unit said control unit for selectively placing said torque converter in said hydraulically discharged condition and said hydraulically charged condition.15. The start-generator of claim 14 including an engine sensor in communication with said control unit.16. The starter-generator of claim 15 wherein said control unit controls said torque converter based on said engine speed sensor.17. The starter-generator of claim 14 including a dynamoelectric machine sensor in communication with said control unit.18. The starter-generator of claim 17 wherein said control unit controls said torque converter based on said dynamoelectric machine sensor.19. The starter-generator of claim 7 including a control unit for controlling said first source of power and said second source of power.

이 특허에 인용된 특허 (100)

이 특허를 인용한 특허 피인용횟수: 34

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Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system

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이 특허에 인용된 특허 (100)

이 특허를 인용한 특허 피인용횟수: 34

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Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system

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이 특허에 인용된 특허 (100)

이 특허를 인용한 특허 피인용횟수: 34

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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