[특허]Power generation unit of integrated gearbox design for aircraft engine

Power generation unit of integrated gearbox design for aircraft engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02B-063/04 H02K-007/10 H02K-007/18 F02C-007/32 H02K-007/116 F02C-007/268 F02N-011/04 H02K-007/108 F01D-015/10 F01D-015/12
출원번호	US-0550083 (2014-11-21)
등록번호	US-9548639 (2017-01-17)
우선권정보	JP-2012-122579 (2012-05-30)
발명자 / 주소	Goi, Tatsuhiko Tanaka, Kenichiro
출원인 / 주소	KAWASAKI JUKOGYO KABUSHIKI KAISHA
대리인 / 주소	Sughrue Mion, PLLC
인용정보	피인용 횟수 : 0 인용 특허 : 32

초록 ▼

A power generation unit is connected with an engine rotary shaft via an accessory gearbox. A rotor extends through the accessory gearbox and a drive gear is disposed at an intermediate portion of the rotor for driving the latter. Permanent magnet elements are mounted on opposite side portions with the intermediate portion intervening therebetween, and stator coils are disposed so as to confront respective outer peripheries of the permanent magnet elements.

대표청구항 ▼

1. A power generation unit for an aircraft engine, which unit is connected with an engine rotary shaft of the aircraft engine via an accessory gearbox, the power generation unit comprising: a rotor extending through the accessory gearbox and having an intermediate portion positioned longitudinally intermediate of the rotor, and opposite side portions with the intermediate portion intervening therebetween;a drive gear mounted on the intermediate portion of the rotor to drive the rotor;permanent magnet elements respectively mounted on outer peripheries of the opposite side portions of the rotor; andstator coils disposed separately from each other so as to respectively confront outer peripheries of the permanent magnet elements and the outer periphery of the rotor on which the permanent magnet elements are mounted, the stator coils being electrically connected with each other. 2. The power generation unit for the aircraft engine as claimed in claim 1, wherein the rotor is disposed parallel to the engine rotary shaft. 3. The power generation unit for the aircraft engine as claimed in claim 1, wherein the stator coils are electrically connected in series with each other. 4. The power generation unit for the aircraft engine as claimed in claim 1, further comprising a mechanical clutch configured to selectively couple and decouple between the drive gear and an input shaft of the accessory gearbox, the input shaft of the accessory gearbox being connected with the engine rotary shaft through an output shaft. 5. The power generation unit for the aircraft engine as claimed in claim 1, further comprising a squeeze film damper configured to support a bearing of the rotor with respect to a power generator housing. 6. The power generation unit for the aircraft engine as claimed in claim 1, wherein the rotor is in the form of a single rod-like member. 7. The power generation unit for the aircraft engine as claimed in claim 1, wherein the rotor is configured to be divided into the intermediate portion and the opposite side portions. 8. The power generation unit for the aircraft engine as claimed in claim 1, wherein the power generation unit is connected with a high pressure shaft that forms a part of the engine rotary shaft, and is configured to operate as an engine starter. 9. An accessory gearbox for an aircraft engine, comprising: an input shaft connected through an output shaft with an engine rotary shaft of the aircraft engine;the power generation unit as defined in claim 1; anda mechanical clutch configured to selectively couple and decouple between the input shaft and the drive gear.

이 특허에 인용된 특허 (32)

Beier, Juergen; Venter, Gideon, Accessory gearbox device for a jet engine.
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Ciokajlo John J. (Cincinnati OH) O\Brien Michael T. (Cincinnati OH), Air-start assembly and method.
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Goi, Tatsuhiko; Tanaka, Kenichiro; Watanabe, Koji, Aircraft starter generator.
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Giordano Serge,FRX, Alternating current-starting device for a helicopter turbine engine unit.
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Kometani, Haruyuki; Asao, Yoshihito, Automotive alternating-current dynamoelectric machine.
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Gabrys, Christopher W.; Rodgers, Timothy S., Commercial low cost, high efficiency motor-generator.
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Dusserre-Telmon, Guy Frank Paul; Galivel, Jean Pierre; Zsiga, Zoltan, Device for driving the rotor of turbine engine auxiliary.
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Becquerelle, Samuel Raymond Germain; Galivel, Jean Pierre, Distributed architecture for a gas-turbine starter/generator.
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Jeffrey Ronald Coles GB; Marc Holme GB; James Patrick Doyle GB, Electrical generator an aero-engine including such a generator, and an aircraft including such a generator.
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Trainer, David R; Feehally, Thomas C J; Moore, Gareth E, Electromechanical arrangement.
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Derouineau,Jean Luc, Engine power extraction control system.
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Moniz, Thomas Ory; Cooker, Paul; Orlando, Robert Joseph, Gas turbine engine assembly and method of assembling same.
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Hoebel, Rudi; Rossberger, Antonius Georg, Gear, motor-gear unit, vehicle and generator with a gear and force transmitting element.
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Stout, David E.; Birdi, Balwinder S.; Down, Edward M.; Meacham, Walter L., High speed aerospace generator resilient mount, combined centering spring and squeeze film damper.
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Berenger, Serge; Kremer, Paul Jean-baptiste; Becquerelle, Samuel Raymond Germain; Vassaux, Alain; Vercherin, Denis Jean Noel, Integration of a starter/generator module in a gas turbine transmission housing.
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Short, Keith E.; Cass, Michael F.; Legros, Craig R., Layshaft generator.
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Berryann, Andrew P.; Suciu, Gabriel L., Mechanism for turbine engine start from low spool.
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Kuznetsov Stephen B., Method and apparatus for detection, classification and reduction of internal electrical faults in alternating current propulsion machinery using synchronous detection scheme.
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Seffernick George H. ; Shah Mahesh J., Method of and system for controlling a variable speed induction motor.
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O'Connor,Richard John, Modulated current gas turbine engine starting system.
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Eick, Chris D.; Gaines, Louie T.; Laidlaw, Mitchell J.; Benson, Dwayne M.; Portolese, Larry A.; Flaherty, Brian L.; Pearson, Wayne T., More electric aircraft power transfer systems and methods.
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Gaines,Louie T.; Auer,Peter J.; Lane,Glenn H.; Wissinger,James A., More electric aircraft starter-generator multi-speed transmission system.
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Hield Paul M. (Bristol GB2) Cundy John M. (Derby GB2) Midgley Ronald A. (Derby GB2) Newton Arnold C. (Derby GB2) Rowe Arthur L. (Derby GB2), Shaft power transfer in gas turbine engines with machines operable as generators or motors.
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Sheridan, William G., Split accessory drive system.
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Chaudhry, Zaffir A., Split gearbox and nacelle arrangement.
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Fingleton, Daniel; Bruno, Rachel, Starter/generator combination with all variable frequency drives.
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Burns, Donald W., System, propulsion system and vehicle.
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Cronin Michael J. (Sherman Oaks CA), Tandem-generator design for aircraft.
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Zeiner, Peter Kenneth; Libera, Tony; Langston, Todd, Turbine drive system with lock-up clutch and method.
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Kumm Emerson L. (Tempe AZ), Turbine engine with differential gearing between high pressure turbine and compressor.
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Welch, Richard C.; Bueche, Gerard H.; DeGroff, William T.; Albero, Jose; Makuszewski, Jerzy, Turbofan emergency generator.
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Petrowicz John P., Windmill engine starting system with fluid driven motor and pump.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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Power generation unit of integrated gearbox design for aircraft engine 원문보기

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Power generation unit of integrated gearbox design for aircraft engine 원문보기

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