More electric aircraft power transfer systems and methods
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/10
F02C-003/00
출원번호
UP-0290745
(2005-11-29)
등록번호
US-7552582
(2009-07-09)
발명자
/ 주소
Eick, Chris D.
Gaines, Louie T.
Laidlaw, Mitchell J.
Benson, Dwayne M.
Portolese, Larry A.
Flaherty, Brian L.
Pearson, Wayne T.
출원인 / 주소
Honeywell International Inc.
대리인 / 주소
Ingrassia Fisher & Lorenz, P.C.
인용정보
피인용 횟수 :
21인용 특허 :
27
초록▼
A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer
A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting/loading sharing systems that use clutches and gear assemblies to share and/or shift load between the turbines.
대표청구항▼
We claim: 1. A multi-spool gas turbine engine, comprising: a differential gear assembly having a first input and a second input, the gear assembly configured, upon rotation of the first input, the second input, or both inputs, to supply a rotational drive force at a first rotational speed; a genera
We claim: 1. A multi-spool gas turbine engine, comprising: a differential gear assembly having a first input and a second input, the gear assembly configured, upon rotation of the first input, the second input, or both inputs, to supply a rotational drive force at a first rotational speed; a generator coupled to receive the rotational drive force supplied from the differential gear assembly and operable, upon receipt thereof, to generate electrical energy; a high pressure turbine coupled to the differential gear assembly first input and adapted to receive a flow of combusted gas, the high pressure turbine operable, upon receipt of the combusted gas, to rotate at a second rotational speed; a low pressure turbine adapted to receive a flow of combusted gas, the low pressure turbine operable, upon receipt of the combusted gas, to rotate at a third rotational speed; a clutch assembly coupled between the low pressure turbine and the differential gear assembly second input, the clutch assembly movable between an engaged position, in which the low pressure turbine is coupled to the differential gear assembly second input, and a disengaged position, in which the low pressure turbine is decoupled from the differential gear assembly second input; and a low pressure input gear assembly coupled to the clutch assembly, the differential gear assembly second input, and the low pressure turbine, the low pressure input gear assembly configured, when the clutch assembly is in the engaged position, to (i) couple the low pressure turbine to the differential gear assembly second input and (ii) increase the third rotational speed to a fourth rotational speed. 2. The engine of claim 1, further comprising: a sprag clutch coupled between the low pressure input gear assembly and the differential gear assembly, the sprag clutch movable between an engaged position, in which the low pressure input gear assembly is coupled to the differential gear assembly second input, and a disengaged position, in which the low pressure input gear assembly is decoupled from the differential gear assembly second input. 3. The engine of claim 1, wherein: the clutch assembly is responsive to clutch actuation commands to move between the engaged and disengaged positions; and the engine further comprises a control circuit operable to selectively supply the clutch actuation commands to the clutch assembly. 4. The engine of claim 1, wherein the generator is a starter-generator that is configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the differential gear assembly or (ii) a generator mode, in which the rotational drive force supplied thereto from the differential gear assembly is converted to electrical energy. 5. The engine of claim 1, further comprising: a second generator coupled to receive the rotational drive force supplied from the differential gear assembly, the second generator operable, upon receipt of the rotational drive force, to generate electrical energy. 6. The engine of claim 5, wherein the second generator is a starter-generator that is configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the differential gear assembly or (ii) a generator mode, in which the rotational drive force supplied thereto from the differential gear assembly is converted to electrical energy. 7. The engine of claim 1, wherein the differential gear assembly is a speed summing differential gear assembly.
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이 특허에 인용된 특허 (27)
Artinian Vatche ; Brim Terry ; Matulich Dan ; Murry Roger, Aircraft air conditioning system including electric generator for providing AC power having limited frequency range.
Latos Thomas S. ; Nelson Jeffrey D. ; Dickes Gary E., Aircraft electrical system providing emergency power and electric starting of propulsion engines.
Ejzak Richard P. (Rockford IL) Thom James B. (Rock City IL) Peterson William J. (Rockford IL) Glennon Timothy F. (Rockford IL), Control for an electrical generating and distribution system, and method of operation.
Diemer John W. (Rockford IL) Teagardin Michael D. (Rockford IL), Cross-start bus configuration for a variable speed constant frequency electric power system.
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.
Goi, Tatsuhiko; Kawakami, Koji; Tanaka, Kenichiro; Isano, Takayuki; Machida, Hisashi; Ito, Hiroyuki; Miyata, Shinji, Method of and apparatus for driving aircraft generator at a constant-speed.
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.
Linet, Hugues Henri Raymond; Mouchnino, Cyril Franck; Pettinotti, Serge Dominique, Device for the offtake of mechanical power between the HP and LP shafts of a double-shaft turbine engine.
Phillips, Steven D.; Neuman, Tom M.; Armstrong, Michael, Engine health monitoring and power allocation control for a turbine engine using electric generators.
Phillips, Steven Daniel; Armstrong, Michael; Neuman, Tom Mark, Engine health monitoring and power allocation control for a turbine engine using electric generators.
Suciu, Gabriel L.; Penda, Allan R.; Merry, Brian D.; Glahn, Jorn A.; Dye, Christoper M.; Snape, Nathan, Integrated thermal management system and environmental control system for a gas turbine engine.
Kern, John Michael; Drexel, Michael V.; VanDam, Jeremy Daniel, Variable coupling of turbofan engine spools via open differential gear set or simple planetary gear set for improved power extraction and engine operability, with torque coupling for added flexibility.
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