More electric aircraft starter-generator multi-speed transmission system
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/10
F02C-003/00
출원번호
US-0323692
(2005-12-30)
등록번호
US-7481062
(2009-01-27)
발명자
/ 주소
Gaines,Louie T.
Auer,Peter J.
Lane,Glenn H.
Wissinger,James A.
출원인 / 주소
Honeywell International Inc.
대리인 / 주소
Ingrassia Fisher & Lorenz, P.C.
인용정보
피인용 횟수 :
29인용 특허 :
34
초록▼
A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its asso
A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.
대표청구항▼
We claim: 1. A multi-spool gas turbine engine, comprising: a gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy; a high pressure starter-g
We claim: 1. A multi-spool gas turbine engine, comprising: a gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy; a high pressure starter-generator coupled to the high pressure turbine and configured to selectively operate in either (i) a generator mode, in which at least a portion of the rotational energy generated by the high pressure turbine is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy and supplied to the high pressure turbine; a first clutch assembly movable between an engaged position and a disengaged position; a multi-speed gear assembly coupled to the low pressure turbine and to the first clutch assembly, the multi-speed gear assembly operable, upon receipt of the rotational energy and in dependence on the position of the first clutch assembly, to supply a rotational drive force at a rotational speed that varies over one of a plurality of rotational speed ranges; a low pressure starter-generator coupled to the multi-speed gear assembly and configured to selectively operate in either (i) a generator mode, in which the rotational drive force supplied from the multi-speed gear assembly is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy; and a second clutch assembly movable between (i) an engaged position, in which the low pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the low pressure starter-generator is decoupled from the high pressure turbine. 2. The engine of claim 1, further comprising: an interconnection gear assembly including at least in input gear coupled to the low pressure starter-generator and an output gear coupled to the high pressure turbine, the output gear coupled to the high pressure turbine when the second clutch assembly is in the engaged position. 3. The engine of claim 2, wherein the interconnection gear assembly further comprises an idler gear disposed between the input gear and the output gear. 4. The engine of claim 1, further comprising: a speed changer coupled between the multi-speed gear assembly and the low pressure starter-generator, the speed changer configured to change the rotational speed of the drive force supplied from the multi-speed gear assembly. 5. The engine of claim 1, wherein: the first and second clutch assemblies are each 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 first and second clutch actuation commands to the first and second clutch assemblies, respectively. 6. The engine of claim 5, wherein: the first clutch assembly includes a first clutch actuator coupled to the first clutch assembly, the first clutch actuator coupled to receive the clutch actuation commands from the control circuit and operable, upon receipt thereof, to selectively move the first clutch between the engaged and disengaged position; and the second clutch assembly includes a second clutch actuator coupled to the second clutch assembly, the second clutch actuator coupled to receive the clutch actuation commands from the control circuit and operable, upon receipt thereof, to selectively move the second clutch between the engaged and disengaged position. 7. The engine of claim 1, further comprising: a decoupler coupled between the high pressure starter-generator and the high pressure turbine and movable between (i) an engaged position, in which the high pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the high pressure starter generator is decoupled from the high pressure turbine. 8. The engine of claim 7, wherein: the first and second clutch assemblies are each responsive to clutch actuation commands to move between the engaged and disengaged positions; the decoupler is responsive to decoupler actuation commands to move from the engaged position to the disengaged positions; and the engine further comprises a control circuit operable to selectively supply the clutch actuation commands to each of the clutch assemblies, and the decoupler actuation commands to the decoupler. 9. The engine of claim 8, wherein: the first clutch assembly includes a first clutch actuator coupled to receive the clutch actuation commands from the control circuit and operable, upon receipt thereof, to selectively move the first clutch between the engaged and disengaged position; the second clutch assembly includes a second clutch actuator coupled to receive the clutch actuation commands from the control circuit and operable, upon receipt thereof, to selectively move the second clutch between the engaged and disengaged position; and the decoupler includes a decoupler actuator coupled to receive the decoupler actuation commands from the control circuit and operable, upon receipt thereof, to selectively move the decoupler from the engaged to the disengaged position. 10. The engine of claim 1, further comprising: an overrunning sprag clutch assembly coupled between the low pressure starter-generator and the multi-speed gear assembly, the overrunning sprag clutch configured to (i) couple the low pressure starter-generator to the multi-speed gear assembly when the low pressure starter-generator is operating in the generate mode and (ii) decouple the low pressure starter-generator from the multi-speed gear assembly when the low pressure starter-generator is operating in the motor mode. 11. The engine of claim 1, wherein the multi-speed gear assembly comprises a planetary gear assembly including, a sun gear, a ring gear, and a carrier. 12. The engine of claim 11, wherein: the sun gear is locked to the carrier and rotates therewith when the first clutch assembly is in the engaged position; and the sun gear is not locked to the carrier and is prevented from rotating when the first clutch assembly is in the disengaged position. 13. The engine of claim 12, further comprising: a sprag clutch coupled between the multi-speed gear assembly and the low pressure starter-generator, the sprag clutch configured to prevent the sun gear from rotating when the first clutch assembly is in the disengaged position. 14. The engine of claim 1, wherein the plurality of rotational speed ranges is two rotational speed ranges. 15. A multi-spool gas turbine engine, comprising: a gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy; a high pressure starter-generator coupled to the high pressure turbine and configured to selectively operate in either (i) a generator mode, in which at least a portion of the rotational energy generated by the high pressure turbine is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy and supplied to the high pressure turbine; a first clutch assembly movable between an engaged position and a disengaged position; a multi-speed gear assembly coupled to the low pressure turbine and to the first clutch assembly, the multi-speed gear assembly operable, upon receipt of the rotational energy and in dependence on the position of the first clutch assembly, to supply a rotational drive force at a rotational speed that varies over one of a plurality of rotational speed ranges; a low pressure starter-generator coupled to the multi-speed gear assembly and configured to selectively operate in either (i) a generator mode, in which the rotational drive force supplied from the multi-speed gear assembly is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy; a second clutch assembly movable between (i) an engaged position, in which the low pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the low pressure starter-generator is decoupled from the high pressure turbine; and an interconnection gear assembly including at least in input gear coupled to the low pressure starter-generator and an output gear coupled to the high pressure turbine, the output gear coupled to the high pressure turbine when the second clutch assembly is in the engaged position. 16. The engine of claim 15, further comprising: a speed changer coupled between the multi-speed gear assembly and the low pressure starter-generator, the speed changer configured to change the rotational speed of the drive force supplied from the multi-speed gear assembly. 17. The engine of claim 15, further comprising: an overrunning sprag clutch assembly coupled between the low pressure starter-generator and the multi-speed gear assembly, the overrunning sprag clutch configured to (i) couple the low pressure starter-generator to the multi-speed gear assembly when the low pressure starter-generator is operating in the generate mode and (ii) decouple the low pressure starter-generator from the multi-speed gear assembly when the low pressure starter-generator is operating in the motor mode. 18. The engine of claim 15, further comprising: a decoupler coupled between the high pressure starter-generator and the high pressure turbine and movable between (i) an engaged position, in which the high pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the high pressure starter generator is decoupled from the high pressure turbine. 19. The engine of claim 18, wherein: the first and second clutch assemblies are each responsive to clutch actuation commands to move between the engaged and disengaged positions; the decoupler is responsive to decoupler actuation commands to move from the engaged to the disengaged position; and the engine further comprises a control circuit operable to selectively supply the clutch actuation commands to each of the clutch assemblies, and the decoupler actuation commands to the decoupler. 20. A multi-spool gas turbine engine, comprising: a gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy; a high pressure starter-generator coupled to the high pressure turbine and configured to selectively operate in either (i) a generator mode, in which at least a portion of the rotational energy generated by the high pressure turbine is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy and supplied to the high pressure turbine; a first clutch assembly movable between an engaged position and a disengaged position; a multi-speed gear assembly coupled to the low pressure turbine and to the first clutch assembly, the multi-speed gear assembly operable, upon receipt of the rotational energy and in dependence on the position of the first clutch assembly, to supply a rotational drive force at a rotational speed that varies over one of a plurality of rotational speed ranges; a low pressure starter-generator coupled to the multi-speed gear assembly and configured to selectively operate in either (i) a generator mode, in which the rotational drive force supplied from the multi-speed gear assembly is converted to electrical energy or (ii) a motor mode, in which electrical energy is converted to rotational energy; a speed changer coupled between the multi-speed gear assembly and the low pressure starter-generator, the speed changer configured to change the rotational speed of the drive force supplied from the multi-speed gear assembly; a second clutch assembly movable between (i) an engaged position, in which the low pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the low pressure starter-generator is decoupled from the high pressure turbine; an interconnection gear assembly including at least in input gear coupled to the low pressure starter-generator and an output gear coupled to the high pressure turbine, the output gear coupled to the high pressure turbine when the second clutch assembly is in the engaged position; an overrunning sprag clutch assembly coupled between the low pressure starter-generator and the multi-speed gear assembly, the overrunning sprag clutch configured to (i) couple the low pressure starter-generator to the multi-speed gear assembly when the low pressure starter-generator is operating in the generate mode and (ii) decouple the low pressure starter-generator from the multi-speed gear assembly when the low pressure starter-generator is operating in the motor mode; and a decoupler coupled between the high pressure starter-generator and the high pressure turbine and movable between (i) an engaged position, in which the high pressure starter-generator is coupled to the high pressure turbine, and (ii) a disengaged position, in which the high pressure starter generator is decoupled from the high pressure turbine.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (34)
MacKay, Robin, Advanced multi pressure mode gas turbine.
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.
Kandil, Magdy A.; Vanek, Laurence D.; Abbot, James L., Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system.
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.
Lando, Jean Louis; Foch, Etienne; Roboam, Xavier; Alejo, Dominique, Device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft.
Bader, Nicolas Alain; Boudyaf, Rachid; Deguin, Thomas; Stutz, Antoine Jean Baptiste, System for controlling a plurality of functions of a turbojet 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.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.