Two-shaft engine for aircraft with high electric power demand
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/36
F02K-003/04
출원번호
US-0806544
(2007-06-01)
등록번호
US-8522526
(2013-09-03)
우선권정보
DE-10 2006 026 287 (2006-06-02)
발명자
/ 주소
Talan, Metin
출원인 / 주소
Rolls-Royce Deutschland Ltd & Co.
대리인 / 주소
Klima, Timothy J.
인용정보
피인용 횟수 :
1인용 특허 :
7
초록▼
With an engine for aircraft with high electric power demand, the power of the low-pressure shaft (7) operating in a lower speed range is transmitted to the high-pressure shaft (6) by an electromagnetic clutch (10). In the clutch element (14) on the side of the low-pressure shaft a frequency-controll
With an engine for aircraft with high electric power demand, the power of the low-pressure shaft (7) operating in a lower speed range is transmitted to the high-pressure shaft (6) by an electromagnetic clutch (10). In the clutch element (14) on the side of the low-pressure shaft a frequency-controllable rotary field is generated, which drives a magnet (13) connected to the high-pressure shaft.
대표청구항▼
1. A two-shaft engine for aircraft with high electric power demand, comprising: a high-pressure shaft connected to at least one generator and driven by a high-pressure turbine,a low-pressure shaft driven by a low-pressure turbine,an electronic engine control system,an electromagnetic clutch connecti
1. A two-shaft engine for aircraft with high electric power demand, comprising: a high-pressure shaft connected to at least one generator and driven by a high-pressure turbine,a low-pressure shaft driven by a low-pressure turbine,an electronic engine control system,an electromagnetic clutch connecting the low-pressure shaft to the high-pressure shaft for non-contact transmission of power from the low-pressure shaft to the high pressure shaft in a variable speed relationship, the electromagnetic clutch also connected to the engine control system, andwherein the engine control system controls the electromagnetic clutch to create a freely settable frequency-controllable rotary field in the electromagnetic clutch to compensate for significant speed ratio differences from idle to flight power conditions between the low-pressure shaft and the high-pressure shaft that allows the low-pressure shaft to transmit power to the high-pressure shaft even though the low-pressure shaft operates at a lower RPM than the high-pressure shaft. 2. A two-shaft engine in accordance with claim 1, wherein the electromagnetic clutch comprises: a coil ring connected to the low-pressure shaft and including several annularly arranged coil sections activated by the engine control system to control the frequency of the rotary field, anda magnet connected to the high-pressure shaft and engaging the rotary field of the coil ring. 3. A two-shaft engine in accordance with claim 2, and further comprising a gear train for connecting each side of the electromagnetic clutch to the low-pressure shaft and to the high-pressure shaft, respectively. 4. A two-shaft engine in accordance with claim 3, and further comprising: a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 5. A two-shaft engine in accordance with claim 2, and further comprising: a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 6. A two-shaft engine in accordance with claim 1, and further comprising: a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 7. A two-shaft engine in accordance with claim 1, and further comprising a gear train for connecting each side of the electromagnetic clutch to the low-pressure shaft and to the high-pressure shaft, respectively. 8. A method for controlling a two-shaft engine for aircraft with high electric power demand, comprising: providing a high-pressure shaft connected to at least one generator and driven by a high-pressure turbine,providing a low-pressure shaft driven by a low-pressure turbine,providing an electronic engine control system,providing an electromagnetic clutch connecting the low-pressure shaft to the high-pressure shaft for non-contact transmission of power from the low-pressure shaft to the high pressure shaft in a variable speed relationship,connecting the electromagnetic clutch to the engine control system, andcontrolling the electromagnetic clutch with the engine control system to create a freely settable frequency-controllable rotary field in the electromagnetic clutch to compensate for significant speed ratio differences from idle to flight power conditions between the low-pressure shaft and the high-pressure shaft that allows the low-pressure shaft to transmit power to the high-pressure shaft even though the low-pressure shaft operates at a lower RPM than the high-pressure shaft. 9. The method of claim 8, and further comprising providing the electromagnetic clutch with: a coil ring connected to the low-pressure shaft and including several annularly arranged coil sections activated by the engine control system to control the frequency of the rotary field, anda magnet connected to the high-pressure shaft and engaging the rotary field of the coil ring. 10. The method of claim 9, and further comprising providing a gear train for connecting each side of the electromagnetic clutch to the low-pressure shaft and to the high-pressure shaft, respectively. 11. The method of claim 10, and further comprising: providing a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 12. The method of claim 9, and further comprising: providing a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 13. The method of claim 8, and further comprising: providing a braking device positioned on the low-pressure shaft side of the electromagnetic clutch for arresting the clutch element connected to the low-pressure shaft in a non-rotatable position, in order to accelerate the high-pressure shaft at engine start with the rotary field. 14. The method of claim 8, and further comprising providing a gear train for connecting each side of the electromagnetic clutch to the low-pressure shaft and to the high-pressure shaft, respectively.
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이 특허에 인용된 특허 (7)
Glinski Robert L. (Wellington FL) Perkins Gary M. (Palm Beach Gardens FL), Gas turbine engine arrangement.
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