[특허]Hybrid propulsive engine including at least one independently rotatable compressor stator

The Invention Science Fund I, LLC

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Hybrid propulsive engine including at least one independently rotatable compressor stator

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/057
미국특허분류(USC)	060/039.23; 060/802
출원번호	US-0287500 (2008-10-08)
등록번호	US-8109073 (2012-02-07)
발명자 / 주소	Foster, Glenn B. Hyde, Roderick A. Ishikawa, Muriel Y. Jung, Edward K. Y. Kare, Jordin T. Myhrvold, Nathan P. Tegreene, Clarence T. Weaver, Thomas Allan Wood, Jr., Lowell L. Wood, Victoria Y. H.
출원인 / 주소	The Invention Science Fund I, LLC
인용정보	피인용 횟수 : 14 인용 특허 : 19

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A hybrid propulsive technique includes providing a flow of a working fluid through at least a portion of an at least one jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to a torque. The hybrid propulsive technique also comprises rotating an at least one independently rotatable compressor stator at least partially responsive to the converting the at least a portion of the electrical power to t...

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1. A hybrid propulsive engine, comprising: at least one jet engine associated with a working fluid passing there through, theat least one jet engine including at least one compressor section, wherein the compressor section includes at least one compressor stage, and wherein the at least one compressor stage includes at least one compressor rotor and at least one independently rotatable compressor stator rotates about an engine axis;at least one energy extraction mechanism configured to extract energy from the working fluid and to at least partially convert the extracted energy to electrical power;at least one torque conversion mechanism configured to convert at least a portion of the electrical power to torque; andwherein the at least one independently rotatable compressor stator is rotatably driven at least partially responsively to the at least one torque conversion mechanism configured to convert at least a portion of the electrical power to torque. 2. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises at least one electric generator. 3. The hybrid propulsive engine of claim 1, wherein the at least one torque conversion mechanism comprises at least one electric motor. 4. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one electrical energy extraction mechanism configured to extract energy from rotation of at least one turbine rotational element. 5. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable compressor stator is configured for independently controllable rotation relative to at least one turbine rotational element. 6. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable compressor stator is configured for independently controllable rotation relative to at least one compressor rotor. 7. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one heat engine configured to extract at least some heat from the working fluid that is at least partially applied to at least one heat receptive fluid. 8. The hybrid propulsive engine of claim 7, wherein the at least one energy extraction mechanism includes at least one thermoelectric heat engine configured to extract electric power from the at least one heat receptive fluid. 9. The hybrid propulsive engine of claim 7, wherein the at least one energy extraction mechanism includes a turbine section, and wherein the turbine section is configured to extract electric power from the at least one heat receptive fluid. 10. The hybrid propulsive engine of claim 7, wherein the at least one energy extraction mechanism comprises at least one magnetohydrodynamic device that is configured to extract electric power from the at least one heat receptive fluid. 11. The hybrid propulsive engine of claim 7, wherein the at least one heat receptive fluid is configured to undergo a phase change rise responsive to the applied heat. 12. The hybrid propulsive engine of claim 7, wherein the at least one heat receptive fluid is configured to undergo a temperature rise responsive to the applied heat. 13. The hybrid propulsive engine of claim 7, wherein the at least one heat receptive fluid at least partially flows around a closed loop. 14. The hybrid propulsive engine of claim 7, wherein the at least one heat receptive fluid at least partially flows around an open loop. 15. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one thermoelectric heat engine configured to extract heat energy from the working fluid. 16. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one magnetohydrodynamic device configured to extract kinetic energy from a flow of the working fluid. 17. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes an at least one turbojet. 18. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one substantially axial-flow jet engine. 19. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one ramjet jet engine. 20. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one externally heated jet engine. 21. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one combustion driven jet engine. 22. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one heat engine configured to extract at least some heat from the working fluid that is at least partially applied to a heat receptive fluid, wherein the at least one energy extraction mechanism comprises a Rankine Cycle energy extraction mechanism configured to extract electrical power from the working fluid. 23. The hybrid propulsive engine of claim 1, further comprising at least one secondary source of electrical energy configured to supply energy to the at least one torque conversion mechanism. 24. The hybrid propulsive engine of claim 23, wherein the at least one secondary source of electrical energy is arranged to obtain at least some electricity from at least one primary energy source. 25. The hybrid propulsive engine of claim 23, wherein the at least one secondary source of electrical energy includes at least one rechargeable energy storage device. 26. The hybrid propulsive engine of claim 25, wherein the at least one rechargeable energy storage device is coupled to receive charge from at least partially from the at least one energy extraction mechanism. 27. The hybrid propulsive engine of claim 25, wherein the at least one rechargeable energy storage device is coupled to receive charge from at least partially from the at least one torque conversion mechanism configured to convert the at least the portion of the electric power to torque. 28. The hybrid propulsive engine of claim 25, wherein the at least one rechargeable energy storage device is coupled to at least partially charge from an at least one external power source. 29. The hybrid propulsive engine of claim 1, further comprising a hybrid propulsive engine starter configured to rotate at least a portion of the at least one jet engine at a sufficient rotational velocity to enhance starting the hybrid propulsive engine. 30. The hybrid propulsive engine of claim 1, further comprising a hybrid propulsive engine starter configured to rotate at least a portion of the at least one independently rotatable compressor stator at a sufficient rotational velocity to enhance starting the hybrid propulsive engine. 31. The hybrid propulsive engine of claim 1, further including a fluid guide arranged such that at least some of the working fluid passes through the at least one independently rotatable compressor stator. 32. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable compressor stator is configured to be powered for a controllable rotation in a first direction or alternately in a second direction that is reversed from the first direction. 33. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable compressor stator is configured to be variably powered for a variable speed rotation. 34. The hybrid propulsive engine of claim 1, further comprising a control circuit to allow a user to control a suitable rotational velocity of the at least one independently rotatable compressor stator based at least partially on a user input indicating a desired flight condition. 35. The hybrid propulsive engine of claim 1, further comprising a control circuit to allow a user to control a suitable rotational velocity of the at least one independently rotatable compressor stator based at least partially on a sensed flight parameter.

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이 특허를 인용한 특허 피인용횟수: 14

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Hybrid propulsive engine including at least one independently rotatable compressor stator

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이 특허에 인용된 특허 (19)

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Hybrid propulsive engine including at least one independently rotatable compressor stator

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이 특허에 인용된 특허 (19)

이 특허를 인용한 특허 피인용횟수: 14

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IPC 상세정보(version : 201201)

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