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

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Hybrid propulsive engine including at least one independently rotatable turbine stator

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/275
미국특허분류(USC)	060/788;
출원번호	US-0287501 (2008-10-08)
등록번호	US-8291716 (2012-10-23)
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 : 13 인용 특허 : 19

초록
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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 at least one jet engine includes an at least one turbine section, wherein the at least one turbine section includes at least one turbine stage. The at least one turbine stage includes an at least one turbine rotor and an at least one independently rotatable turbine stator. The hybrid propulsive technique further involves extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one at least one independently rotatable turbine stator at least partially responsive to the converting the at least a portion of the electrical power to torque.

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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 a turbine section, the turbine section including at least one turbine rotor and at least one independently rotatable turbine stator having a stator member that rotates with a turbine shaft to assist in starting the jet engine;at least one energy extraction mechanism configured to extract energy from the working fluid, and at least partially convert that energy to electrical power; andat least one torque conversion mechanism configured to convert at least a portion of the electrical power to torque, wherein the at least one independently rotatable turbine stator of the turbine section is rotatably driven at least partially responsively to the at least one torque conversion mechanism configured to convert the at least a portion of the electrical power to torque,wherein the at least one energy extraction mechanism and the at least one torque conversion mechanism are configured to be run selectively simultaneously. 2. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism includes at least one electric generator. 3. The hybrid propulsive engine of claim 1, wherein the at least one torque conversion mechanism includes 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 the at least one turbine rotor. 5. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable turbine stator is configured for independently controllable rotation relative to the at least one turbine. 6. 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 an at least one heat receptive fluid. 7. The hybrid propulsive engine of claim 6, wherein the at least one energy extraction mechanism includes at least one thermoelectric heat engine configured to extract heat energy from the at least one heat receptive fluid. 8. The hybrid propulsive engine of claim 6, wherein the jet engine further comprises a second turbine section wherein the second turbine section is configured to extract electric power from the at least one heat receptive fluid. 9. The hybrid propulsive engine of claim 6, wherein the at least one energy extraction mechanism includes at least one magnetohydrodynamic device that is configured to extract electric power from the at least one heat receptive fluid. 10. The hybrid propulsive engine of claim 6, wherein the at least one heat receptive fluid is configured to undergo a phase change. 11. The hybrid propulsive engine of claim 6, wherein the at least one heat receptive fluid is configured to undergo a temperature rise. 12. The hybrid propulsive engine of claim 6, wherein the at least one heat receptive fluid at least partially flows around a closed loop responsive to the applied heat. 13. The hybrid propulsive engine of claim 6, wherein the at least one heat receptive fluid at least partially flows around an open loop responsive to the applied heat. 14. 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. 15. 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. 16. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one turbojet. 17. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one substantially axial-flow jet engine. 18. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one ramjet jet engine. 19. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one externally heated jet engine. 20. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes at least one combustion driven jet engine. 21. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises 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. 22. 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. 23. The hybrid propulsive engine of claim 22, wherein the at least one secondary source of electrical energy is arranged to obtain at least some electrical power from at least one primary energy source. 24. The hybrid propulsive engine of claim 22, wherein the at least one secondary source of electrical energy comprises at least one rechargeable energy storage device. 25. The hybrid propulsive engine of claim 24, wherein the at least one rechargeable energy storage device is coupled to charge at least partially from the at least one energy extraction mechanism. 26. The hybrid propulsive engine of claim 24, wherein the at least one rechargeable energy storage device is coupled to charge 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. 27. The hybrid propulsive engine of claim 24, wherein the at least one rechargeable energy storage device is at least partially charged from at least one external power source. 28. The hybrid propulsive engine of claim 1, further comprising a hybrid propulsive engine starter configured to rotate at least a portion of the jet engine at a sufficient rotational velocity to enhance starting the hybrid propulsive engine. 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 independently rotatable turbine stator at a sufficient rotational velocity to enhance starting the hybrid propulsive engine. 30. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable turbine stator is arranged so that at least some of the working fluid passes through the at least one independently rotatable turbine stator. 31. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable turbine 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. 32. The hybrid propulsive engine of claim 1, wherein the at least one independently rotatable turbine stator is configured to be variably powered for a variable speed rotation. 33. 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 turbine stator based at least partially on a user input indicating a desired flight condition. 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 turbine stator based at least partially on a sensed flight parameter.

이 특허에 인용된 특허 (19)

이 특허를 인용한 특허 피인용횟수: 13

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Hybrid propulsive engine including at least one independently rotatable turbine stator

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이 특허에 인용된 특허 (19)

이 특허를 인용한 특허 피인용횟수: 13

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Hybrid propulsive engine including at least one independently rotatable turbine stator

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이 특허에 인용된 특허 (19)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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