Hybrid propulsive engine including at least one independently rotatable compressor rotor

• US 8,596,036 B2
• Filed: 10/30/2009
• Issued: 12/03/2013
• Est. Priority Date: 10/08/2008
• Status: Expired due to Fees

• Current Assignee: Enterprise Science Fund, LLC (Intellectual Ventures LLC)
• Original Assignee: The Invention Science Fund I, L.L.C. (Intellectual Ventures LLC)
• Inventors: Hyde, Roderick A., Ishikawa, Muriel Y., Jung, Edward K. Y., Kare, Jordin T., Myhrvold, Nathan P., Tegreene, Clarence T., Weaver, Thomas A., Wood, Lowell L. Jr., Wood, Victoria Y. H.
• Primary Examiner(s): Wongwian, Phutthiwat
• Application Number:
  US12/590,046
• Publication Number:
  US 20100107652A1
• Time in Patent Office: 1,495 Days
• Field of Search: 602/261, 607/86, 607/88, 608/02, 608/05, 602/04, 290/52, 244/53.B, 244/53.R, 244/60
• US Class Current: 60/204
• CPC Class Codes: F02C 6/00 Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• CPC Class Codes: F02C 6/18 using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants using waste heat as source of energy for refrigeration plants F25B27/02; using the waste heat of a gasturbine for steam generation or in a steam cycle see F01K23/10
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/31 in steam turbines
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2220/325 to drive unshrouded, high solidity propeller
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y02T 70/50 Measures to reduce greenhouse gas emissions related to the propulsion system

Abstract

A hybrid propulsive technique, comprises providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique includes 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 includes rotating an at least one substantially axial-flow independently rotatable compressor rotor at least partially responsive to the converting the at least a portion of the electrical power to torque.

Claims

1. A hybrid propulsive engine, comprising:

an at least one co-axial-flow jet engine including an at least one substantially co-axial-flow independently rotatable compressor rotor drivingly connected to a turbine via a shaft, wherein the at least one co-axial-flow jet engine is configured to provide an at least one thrust associated with a working fluid passing through at least a portion of the at least one axial-flow jet engine;

an at least one mechanical energy extraction mechanism configured to extract energy from the working fluid by being directly mechanically driven by the movement of the working fluid and being mechanically coupled to the energy extraction mechanism, and at least partially convert that energy to electrical power;

a control circuit to allow a user to control a suitable rotational velocity of the at least one substantially co-axial-flow independently rotatable compressor rotor based at least partially on a user input indicating a desired flight condition;

an at least one torque conversion mechanism configured to convert at least a portion of the electrical power to torque; and

the at least one substantially co-axial-flow independently rotatable compressor rotor mounted to rotates on bearing members that disposed radially outward from the axial-flow independently rotatable compressor rotor and configured to be rotatably driven at least partially responsively from the torque provided by the at least one torque conversion mechanism.

2. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises an at least one electric generator.

3. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises an at least one turbine rotational element configured to extract energy from motion of the working fluid within the at least one co-axial-flow jet engine.

4. The hybrid propulsive engine of claim 1, further comprising a second torque conversion mechanism configured to generate a second torque, wherein the at least one substantially co-axial-flow independently rotatable compressor rotor is configured to be powered for rotation at least partially responsive to the second torque conversion mechanism configured to generate the second torque in addition to the at least one torque conversion mechanism configured to convert the at least a portion of the electrical power to torque.

5. The hybrid propulsive engine of claim 4, further comprising an at least one turbine rotational element configured to rotate at least partially responsive to the working fluid within the at least one co-axial-flow jet engine, and wherein the second torque conversion mechanism is configured to generate the second torque responsive to a rotation of the at least one turbine rotational element.

6. The hybrid propulsive engine of claim 4, further comprising a clutch mechanism configured to adjust a ratio of the torque and the second torque that powers the at least one substantially axial-flow independently rotatable compressor rotor for rotation.

7. The hybrid propulsive engine of claim 1, wherein the at least one torque conversion mechanism comprises at least one electric motor.

8. 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 an at least one substantially axial-flow turbine rotational element.

9. The hybrid propulsive engine of claim 1, wherein the at least one substantially axial-flow independently rotatable compressor rotor is configured for independently controllable rotation relative to an at least one substantially axial-flow turbine rotational element.

10. 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.

11. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises an at least one thermoelectric heat engine configured to extract heat energy from the working fluid.

12. The hybrid propulsive engine of claim 1, wherein the at least one energy extraction mechanism comprises an at least one magnetohydrodynamic device configured to extract kinetic energy from a flow of the working fluid.

13. The hybrid propulsive engine of claim 1, wherein the at least one co-axial-flow jet engine includes an at least one turbojet.

14. The hybrid propulsive engine of claim 1, wherein the at least one co-axial-flow jet engine includes an at least one ramjet jet engine.

15. The hybrid propulsive engine of claim 1, wherein the at least one co-axial-flow jet engine includes an at least one externally heated jet engine.

16. The hybrid propulsive engine of claim 1, wherein the at least one axial-flow jet engine includes an at least one combustion driven jet engine.

17. 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 the electric power in the form of heat from the working fluid.

18. 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.

19. 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 co-axial-flow jet engine at a sufficient rotational velocity to enhance starting the hybrid propulsive engine.

20. The hybrid propulsive engine of claim 1, further comprising a hybrid propulsive engine starter configured to rotate at least a portion of an at least one substantially co-axial-flow independently rotatable compressor rotor at a sufficient rotational velocity to enhance starting the hybrid propulsive engine.

21. The hybrid propulsive engine of claim 1, wherein at least some of the working fluid passes through the at least one substantially co-axial-flow independently rotatable compressor rotor.

22. The hybrid propulsive engine of claim 1, wherein the at least one substantially co-axial-flow independently rotatable compressor rotor is configured to compress at least some of the working fluid.

23. The hybrid propulsive engine of claim 1, wherein the at least one substantially co-axial-flow independently rotatable compressor rotor 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.

24. The hybrid propulsive engine of claim 1, wherein the at least one substantially co-axial-flow independently rotatable compressor rotor is configured to be variably powered for a variable speed rotation.

25. The hybrid propulsive engine of claim 1, that is applied to an aircraft.

26. The hybrid propulsive engine of claim 1, that is applied to a hovercraft.

27. A hybrid propulsive method, comprising:

providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine;

extracting energy at least partially in the form of electrical power from the working fluid;

converting at least a portion of the electrical power to torque; and

rotating an at least one substantially axial-flow independently rotatable compressor rotor that mounted to rotate on bearing members that disposed radially outward from the axial-flow independently rotatable compressor rotor, at least partially responsive to the converting the at least a portion of the electrical power to torque to produce thrust during inflight operation, wherein the at least one substantially axial-flow independently rotatable compressor rotor is drivingly connected to a turbine via a shaft.

28. A hybrid propulsive method, comprising:

providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine;

extracting energy mechanically, from the working fluid driving at least one rotatable element that is directly mechanically coupled to an energy extraction mechanism, that is at least partially converted into an electrical power;

converting at least a portion of the first electrical power to a torque; and

rotating an at least one substantially axial-flow independently rotatable compressor rotor that mounted to rotates on bearing members that disposed radially outward from the axial-flow independently rotatable compressor rotor, at least partially responsive to the converting the at least a portion of the electrical power to the torque to produce thrust during inflight operation, wherein the at least one substantially axial-flow independently rotatable compressor rotor is drivingly connected to a turbine via a shaft.

29. The hybrid propulsive method of claim 28, further comprising:

stopping a rotation of the substantially axial-flow independently rotatable compressor rotor; and

restarting the rotation of the at least one jet engine at least partially using the torque used to rotate the substantially axial-flow independently rotatable compressor rotor.

30. The hybrid propulsive method of claim 28, further comprising:

starting a rotational operation of the at least one jet engine at least partially responsive to the rotating the substantially axial-flow independently rotatable compressor rotor.

31. A method of driving a rotational element, comprising:

moving a working fluid through at least a portion of an at least one axial flow jet engine;

extracting energy mechanically at least partially in the form of electrical power from the working fluid, by the movement of the working fluid driving at least one mechanical element that is directly mechanically coupled to an energy extraction mechanism;

converting at least a portion of the electrical power to torque; and

rotating an at least one rotatable compressor rotor that mounted to rotates on bearing members that disposed radially outward from the axial-flow independently rotatable compressor rotor, at least partially responsive to the torque from the converting to produce thrust during inflight operation, wherein the at least one substantially axial-flow independently rotatable compressor rotor is drivingly connected to a turbine via a shaft.

32. The method of claim 31, wherein the extracting energy at least partially in the form of the electrical power from the working fluid is at least partially performed with an at least one energy extraction mechanism.

33. The method of claim 31, further comprising generating a second torque, and powering the substantially axial-flow independently rotatable compressor rotor for rotation at least partially responsive to the second torque in addition to the torque.

34. The method of claim 31, wherein the extracting energy at least partially in the form of the electrical power from the working fluid is at least partially performed with an at least one electric generator.

35. The method of claim 31, wherein the converting at least a portion of the electrical power to torque is at least partially performed using at least one torque conversion mechanism.

36. The method of claim 31, wherein the converting at least a portion of the electrical power to torque is at least partially performed using at least one electric motor.

37. The method of claim 31, wherein the extracting energy at least partially in the form of electrical power comprises extracting energy from motion of the working fluid within the at least one axial-flow jet engine using an at least one turbine rotational element.

38. The method of claim 31, wherein the energy that is at least partially extracted in the form of the electrical power from the working fluid is at least partially applied to an at least one heat receptive fluid.

39. The method of claim 31, further comprising controllably powering the substantially axial-flow independently rotatable compressor rotor to be powered for a controllable rotation in a first direction or alternately in a second direction that is reversed from the first direction.

40. A hybrid propulsive method, comprising:

providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine;

extracting energy mechanically, from the working fluid driving at least one rotatable element that is directly mechanically coupled to an energy extraction mechanism, that is at least partially converted into an electrical power;

converting at least a portion of the first electrical power to a torque; and

rotating an at least one substantially axial-flow independently rotatable compressor rotor that mounted to rotates on bearing members that disposed radially outward from the axial-flow independently rotatable compressor rotor, at least partially responsive to the converting the at least a portion of the electrical power to the torque to produce thrust during inflight operation, wherein the at least one substantially axial-flow independently rotatable compressor rotor is drivingly connected to a turbine via a shaft.

41. The hybrid propulsive method of claim 40, further comprising:

stopping a rotation of the substantially axial-flow independently rotatable compressor rotor; and

restarting the rotation of the at least one jet engine at least partially using the torque used to rotate the substantially axial-flow independently rotatable compressor rotor.

42. The hybrid propulsive method of claim 40, further comprising:

starting a rotational operation of the at least one jet engine at least partially responsive to the rotating the substantially axial-flow independently rotatable compressor rotor.