Hybrid propulsive engine including at least one independently rotatable turbine stator

• US 20100126178A1
• Filed: 10/30/2009
• Published: 05/27/2010
• Est. Priority Date: 10/08/2008
• Status: Abandoned Application

• Current Assignee: Searete LLC (Intellectual Ventures LLC)
• Original Assignee: Searete LLC (Intellectual Ventures LLC)
• Inventors: Ishikawa, Muriel Y., Weaver, Thomas A., Myhrvold, Nathan P., Tegreene, Clarence T., Jung, Edward K.Y., Wood, Lowell L. JR., Hyde, Roderick A., Kare, Jordin T., Wood, Victoria Y.H.
• Application Number:
  US12/590,047
• Publication Number:
  US 20100126178A1
• Time in Patent Office: Days
• US Class Current: 60/767
• CPC Class Codes: B64D 2027/026 comprising different types of power plants, e.g. combination of an electric motor and a gas-turbines
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01K 23/10 with exhaust fluid of one cycle heating the fluid in another cycle F01K17/025 takes precedence
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• 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: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02K 3/025 the by-pass flow being at least partly used to create an independent thrust component
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/72 a steam turbine
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2240/50 Bearings
• CPC Class Codes: H02K 7/1823 structurally associated with turbines or similar engines
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

One aspect relates to a hybrid propulsive technique, comprising 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.

Claims

1. A hybrid propulsive engine, comprising:

an at least one jet engine associated with a working fluid passing there through, the at least one jet engine including a turbine section, the turbine section including an at least one turbine rotor and an at least one independently rotatable turbine stator;

an at least one energy extraction mechanism configured to extract energy from the working fluid, and at least partially convert the that energy to electrical power; and

an at 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 the portion of the electrical power to torque.

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 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 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. A 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.

14. 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.

15. 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.

16. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes an at least one turbojet.

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

18. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes an at least one ramjet jet engine.

19. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes an at least one externally heated jet engine.

20. The hybrid propulsive engine of claim 1, wherein the at least one jet engine includes an 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.

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 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, that is applied to an aircraft.

34. The hybrid propulsive engine of claim 1, that is applied to a boat or ship.

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

36. The hybrid propulsive engine of claim 1, that is applied to a land vehicle.

37. 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.

38. 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.

7-13. -13. (canceled)

23-27. -27. (canceled)

39. A hybrid propulsive method, comprising:

providing a flow of a working fluid through at least a portion of an at least one jet engine, wherein 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, and wherein the at least one turbine stage includes an at least one turbine rotor and an at least one independently rotatable turbine stator;

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 the 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.

40-62. -62. (canceled)

63. A hybrid propulsive method, comprising:

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

extracting energy from the working fluid that is at least partially converted into a electrical power;

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

rotating an at least one independently rotatable turbine stator at least partially responsive to the converting the at least a portion of the electrical power to a torque.

64. The hybrid propulsive method of claim 63, further comprising:

stopping a rotation of the at least one jet engine; and

restarting the rotation of the at least one jet engine at least partially using the torque used to rotate the at least one independently rotatable turbine stator.

65. The hybrid propulsive method of claim 63, further comprising:

starting a rotational operation of the second one of the at least one jet engine at least partially responsive to the rotating the at least one independently rotatable turbine stator.

66. A hybrid propulsive method, comprising:

providing a flow of a working fluid through at least a portion of an at least one jet engine, wherein the at least one jet engine includes at least one turbine stage, and wherein the at least one turbine stage includes an at least one turbine rotor and an at least one independently rotatable turbine stator;

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 the 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 and responsive to a control signal representative of a command to use electrical power.

67. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid is at least partially performed with an at least one energy extraction mechanism.

68. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid is at least partially performed with an at least one electric generator.

69. The hybrid propulsive method of claim 66, 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.

70. The hybrid propulsive method of claim 66, wherein the converting at least a portion of the electrical power to torque is at least partially performed using at least one electric motor.

71. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid comprises extracting energy from motion of the working fluid using the at least one turbine rotor.

72. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid comprises extracting heat energy from an at least one heat receptive fluid.

77. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid comprises extracting kinetic energy from the working fluid involving an at least one magnetohydrodynamic device.

78. The hybrid propulsive method of claim 66, further comprising supplying energy to at least partially perform the converting at least a portion of the electrical power to torque.

83. The hybrid propulsive method of claim 66, wherein the extracting energy at least partially in the form of electrical power from the working fluid is at least partially responsive to the working fluid being applied to an at least one turbine rotor to rotate the at least one turbine rotor.

84. The hybrid propulsive method of claim 66, further comprising controllably powering the at least one independently rotatable turbine stator for a controllable rotation in a first direction or alternately in a second direction that is reversed from the first direction.

85. The hybrid propulsive method of claim 66, further comprising varying the torque applied to the at least one independently rotatable turbine stator to vary a rotational velocity of the at least one independently rotatable turbine stator.

73-76. -76. (canceled)

79-82. -82. (canceled)

86-89. -89. (canceled)

90. A hybrid propulsive method, comprising:

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

selectively extracting energy from the working fluid that is at least partially converted into a electrical power;

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

rotating an at least one independently rotatable turbine stator at least partially responsive to the converting the at least a portion of the electrical power to a torque.

91. The hybrid propulsive method of claim 90, further comprising:

stopping a rotation of the at least one jet engine; and

restarting the rotation of the at least one jet engine at least partially using the torque used to rotate the at least one independently rotatable turbine stator.

92. The hybrid propulsive method of claim 90, further comprising:

starting a rotational operation of the second one of the at least one jet engine at least partially responsive to the rotating the at least one independently rotatable turbine stator.

93. The hybrid propulsive method of claim 90, wherein the selectively extracting is based on a control signal.