Phase change material cooling system for a vehicle

• US 9,534,537 B2
• Filed: 03/28/2012
• Issued: 01/03/2017
• Est. Priority Date: 03/29/2011
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Gagne, Steven, Rodriguez, Rigoberto J., Siegel, William L., Arvin, John R.
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): LINDERMAN, ERIC W
• Application Number:
  US13/432,590
• Publication Number:
  US 20120247117A1
• Time in Patent Office: 1,742 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 15/08 Adaptations for driving, or combinations with, pumps
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 6/20 Adaptations of gas-turbine plants for driving vehicles
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F02C 7/141 of working fluid
• CPC Class Codes: F02C 7/16 characterised by cooling medium
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/207 using a phase changing mass, e.g. heat absorbing by melting or boiling
• CPC Class Codes: F25B 23/00 Machines, plants or systems, with a single mode of operation not covered by groups F25B1/00 - F25B21/00, e.g. using selective radiation effect
• CPC Class Codes: F25B 2400/24 Storage receiver heat
• CPC Class Codes: F41H 13/005 the high-energy beam being a laser beam
• CPC Class Codes: F41H 13/0068 the high-energy beam being of microwave type, e.g. for causing a heating effect in the target
• 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

Abstract

A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Claims

1. An apparatus comprising:

a vehicle having a gas turbine engine for providing a motive force of the vehicle coupled to an outer surface of the vehicle in a first location;

a first pod coupled to the outer surface of the vehicle in a second location, the first pod having a body extending from a leading edge to a trailing edge, the body defining a cavity therein, wherein the first location of the gas turbine engine is different from the second location of the first pod;

a first work providing device positioned in the cavity of the first pod, the first work providing device configured to generate electrical power in response to a change in a pressure of a first compressed fluid generated by a compressor stage of the gas turbine engine;

a first thermal conditioning system powered by the first work providing device, the first thermal conditioning system including a thermal energy transfer system having a first working fluid and a phase transition material capable of transferring thermal energy with one or more components of the vehicle, wherein thermal energy is transferred between the first thermal energy transfer system and the phase transition material via the first working fluid;

a second thermal conditioning system powered by the first work providing device, the second thermal conditioning system including the phase transition material and a second thermal energy transfer system having a second working fluid configured to transfer thermal energy from the phase transition material;

an electrically driven device positioned in an interior of the vehicle, the electrically driven device having a heat-producing component which generates thermal energy, the heat-producing component being in thermal communication with the phase transition material; and

a third thermal energy transfer system having a third working fluid, the third thermal energy transfer system providing thermal communication between the phase transition material and the heat-producing component, wherein the third working fluid withdraws thermal energy from the heat-producing component and delivers the thermal energy to the phase transition material.

2. The apparatus of claim 1, wherein the vehicle is an airborne vehicle capable of producing lift, and the gas turbine engine is capable of producing at least one of a thrust force and a lift force.

3. The apparatus of claim 1, further comprising:

a second pod coupled to the outer surface of the vehicle, the second pod having a body extending from a leading edge to a trailing edge, the body defining a cavity therein; and

a second work providing device positioned in the cavity of the second pod, the second work providing device configured to generate electrical power in response to a change in a pressure of a second compressed fluid;

wherein the second thermal conditioning system is powered by the second work providing device.

4. The apparatus of claim 1, wherein the first work providing device is a gas turbine engine, and wherein the first pod includes a passageway formed in the body of the first pod to receive the first compressed fluid from the gas turbine engine of the vehicle, the passageway being in fluid communication with the first work providing device.

5. The apparatus of claim 1, wherein the first pod is positioned on the vehicle such that it at least partially extends into a free stream of the vehicle.

6. The apparatus of claim 1, wherein the first pod is positioned beneath a wing of the vehicle.

7. The apparatus of claim 1, wherein the first thermal energy transfer system further includes a compressor, a condenser, an evaporator, and a pump configured to provide a motive force to the first working fluid.

8. The apparatus of claim 1, wherein the electrically driven device is powered by the electrical energy generated by the first work providing device.

9. The apparatus of claim 8, further comprising an electrical energy converter to convert the electrical energy generated by the work providing device to an appropriate voltage for use with the electrically driven device.

10. An apparatus comprising:

an aircraft including a body defining an interior compartment and one or more gas turbine engines to provide a motive force for the aircraft;

a phase-change material positioned in the interior compartment of the aircraft, the phase-change material configured to transfer thermal energy between two or more components of the aircraft;

a pod coupled to an outer surface of the aircraft, the pod having a body extending from a leading edge to a trailing edge, the body defining a cavity therein, the pod including an engine positioned in the cavity of the pod configured to generate electrical power in response to a change in a pressure of a fluid;

a first thermal energy transfer system having a first working fluid configured to transfer thermal energy from the phase-change material;

a second thermal energy transfer system having a second working fluid configured to transfer thermal energy from the phase-change material;

a device positioned in the interior compartment of the aircraft; and

a third thermal energy transfer system having a third working fluid configured to transfer thermal energy between the phase-change material and the device.

11. The apparatus of claim 10, wherein the pod further includes a generator positioned in the cavity, the generator configured to generate electrical power in response to receiving a rotational motive force generated by the engine.

12. The apparatus of claim 11, wherein the generator provides power to the first thermal energy transfer system and the device positioned in the interior compartment of the aircraft.

13. The apparatus of claim 10, wherein the first thermal energy transfer system further comprises a compressor, a condenser, and a pump configured to provide a motive force to the first working fluid.

14. The apparatus of claim 10, wherein the aircraft includes a pair of wings extending from the body of the aircraft and the pod is positioned beneath one of the pair of wings of the aircraft to be at least partially in a free stream of the aircraft.

15. The apparatus of claim 10, wherein the engine provides a motive force in response to receiving compressed fluid generated by the a compressor stage of one of the one or more gas turbine engines of the aircraft.

16. The apparatus of claim 14, wherein the pod includes a passageway formed in the body of the pod, the passageway providing fluid communication between at least one of the one or more gas turbine engines and the engine positioned within the cavity of the pod.

17. The apparatus of claim 10, wherein the pod is coupled to the aircraft in a first location, and the one or more gas turbine engines are coupled to the aircraft in one or more other locations, wherein the first location of the pod is different than the one or more other locations of the one or more gas turbine engines.