Aircraft vehicle thermal management system and method

Patent metadata

Field	Value
Publication number	US-10053222-B2
Application number	US-201514692104-A
Country	US
Kind code	B2
Filing date	Apr 21, 2015
Priority date	Oct 31, 2012
Publication date	Aug 21, 2018
Grant date	Aug 21, 2018

Abstract

An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.

First claim

What is claimed is:

1. An air vehicle power and thermal management system comprising:
an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system to cool an engine fuel cooling medium and an electrically powered load;
the aircraft controller being configured to:
direct the power to create a first duration cooling power from the gas turbine engine to the cooling system to cool the engine fuel cooling medium, wherein the first duration cooling power is directed over a first power time period, and
shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period that follows the first power time period,
wherein by operation of the aircraft controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period by the first duration cooling power; and
wherein by operation of the aircraft controller the second duration cooling power is provided to a fluid control device of the cooling system to transfer the cooled engine fuel cooling medium to the electrically powered load.

2. The air vehicle power and thermal management system of claim 1 , wherein the aircraft controller is configured to direct the power to create the load electrical power at a higher wattage than the first duration cooling power.

3. The air vehicle power and thermal management system of claim 1 , wherein the aircraft controller comprises multiple controllers.

4. The air vehicle power and thermal management system of claim 1 , wherein the aircraft controller is configured to direct the power to create the first duration cooling power from the gas turbine engine to a refrigeration device of the cooling system to cool the engine fuel cooling medium.

5. The air vehicle power and thermal management system of claim 4 , wherein by operation of the aircraft controller the second duration cooling power is provided as zero watts to the refrigeration device of the cooling system.

6. The air vehicle power and thermal management system of claim 1 , wherein the aircraft controller is configured to direct the power to create the first duration cooling power at a higher wattage than the second duration cooling power.

7. An aircraft thermal regulation system for thermally cooling an electrically driven aircraft component, comprising:
a thermal management device, an electrically driven aircraft component, an aircraft power source, and an air vehicle control unit;
the thermal management device being configured to operate at a first power to reduce a temperature of a cooling system fluid in a cooling system reservoir and at a second power to use the cooling system fluid from the cooling system reservoir to cool the electrically driven aircraft component;
the electrically driven aircraft component being configured to operate at a third power;
the aircraft power source being configured to provide the first power and the second power to the thermal management device and to provide the third power to the electrically driven aircraft component; and
the air vehicle control unit being configured to control a flow of power from the aircraft power source to provide the first power over a first period of time, and to control the flow of power from the aircraft power source to discontinue the first power and provide the second power and the third power over a second period of time;
wherein by operation of the air vehicle control unit, power is provided to the thermal management device to transfer the cooling system fluid from the cooling system reservoir to the electrically driven aircraft component.

8. The aircraft thermal regulation system of claim 7 , wherein the thermal management device includes a refrigeration unit to reduce the temperature of the cooling system fluid in the cooling system reservoir.

9. The aircraft thermal regulation system of claim 7 , wherein the thermal management device includes a thermal transfer unit to cool the electrically driven aircraft component.

10. The aircraft thermal regulation system of claim 7 , wherein the thermal management device includes a refrigeration unit to reduce the temperature of the cooling system fluid, and a fluid control unit to transfer the cooling system fluid from the refrigeration unit to the electrically driven aircraft component and back to the refrigeration unit;
the thermal management device being configured to operate at a fourth power to drive the refrigeration unit and the fluid control unit;
the aircraft power source being configured to provide the fourth power to the thermal management device; and
the air vehicle control unit being configured to control the aircraft power source to provide the fourth power over at least a portion of the first period of time.

11. The aircraft thermal regulation system of claim 10 , wherein the second power is zero watts over at least a portion of the second period of time.

12. The aircraft thermal regulation system of claim 7 , wherein the third power at which the electrically driven aircraft component is configured to operate is relatively greater than the first power and relatively greater than the second power at which the thermal management device operates.

13. A method of thermally managing an electrical system of an air vehicle comprising:
providing power to a cooling system of the air vehicle to cool a thermal storage medium stored in a reservoir;
reducing the power to the cooling system for an amount of time;
directing power to the electrical system and using the cooled thermal storage medium stored in the reservoir to cool the electrical system for at least a portion of the amount of time; and
providing cooling power, by operation of an aircraft controller, to a fluid control device of the cooling system to transfer the cooled engine fuel cooling medium to an electrically powered load of the electrical system.

14. The method of claim 13 , wherein the thermal storage medium includes a portion of the engine fuel of the air vehicle.

15. The method of claim 13 , wherein the providing power to the cooling system comprises power to a cyclic refrigeration system of the cooling system to cool the thermal storage medium stored in the reservoir.

16. An air vehicle power and thermal management system comprising:
an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system to cool an engine fuel cooling medium and an electrically powered load;
the aircraft controller being configured to:
direct the power to create a first duration cooling power from the gas turbine engine to the cooling system to cool the engine fuel cooling medium, wherein the first duration cooling power is directed over a first power time period, and
shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period that follows the first power time period,

wherein by operation of the aircraft controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period by the first duration cooling power; and
wherein the aircraft controller is configured to dire

Assignees

• Rolls Royce Corp

Inventors

• Snyder Douglas J

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D33/08 Primary

  of power plant cooling systems · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title