Thermal management for aircraft hydraulic systems

Patent metadata

Field	Value
Publication number	US-11261889-B2
Application number	US-201916712930-A
Country	US
Kind code	B2
Filing date	Dec 12, 2019
Priority date	Dec 12, 2019
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

The present disclosure provides an aircraft thermal management system. The aircraft thermal management system includes a first hydraulic system for circulating a first hydraulic fluid, a second hydraulic system for circulating a second hydraulic fluid, and a third hydraulic system for circulating a third hydraulic fluid. The aircraft thermal management system also includes a controller configured to: (i) determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid, and (ii) based on the determined temperature of the first hydraulic fluid, utilize the second hydraulic fluid and/or the third hydraulic fluid to modify an operational temperature of the first hydraulic fluid.

First claim

What is claimed is:

1. An aircraft thermal management system comprising:
a first hydraulic system for circulating a first hydraulic fluid;
a second hydraulic system for circulating a second hydraulic fluid;
a third hydraulic system for circulating a third hydraulic fluid; and
a controller configured to:
determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid;
compare the determined temperature of the first hydraulic fluid to a first threshold temperature and a second threshold temperature, wherein the second threshold temperature is greater than the first threshold temperature; and
based on the determined temperature of the first hydraulic fluid being between the first threshold temperature and the second threshold temperature, provide the second hydraulic fluid or the third hydraulic fluid to the first hydraulic system to thereby increase an operational temperature of the first hydraulic fluid.

2. The aircraft thermal management system of claim 1 , wherein the controller is further configured to:
provide the second hydraulic fluid and the third hydraulic fluid to the first hydraulic system to thereby increase the operational temperature of the first hydraulic fluid when the determined temperature of the first hydraulic fluid is less than or equal to the first threshold temperature.

3. The aircraft thermal management system of claim 1 , wherein the controller is further configured to:
provide the first hydraulic fluid to the second hydraulic system and/or the third hydraulic system to thereby decrease the operational temperature of the first hydraulic fluid when the determined temperature of the first hydraulic fluid is greater than or equal to the second threshold temperature.

4. The aircraft thermal management system of claim 1 , further comprising:
a first heat exchanger in fluid communication with the first hydraulic system and the second hydraulic system;
a second heat exchanger in fluid communication with the first hydraulic system and the third hydraulic system; and
a third heat exchanger in fluid communication with the second hydraulic system and the third hydraulic system.

5. The aircraft thermal management system of claim 4 , wherein each of the first heat exchanger, the second heat exchanger, and the third heat exchanger are located remote from a fuel tank.

6. The aircraft thermal management system of claim 4 , wherein each of the first heat exchanger, the second heat exchanger, and the third heat exchanger comprises a tube-in-tube heat exchanger comprising:
a first tube; and
a second tube, wherein the first tube circumscribes the second tube.

7. The aircraft thermal management system of claim 6 , wherein the first tube of the first heat exchanger is in fluid communication with the first hydraulic system, wherein the second tube of the first heat exchanger is in fluid communication with the second hydraulic system, wherein the first tube of the second heat exchanger is in fluid communication with the first hydraulic system, wherein the second tube of the second heat exchanger is in fluid communication with the third hydraulic system, wherein the first tube of the third heat exchanger is in fluid communication with the second hydraulic system, and wherein the second tube of the third heat exchanger is in fluid communication with the third hydraulic system.

8. The aircraft thermal management system of claim 4 , further comprising:
a first control valve in fluid communication with the first hydraulic system and the first heat exchanger, wherein the first heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid when the first control valve is actuated;
a second control valve coupled in fluid communication with the first hydraulic system and the second heat exchanger, wherein the second heat exchanger is configured to exchange heat between the first hydraulic fluid and the third hydraulic fluid when the second control valve is actuated; and
a third control valve in fluid communication with the second hydraulic system and the third heat exchanger, wherein the third heat exchanger is configured to exchange heat between the second hydraulic fluid and the third hydraulic fluid when the third control valve is actuated.

9. The aircraft thermal management system of claim 8 , wherein the first control valve is configured to transition from an open position to a closed position, wherein the first heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid when the first control valve is in the open position, wherein the second control valve is configured to transition from an open position to a closed position, wherein the second heat exchanger is configured to exchange heat between the first hydraulic fluid and the third hydraulic fluid when the second control valve is in the open position, wherein the third control valve is configured to transition from an open position to a closed position, wherein the third heat exchanger is configured to exchange heat between the second hydraulic fluid and the third hydraulic fluid when the third control valve is in the open position.

10. The aircraft thermal management system of claim 8 , wherein each of the first control valve, the second control valve, and the third control valve comprises a solenoid valve.

11. The aircraft thermal management system of claim 8 , further comprising:
a fourth heat exchanger in fluid communication with the first hydraulic fluid and the second hydraulic fluid;
a fourth control valve in fluid communication with the second hydraulic system and the fourth heat exchanger, wherein the fourth heat exchanger is configured to exchange heat between the second hydraulic fluid and the first hydraulic fluid when the fourth control valve is actuated;
a fifth heat exchanger in fluid communication with the first hydraulic fluid and the third hydraulic fluid;
a fifth control valve in fluid communication with the third hydraulic system and the fifth heat exchanger, wherein the fifth heat exchanger is configured to exchange heat between the third hydraulic fluid and the first hydraulic fluid when the fifth control valve is actuated;
a sixth heat exchanger in fluid communication with the second hydraulic fluid and the third hydraulic fluid; and
a sixth control valve in fluid communication with the third hydraulic system and the sixth heat exchanger, wherein the sixth heat exchanger is configured to exchange heat between the third hydraulic fluid and the second hydraulic fluid when the sixth control valve is actuated.

12. A method for managing temperatures in an aircraft, the method comprising:
circulating a first hydraulic fluid through a first hydraulic system;
circulating a second hydraulic fluid through a second hydraulic system;
circulating a third hydraulic fluid through a third hydraulic system;
determining a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid;
comparing the determined temperature of the first hydraulic fluid to a first threshold temperature and a second threshold temperature, wherein the second threshold temperature is greater than the first threshold temperature; and
based on the determined temperature of the first hydraulic fluid being greater than or equal to the second threshold temperature, providing the first hydraulic fluid to the second hydraulic system and/or the third hydraulic system to thereby decrease an operational temperature of the first hydraulic fluid.

13. The m

Assignees

• Boeing Co

Inventors

• Liao Jianmin

Classifications

• F02C7/224

  Heating fuel before feeding to the burner · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F15B2211/62

  Cooling or heating means · CPC title

• F15B21/042 Primary

  Controlling the temperature of the fluid · CPC title

• F15B2211/20576

  with multiple pumps · CPC title