Aircraft systems and methods utilizing waste heat in fuel

Patent metadata

Field	Value
Publication number	US-11199133-B2
Application number	US-201816222599-A
Country	US
Kind code	B2
Filing date	Dec 17, 2018
Priority date	Dec 17, 2018
Publication date	Dec 14, 2021
Grant date	Dec 14, 2021

Abstract

An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

First claim

What is claimed is:

1. An aircraft fuel system, comprising:
a main fuel line configured to transport fuel to an engine;
a fuel pump disposed on the main fuel line;
a pump return fuel line connected to the main fuel line to take a portion of the fuel from the main fuel line at a position downstream of the fuel pump and to return the portion of the fuel to the main fuel line at a position upstream of the fuel pump;
an exposed aircraft structure in direct or indirect thermal communication with the fuel to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure; and
a thermal fuel line that either:
runs from the pump return fuel line to the exposed aircraft structure in the case of direct thermal communication, or
runs from the pump return fuel line to a fuel/fluid heat exchanger which is in thermal communication with the exposed aircraft structure in the case indirect thermal communication.

2. The system of claim 1 , further comprising a valve disposed in the thermal fuel line thermally upstream of the exposed aircraft structure and configured to selectively shutoff and/or meter the fuel that is in thermal communication with the exposed aircraft structure.

3. The system of claim 1 , wherein, in the case of direct thermal communication, the exposed aircraft structure includes at least one internal fuel channel in fluid communication with the thermal fuel line for direct thermal communication with the fuel.

4. The system of claim 3 , wherein the at least one internal fuel channel is in fluid communication with a fuel tank of the aircraft.

5. The system of claim 1 , wherein in the case of indirect thermal communication, further comprising the fuel/fluid heat exchanger in fluid communication with the thermal fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

6. The system of claim 5 , wherein the fluid is air.

7. The system of claim 5 , wherein the fuel/fluid heat exchanger is in fluid communication with a fuel tank of the aircraft.

8. The system of claim 5 , wherein the fluid is in direct thermal communication with the exposed aircraft structure.

9. The system of claim 8 , wherein the exposed aircraft structure includes at least one internal fluid channel in fluid communication with the fuel/fluid heat exchanger for receiving the fluid from the fuel/fluid heat exchanger.

10. The system of claim 9 , wherein the at least one internal fluid channel is in fluid communication with an exhaust to exhaust air after passing through the exposed aircraft structure.

11. The system of claim 9 , wherein the at least one internal fluid channel includes a heat exchanger loop such that fluid loops back to the heat exchanger after passing through the exposed aircraft structure which cools the fluid for accepting more heat from the heat exchanger.

12. A method for heating an exposed aircraft structure and/or cooling fuel using an aircraft fuel system, comprising:
a main fuel line configured to transport fuel to an engine;
a fuel pump disposed on the main fuel line;
a pump return fuel line connected to the main fuel line to take a portion of the fuel from the main fuel line at a position downstream of the fuel pump and to return the portion of the fuel to the main fuel line at a position upstream of the fuel pump;
an exposed aircraft structure in direct or indirect thermal communication with the fuel to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure; and
a thermal fuel line that either:
runs from the pump return fuel line to the exposed aircraft structure in the case of direct thermal communication, or
runs from the pump return fuel line to a fuel/fluid heat exchanger which is in thermal communication with the exposed aircraft structure in the case indirect thermal communication,

wherein the method comprises: thermally communicating a hot fuel in the thermal fuel line with the exposed aircraft structure to heat the exposed aircraft structure to deice or prevent ice formation on the exposed aircraft structure.

13. The method of claim 12 , wherein, in the case of direct thermal communication, the exposed aircraft structure is a deicing structure, wherein thermally communicating includes flowing the hot fuel into at least one internal fuel channel of the aircraft structure thereby directly thermally communicating the hot fuel with the exposed aircraft structure.

14. The method of claim 12 , wherein, in the case of indirect thermal communication, the exposed aircraft structure is a deicing aircraft structure, wherein thermally communicating includes flowing the hot fuel to the fuel/fluid heat exchanger to transfer heat from the hot fuel to a fluid, wherein thermally communicating includes flowing the fluid to the exposed aircraft structure to indirectly thermally communicate the hot fuel to the exposed aircraft structure.

15. The method of claim 12 , further comprising flowing the hot fuel to a fuel tank after thermally communicating the hot fuel with the exposed aircraft structure.

16. The method of claim 12 , further comprising controlling a valve to allow, prevent, or meter the hot fuel in thermal communication with the exposed aircraft structure.

17. The method of claim 16 , wherein controlling the valve includes opening the valve to allow the hot fuel to be in thermal communication with the exposed aircraft structure at a cruise or descent power setting.

18. The method of claim 17 , wherein controlling the valve can include opening the valve to allow a flow of the hot fuel at a threshold fuel temperature.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Cocks Peter A T

Classifications

• F02C7/232

  Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) · CPC title

• F02C7/14 Primary

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

• F02C7/047

  Heating to prevent icing · CPC title

• B64D15/02

  by ducted hot gas or liquid · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title