Fuel recirculation system

Patent metadata

Field	Value
Publication number	US-11623759-B2
Application number	US-201916669868-A
Country	US
Kind code	B2
Filing date	Oct 31, 2019
Priority date	Jul 19, 2019
Publication date	Apr 11, 2023
Grant date	Apr 11, 2023

Abstract

Disclosed are systems and methods for maintaining bulk fuel temperatures in an aircraft. In one aspect, a recirculation system causes fuel to be delivered from a relatively low point near the feed hopper of each tank on the aircraft to one or more outboard locations of the wings. Once there, the fuel, due to gravity, flows back over the lower skin of the wing in channels back towards the fuselage, thus cooling the fuel. In other aspects, control systems are disclosed that coordinate the recirculation based on fuel levels in the tanks and fuel temperatures. The control systems also utilize a fuel scavenge system to maintain acceptable temperatures in the tanks.

First claim

What is claimed is:

1. A fuel system for an aircraft, the fuel system comprising:
a fuel-temperature-control system for maintaining fuel temperatures in the fuel system, the fuel temperature-control system including a controller;
a temperature-reading device located in the fuel system;
a circulation-flow delivery subsystem, the circulation-flow delivery subsystem delivering fuel to a plurality of heat dissipating channels at an outboard section of an aircraft wing via a plurality of delivery conduits, wherein each heat dissipating channel of the plurality of heat dissipating channels is paired with a fuel outlet on each delivery conduit in the plurality of delivery conduits to deliver fuel to each heat dissipating channel, wherein the plurality of heat dissipating channels exchange heat through an aircraft skin into an environment outside the aircraft wing;
a return arrangement returning fuel from the plurality of heat dissipating channels;
the controller being configured to activate the circulation-flow delivery subsystem upon a detection of a first reading made by the temperature-reading device, the first reading being reflective of a first fuel temperature which is either greater than or equal to a predetermined temperature maximum, the predetermined temperature maximum reflecting a fuel-cooling need.

2. The fuel system of claim 1 wherein the controller is further configured to deactivate the circulation-flow delivery subsystem upon detection of a second reading made by the temperature-reading device, the second reading reflecting a second temperature which is either less than or equal to a predetermined temperature minimum, the predetermined temperature minimum being reflective of a fuel-warming need.

3. The fuel system of claim 1 comprising:
a scavenge system, the scavenge system adapted to direct fuel from one or more low points in a fuel vessel in the fuel system to a feed hopper;
a level-reading device in the fuel vessel;
the controller being further configured to bring the scavenge system from an inactive state to an active state upon detection that a fuel level is either equal to or has fallen below a predetermined minimum level.

4. The fuel system of claim 1 comprising:
the controller being configured to, when an engine is operating, determine whether a boost pump is operating as a primary source of fuel for the engine, and if the boost pump is operational, turning off either or both of a scavenge system or the circulation-flow delivery device if either or both are on.

5. The fuel system of claim 1 wherein the circulation-flow delivery subsystem includes a pump.

6. The fuel system of claim 5 wherein the pump is dedicated to the delivery of fuel to the plurality of heat dissipating channels.

7. The fuel system of claim 1 including a junction where motive flow from an engine is made to be combinable with the fuel being delivered to the plurality of heat dissipating channels, the fuel system further comprising:
a modulation process operating on the controller, the modulation process, upon a plurality of subsequent fuel temperature readings, increasing a flow of the fuel being delivered to the plurality of heat dissipating channels relative to an amount of motive flow upon elevated temperature detections.

8. The fuel system of claim 7 wherein the modulation process, upon low temperature detections, decreases the flow of the fuel being delivered to the plurality of heat dissipating channels relative to the amount of motive flow.

9. The fuel system of claim 1 wherein the aircraft skin is located on an underside of an aircraft wing.

10. The fuel system of claim 9 wherein the aircraft skin located on the underside of the aircraft wing defines internal surfaces of a fuel tank.

11. The system of claim 10 wherein the circulation-flow delivery subsystem includes a fuel conduit that runs from an inboard location in the fuel tank and delivers the fuel to the outboard location inside the fuel tank, the inboard location in the tank being lower than the outboard location.

12. The system of claim 11 wherein the fuel flows back towards the inboard location under an influence of gravity.

13. The system of claim 12 wherein the fuel flows back towards the inboard location through at least one channel being at least partially defined by longitudinally-extending structural configurations rising from a lower skin of the wing.

14. A method for maintaining temperatures in an aircraft, the aircraft having symmetrical fuel tanks, each tank being defined by an internal surface of a wing, the method comprising:
on detection of a fuel temperature which needs to be cooled to a lower temperature, circulating fuel from an inboard region in each fuel tank to a plurality of heat dissipating channels located at an outer region in each fuel tank such that the fuel flows back to the inboard region under an influence of gravity from the outer region, a lower portion of each wing serving to dissipate heat from the fuel being circulated,
wherein each heat dissipating channel of the plurality of heat dissipating channels is paired with one fuel outlet to deliver fuel to the heat dissipating channel.

15. The method of claim 14 comprising:
maintaining a fuel scavenge system in an off state; and
activating the fuel scavenge system upon the detection of a fuel level in a wing fuel tank falling below a preselected minimum.

16. A control process for maintaining acceptable fuel temperatures in a fuel system, the fuel system including a scavenging system, the scavenging system when subjected to motive flow from an engine (i) operating at least one extraction pump; and (ii) returning the motive fuel to a fuel tank, the control process comprising:
beginning with motive flow to the scavenging system turned off;
continually reading a fuel level and a fuel temperature in the fuel tank; and
activating the scavenge system by opening up motive flow to a conduit feeding the scavenge system upon receiving a first level indication reflecting the fuel level has reached or fallen below a predetermined minimum level, or upon receiving a temperature reading indicating that the fuel temperature has reached a predetermined minimum temperature,
transferring the motive flow from the fuel tank to a plurality of heat dissipating channels located at an outboard section of an aircraft wing,
wherein each channel of the plurality of heat dissipating channels is paired with one fuel outlet to deliver fuel to the heat dissipating channel,
maintaining fuel temperatures using the beginning and activating steps above.

17. The control process of claim 16 comprising:
deactivating the scavenge system by stopping motive flow upon the fuel level in the fuel tank rising back above the predetermined minimum level or some other predetermined level.

18. The control process of claim 17 comprising:
disposing a valve in the conduit feeding the scavenge system for executing the activating and deactivating steps.

19. The control process of claim 16 comprising:
executing the activating step even if the fuel level remains above the predetermined minimum level.

Assignees

• Textron Aviation Inc

Inventors

• Dwier Thomas Edward
• Wellemeyer Robert G

Classifications

• B64C3/14

  Aerofoil profile · CPC title

• B64C2003/143

  comprising interior channels · CPC title

• B64D37/04 Primary

  Arrangement thereof in or on aircraft · CPC title

• B64D37/34 Primary

  Conditioning fuel, e.g. heating (during filling B64D37/18) · CPC title

• Y02T50/40

  Weight reduction · CPC title