Combined fluid ice protection and electronic cooling system

Patent metadata

Field	Value
Publication number	US-10696412-B2
Application number	US-201715720938-A
Country	US
Kind code	B2
Filing date	Sep 29, 2017
Priority date	Sep 29, 2017
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A method and apparatus combining an aircraft wing and engine ice protection system with an aircraft electronic cooling system.

First claim

What is claimed is:

1. An ice protection system for an aerodynamic surface of an aircraft, the ice protection system comprising:
a reservoir;
an electronics cooling system connected to the reservoir and comprising a first conduit, wherein:
the electronics cooling system distributes coolant from the reservoir through the first conduit in thermal contact with electronics, whereby
heat is transferred from the electronics to the coolant;

a pump operatively coupled to the reservoir; and
a second conduit in communication with the pump and including an outlet disposed at the aerodynamic surface located on an outside of the aircraft, wherein the pump pumps the coolant onto the aerodynamic surface and the coolant reduces or prevents ice formation on the aerodynamic surface.

2. The ice protection system of claim 1 , further comprising a porous panel on the aerodynamic surface and including the outlet, wherein the coolant leaks out of the porous panel onto the aerodynamic surface.

3. The ice protection system of claim 2 , wherein the porous panel is attached to a slat, a wing, a propeller, a cockpit window, or an engine inlet.

4. The ice protection system of claim 1 , wherein the electronics comprises an air conditioning unit and the coolant mixes with water on the aerodynamic surface and suppresses a freezing point of the water.

5. The ice protection system of claim 4 , wherein the water comprises super cooled liquid droplets.

6. The ice protection system of claim 4 , wherein the water comprises the water encountered in an icing envelope as defined in FAR 24 Appendix C or FAR 24 Appendix O.

7. The ice protection system of claim 1 , wherein the electronics comprises an air conditioning unit and the coolant includes an ice-protection fluid comprising propylene glycol and a thinner.

8. The ice protection system of claim 1 , further comprising a connector connecting the first conduit to the second conduit downstream of the electronics, wherein the coolant pumped to the aerodynamic surface comprises at least a portion of the heat transferred from the electronics including an air conditioning unit.

9. The ice protection system of claim 1 , wherein the first conduit and the second conduit comprise flex hoses or plastic tubing.

10. The ice protection system of claim 1 , further comprising a plurality of reservoirs storing the coolant, wherein at least one of reservoirs has a coolant capacity of least 20 gallons (about 75.7 liters) to replenish the coolant pumped onto the aerodynamic surface.

11. The ice protection system of claim 1 , further including a fluid level sensor connected to the reservoir, the fluid level sensor measuring the coolant level in the reservoir and sending an alert when the coolant level of the coolant falls below a threshold level due to pumping of the coolant onto the aerodynamic surface.

12. The ice protection system of claim 1 , further comprising a service port for connection to ground service equipment, wherein the coolant in the reservoir is replenished through the service port.

13. The ice protection system of claim 1 , wherein:
the electronics comprises a motor controller controlling a radiator or an air conditioning unit, or the motor controller and the air conditioning unit, and
the coolant distributed to the aerodynamic surface comprises at least a portion of the heat transferred from the air conditioning unit, the motor controller, or the motor controller and the air conditioning unit.

14. An aircraft 202 comprising the ice protection system of claim 1 .

15. A method of manufacturing, refitting, or servicing an aircraft, comprising:
mounting an electronics cooling apparatus distributing coolant for cooling electronics comprising an air conditioning unit on an aircraft; and
mounting an ice protection apparatus on the aircraft and connecting the ice protection apparatus to the electronics cooling apparatus, wherein the ice protection apparatus receives the coolant from the electronics cooling apparatus and distributes the coolant onto the aerodynamic surface outside of the aircraft, the coolant reducing and removing ice formation on the aerodynamic surface of the aircraft, wherein the coolant distributed to the aerodynamic surface comprises at least a portion of heat transferred from the air conditioning unit.

16. The method of claim 15 , wherein the electronics cooling apparatus comprises a reservoir and a first conduit and the ice-protection apparatus further comprises a second conduit, the method further comprising:
connecting the first conduit to the reservoir and thermally contacting the first conduit to the electronics on the aircraft, wherein the heat dissipates from the electronics when the coolant from the reservoir flows through the first conduit in thermal contact with the electronics; and
connecting the second conduit to the first conduit or the reservoir using a connector, wherein the connector diverts at least a portion of the coolant to the second conduit distributing the portion of the coolant to an outlet on the aerodynamic surface.

17. The method of claim 16 , further comprising:
positioning the connector on the first conduit downstream of the electronics, such that the coolant on the aerodynamic surface comprises the at least a portion of the heat transferred from the electronic including the air conditioning unit.

18. The method of claim 15 , wherein the ice-protection apparatus includes a porous panel and the coolant flows from the porous panel onto the aerodynamic surface on a tail or wing of the aircraft.

19. The method of claim 15 , further comprising
replenishing the coolant in a reservoir through a service port connected to the reservoir;
mounting a generator having lower power output, as compared to the generator on the aircraft without the ice protection apparatus; and
mounting a turbofan engine having a smaller fuel consumption, as compared to the turbofan engine on the aircraft without the ice protection apparatus.

20. A method of operating an aircraft, comprising:
providing an aircraft comprising an ice protection system, the ice protection system comprising
a reservoir;
an electronics cooling system connected to the reservoir and comprising a first conduit, wherein:
the electronics cooling system distributes coolant from the reservoir through the first conduit in thermal contact with electronics, whereby
heat is transferred from the electronics to the coolant;

a pump operatively coupled to the reservoir; and
a second conduit in communication with the pump and including an outlet disposed at an aerodynamic surface located on an outside of the aircraft, wherein the pump pumps the coolant onto the aerodynamic surface and the coolant reduces or prevents ice formation on the aerodynamic surface;
providing instructions allowing higher thrust for the aircraft in icing conditions, as compared to the aircraft without the ice protection system; and
providing instructions allowing an operation of the ice protection system while the aircraft is parked.

Assignees

• Boeing Co

Inventors

• Mackin Steve G

Classifications

• B64D15/02

  by ducted hot gas or liquid · CPC title

• B64D15/00

  De-icing or preventing icing on exterior surfaces of aircraft · CPC title

• B64D2013/0614

  with subsystems for cooling avionics · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D15/08 Primary

  exuded from surface · CPC title