Active cooling system for landing gear brakes

Patent metadata

Field	Value
Publication number	US-11466742-B2
Application number	US-202016777232-A
Country	US
Kind code	B2
Filing date	Jan 30, 2020
Priority date	Jan 30, 2020
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

A brake assembly for landing gear of an aircraft includes a caliper member and a carrier member. The caliper member includes a gas inlet configured to receive a cooling gas supplied by an on board fuel inerting gas supply system of the aircraft, and a manifold fluidly coupled to the gas inlet. The manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member. The carrier member is configured to be coupled to the caliper member. The carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors. The cylindrical section defines one or more interior passages configured to fluidly couple the outlet ports of the caliper member to one or more outlet ports of the cylindrical section. The outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate forced convective cooling of the stacked arrangement of stators and rotors with the cooling gas supplied by the on board fuel inerting gas supply system.

First claim

What is claimed is:

1. A brake assembly for landing gear of an aircraft, the brake assembly comprising:
a caliper member that includes:
a gas inlet configured to receive a cooling gas from an on-board fuel inerting gas supply system of the aircraft; and
a manifold fluidly coupled to the gas inlet, wherein the manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member; and

a carrier member configured to be coupled to the caliper member, wherein the carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors, wherein the cylindrical section defines one or more interior passages configured to fluidly couple the one or more outlet ports of the caliper member to one or more outlet ports of the cylindrical section, wherein the one or more outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate cooling the stacked arrangement of stators and rotors with the cooling gas.

2. The brake assembly according to claim 1 , wherein the caliper member defines a central opening for receiving an axle of the landing gear, wherein the manifold includes an interior passage that extends coaxially about the central opening.

3. The brake assembly according to claim 1 , wherein the one or more interior passages extend longitudinally through the cylindrical section from the one or more outlet ports of the manifold of the caliper member towards a backing plate of the carrier member.

4. The brake assembly according to claim 1 , wherein a diameter of the one or more interior passages is between 0.12 inches and 0.25 inches.

5. The brake assembly according to claim 1 , wherein at least one interior passage of the one or more interior passages of the carrier member includes a plurality of outlet ports, wherein the outlet ports of the plurality are distributed along a length of the at least one interior passage at positions proximate the rotors of the stacked arrangement of stators and rotors to facilitate cooling gas flow over each rotor of the stacked arrangement of stators and rotors.

6. The brake assembly according to claim 5 , wherein a number of outlet ports of the at least one interior passage corresponds to a number of rotors of the stacked arrangement of stators and rotors.

7. The brake assembly according to claim 1 , wherein the cooling gas is an inert gas.

8. A braking system for an aircraft, the braking system comprising:
a supply line fluidly coupled to an on-board inert gas generation system;
a brake assembly for landing gear of the aircraft fluidly coupled to the supply line, wherein the brake assembly is configured to be cooled by inert gas communicated via the supply line from the on-board inert gas generation system;
a pump downstream of and in fluid communication with the on-board inert gas generation system, wherein the pump is configured to pressurize the inert gas; and
an accumulator downstream of the pump, wherein the accumulator is configured to store pressurized inert gas.

9. The braking system according to claim 8 , wherein the pump is configured to pressurize the inert gas to between 0.0 psig and 2200 psig above ambient pressure.

10. The braking system according to claim 8 , wherein the accumulator is configured to store between 10 and 18 liters of pressurized inert gas.

11. The braking system according to claim 8 , further comprising a control valve downstream of the accumulator to control a flow of cooling gas to the brake assembly.

12. The braking system according to claim 11 , wherein when the control valve is open, cooling gas flows to the brake assembly at a rate of between 30 CFM to 35 CFM for at least 6 minutes at 3 psig above ambient.

13. The braking system according to claim 12 , wherein the control valve is controlled to open when the landing gear is deployed and the control valve is controlled to close when the landing gear is retracted.

14. The braking system according to claim 8 , wherein the brake assembly comprises:
a caliper member that includes:
a gas inlet configured to couple to the supply line; and
a manifold fluidly coupled to the gas inlet, wherein the manifold is configured to distribute the inert gas to one or more outlet ports of the caliper member; and

a carrier member configured to be coupled to the caliper member, wherein the carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors, wherein the cylindrical section defines one or more interior passages configured to fluidly couple the one or more outlet ports of the caliper member to one or more outlet ports of the cylindrical section, wherein the one or more outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate cooling the stacked arrangement of stators and rotors with the inert gas.

15. The braking system according to claim 14 , wherein the caliper member defines a central opening for receiving an axle of the landing gear, wherein the manifold includes an interior passage that extends coaxially about the central opening.

16. A method for lowering a temperature of a brake assembly of landing gear of an aircraft, the method comprising:
measuring a temperature of the brake assembly of the aircraft;
responsive to the temperature being above an upper threshold, opening a control valve to allow inert gas from an on-board fuel inerting gas supply system of the aircraft to flow to the brake assembly;
responsive to the temperature being at or below a lower temperature threshold, closing the control valve to cease the flow of the inert gas to the brake assembly;
pressurizing, by a pump downstream of and in fluid communication with the on-board fuel inerting gas supply system, the inert gas; and
storing pressurized inert gas in an accumulator downstream of the pump.

17. The method according to claim 16 , further comprising:
opening a valve that is downstream of the accumulator and configured to control a flow of the inert gas to the brake assembly to allow the inert gas to flow to the brake assembly when the landing gear of the aircraft is deployed; and
closing the valve to prevent the flow of the inert gas to the brake assembly when the landing gear of the aircraft is retracted.

18. The method according to claim 17 , wherein opening the valve further comprises communicating the inert gas to the brake assembly at a rate of between 30 CFM to 35 CFM for at least 6 minutes at 3 psig above ambient.

19. The method according to claim 16 , further comprising:
receiving the inert gas at a gas inlet of a caliper member;
distributing, by a manifold fluidly coupled to the gas inlet, the inert gas to one or more outlet ports of the caliper member; and
distributing, by a carrier member coupled to the caliper member, the inert gas to one or more outlet ports of a cylindrical section of the carrier member, wherein the cylindrical section is configured to receive a stacked arrangement of stators and rotors, wherein the cylindrical section defines one or more interior passages configured to fluidly couple the one or more outlet ports of the caliper member to the one or more outlet ports of the cylindrical section, wherein the one or more outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate cooling the stacked arrangement of stators and rotors with the inert gas.

20. The method according to claim 19 ,

Assignees

• Boeing Co

Inventors

• Kirkbride David W

Classifications

• F16D2065/787

  Pumps · CPC title

• F16D2065/786

  Fluid spray devices · CPC title

• F16D55/36

  Brakes with a plurality of rotating discs all lying side by side · CPC title

• B64C25/44

  Actuating mechanisms · CPC title

• F16D65/853 Primary

  with closed cooling system · CPC title