AIRCRAFT GASEOUS COOLING SYSTEM

• US 20160025206A1
• Filed: 07/24/2014
• Published: 01/28/2016
• Est. Priority Date: 07/24/2014
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Modrzejewski, Brian S., McGlaun, Monte, Jurell, Travis
• Granted Patent: US 10,578,207 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F16H 57/0412 Cooling or heating; Control of temperature
• CPC Class Codes: F16H 57/0416 Air cooling or ventilation
• CPC Class Codes: F16H 57/0442 for supply in case of failure, i.e. auxiliary supply

Abstract

One aspect of a cooling system includes a gas source connected to a component to be cooled. The gas source continuously supplies compressed gas to the component in response to an input. The cooling system also includes a controller connected to the gas source, the controller to provide the input to the gas source to continuously supply the compressed gas to the component.

Claims

1. A cooling system comprising:

a gas source connected to a component to be cooled, the gas source to continuously supply compressed gas to the component in response to an input; and

a controller connected to the gas source, the controller to provide the input to the gas source to continuously supply the compressed gas to the component.

2. The system of claim 1, wherein the gas source is a compressor that generates the compressed gas.

3. The system of claim 1, wherein the compressed gas has a heat transfer coefficient to transfer heat from the component to atmosphere.

4. The system of claim 3, wherein the compressed gas comprises at least one of helium, air, or argon.

5. The system of claim 1, wherein the controller is configured to provide the input to the gas source in response to determining a lubrication failure in the component.

6. The system of claim 5, further comprising a detection sensor to:

detect the lubrication failure in the component; and

provide a notification of the lubrication failure to the controller.

7. The system of claim 6, wherein the detection sensor comprises a pressure sensor to detect the lubrication failure in response to a pressure in the component being greater than a threshold pressure.

8. The system of claim 6, wherein the detection sensor comprises a temperature sensor to detect the lubrication failure in response to a temperature in the component being greater than a threshold temperature.

9. The system of claim 6, wherein the detection sensor comprises a lubrication quantity sensor to detect the lubrication failure in response to a lubricant quantity in the component being less than a threshold lubricant quantity.

10. The system of claim 1, further comprising a vent valve connected to the controller, the vent valve to vent the compressed gas from the component to atmosphere in response to input from the controller.

11. The system of claim 10, wherein the controller is configured to provide input to the vent valve based, in part, on a pressure in the component.

12. The system of claim 1, further comprising:

a gas line connecting the gas source to the component; and

an inlet valve positioned in the gas line and the controller, the inlet valve to permit flow of the compressed gas to the component in response to input from the controller.

13. The system of claim 1, further comprising a pressure sensor connected to the component and the controller, the pressure sensor to monitor a pressure in the component in response to the compressed gas being flowed to the component from the gas source.

14. The system of claim 13, wherein the controller is configured to:

monitor the pressure in the component sensed by the pressure sensor;

determine that the pressure in the component is greater than a threshold pressure; and

provide an input to the gas source to stop supplying compressed gas to the component.

15. The system of claim 1, wherein the component comprises a gearbox connected to a rotary shaft, and wherein the gas source is connected to the rotary shaft to receive power to generate the compressed gas.

16. A method comprising:

determining that a lubrication system of a gearbox has failed; and

continuously supplying compressed gas to the gearbox in response to determining that the lubrication system has failed.

17. The method of claim 16, wherein determining that the lubrication system has failed comprises determining that a gearbox temperature is greater than a threshold gearbox temperature or that a gearbox pressure is greater than a threshold gearbox pressure or that a gearbox lubricant quantity is less than a threshold gearbox lubricant quantity.

18. The method of claim 16, wherein continuously supplying compressed gas to the gearbox in response to determining that the lubrication system has failed comprises operating an inlet valve positioned in a gas line connecting a compressor to the gearbox to transport the compressed gas generated by the compressor through the gas line to the gearbox.

19. The method of claim 16, further comprising operating a vent valve connected to the gearbox to vent the compressed gas from the gearbox to atmosphere based, at least in part on, a pressure in the gearbox.

20. A cooling system comprising:

a controller connected to a rotorcraft component; and

a compressor connected to the controller and the rotorcraft component, the compressor to continuously supply compressed gas to the rotorcraft component in response to the controller determining a failure of a lubrication system of the rotorcraft component.