Aircraft gaseous cooling system

• US 10,578,207 B2
• Filed: 07/24/2014
• Issued: 03/03/2020
• 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
• Primary Examiner(s): Kim, Craig
• Application Number:
  US14/340,340
• Publication Number:
  US 20160025206A1
• Time in Patent Office: 2,049 Days
• 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 rotorcraft cooling system comprising:

a compressor connected to a rotorcraft gearbox to be cooled, the rotorcraft gearbox comprising a housing that encloses a subcomponent of the rotorcraft gearbox, the compressor to continuously supply a compressed gas to the housing of the rotorcraft gearbox in response to a first input;

two or more detection sensors coupled to the rotorcraft gearbox comprising a pressure sensor and a temperature sensor;

a controller connected to the compressor and the two or more detection sensors, the controller to provide the first input to the compressor to generate the compressed gas and continuously supply the compressed gas to the housing of the rotorcraft gearbox in response to the controller determining a failure of a lubrication system of the rotorcraft gearbox via the two or more detection sensors;

an inlet valve coupled between the compressor and the housing of the rotorcraft gearbox, the inlet valve connected to the controller and configured to selectively introduce the compressed gas into the rotorcraft gearbox in response to a second input from the controller;

a vent valve coupled to the housing of the rotorcraft gearbox and connected to the controller, the vent valve configured to selectively vent the compressed gas from the rotorcraft gearbox to an atmosphere in response to a third input from the controller; and

the controller is configured to monitor a pressure in the rotorcraft gearbox sensed by the pressure sensor, monitor a temperature in the rotorcraft gearbox sensed by the temperature sensor, and in response to determining the failure of the lubrication system control a rate at which the compressed gas is transferred from the compressor to the rotorcraft gearbox by selectively controlling the compressor, the inlet valve and the vent valve to reach and maintain a desired pressure in the rotorcraft gearbox by;

(a) in response to determining that the pressure in the rotorcraft gearbox is greater than a threshold pressure, providing the first input to the compressor to stop supplying the compressed gas to the rotorcraft gearbox and/or the second input to the inlet valve to close the inlet valve, or the third input to the vent valve to open the vent valve, and (b) in response to determining that the temperature in the rotorcraft gearbox exceeds a threshold temperature, providing the third input to the vent valve to open the vent valve, and the second input to the inlet valve to open the inlet valve and/or the first input to the compressor to supply the compressed gas to the rotorcraft gearbox.

2. The system of claim 1, wherein the compressed gas has a heat transfer coefficient to transfer heat from the rotorcraft gearbox to atmosphere.

3. The system of claim 2, wherein the compressed gas comprises at least one of helium, air, or argon.

4. The system of claim 1, wherein the controller is configured to provide the first input to the compressor in response to determining the failure of the lubrication system in the rotorcraft gearbox.

5. The system of claim 4, wherein the two or more detection sensors detect the failure of the lubrication system in the rotorcraft gearbox, and provide a notification of the failure of the lubrication system to the controller.

6. The system of claim 5, wherein the pressure sensor detects the failure of the lubrication system in response to the pressure in the rotorcraft gearbox being less than a threshold pressure.

7. The system of claim 5, wherein the temperature sensor detects the failure of the lubrication system in response to the temperature in the rotorcraft gearbox being greater than a threshold temperature.

8. The system of claim 5, wherein the two or more detection sensors further comprise a lubrication quantity sensor to detect the failure of the lubrication system in response to a lubricant quantity in the rotorcraft gearbox being less than a threshold lubricant quantity.

9. The system of claim 1, further comprising:

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

wherein the inlet valve is positioned in the gas line to permit or stop flow of the compressed gas to the rotorcraft gearbox in response to the second input from the controller.

10. The system of claim 1, wherein the pressure sensor monitors the pressure in the rotorcraft gearbox in response to the compressed gas being flowed to the rotorcraft component from the compressor.

11. The system of claim 1, wherein the rotorcraft gearbox is connected to a rotary shaft, and wherein the compressor is connected to the rotary shaft to receive power to generate the compressed gas.

12. A method comprising:

determining that a lubrication system of a gearbox has failed using a controller coupled to two or more detection sensors comprising a pressure sensor and a temperature sensor coupled to the gearbox;

continuously supplying a compressed gas to the gearbox in response to determining that the lubrication system has failed by the controller using a compressor and an inlet valve coupled between the compressor and the gearbox;

compressing a gas supplied by a gas container or an atmospheric air using a compressor;

operating an inlet valve positioned in a gas line connecting the compressor to the gearbox to transport the compressed gas generated by the compressor through the gas line to the gearbox;

operating a vent valve connected to the gearbox to selectively vent the compressed gas out of the gearbox to atmosphere through the vent valve in response to the controller; and

the controller is configured to monitor a pressure in the gearbox sensed by the pressure sensor, monitor a temperature in the gearbox sensed by the temperature sensor, and in response to determining that the lubrication system has failed control a rate at which the compressed gas is transferred from the compressor to the gearbox by selectively controlling the compressor, the inlet valve and the vent valve to reach and maintain a desired pressure in the gearbox by;

(a) in response to determining that the pressure in the gearbox is greater than a threshold pressure, operating the compressor to stop supplying the compressed gas to the gearbox and/or the inlet valve to close the inlet valve, or the vent valve to open the vent valve, and (b) in response to determining that the temperature in the gearbox exceeds a threshold temperature, operating the vent valve to open the vent valve, and the inlet valve to open the inlet valve and/or to the compressor to supply the compressed gas to the gearbox.

13. The method of claim 12, 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.

14. A cooling system comprising:

a rotorcraft gearbox comprising a housing enclosing a subcomponent within the housing;

a controller connected to two or more detection sensors comprising a pressure sensor and a temperature sensor coupled to the rotorcraft gearbox;

a compressor connected to the controller, the compressor to continuously supply compressed gas to the rotorcraft gearbox in response to a first input from the controller determining a failure of a lubrication system of the rotorcraft gearbox via the two or more detection sensors;

a gas line connecting the compressor to the rotorcraft gearbox connecting the compressor to the rotorcraft gearbox;

an inlet valve positioned in the gas line and coupled between the compressor and the housing of the rotorcraft gearbox, the inlet valve connected to the controller and configured to selectively introduce the compressed gas into the rotorcraft gearbox in response to a second input from the controller;

a vent valve coupled to the housing of the rotorcraft gearbox and connected to the controller, the vent valve configured to selectively vent the compressed gas from the rotorcraft gearbox to an atmosphere in response to a third input from the controller; and

the controller is configured to monitor a pressure in the rotorcraft gearbox sensed by the pressure sensor, monitor a temperature in the rotorcraft gearbox sensed by the temperature sensor, and in response to determining the failure of the lubrication system control a rate at which the compressed gas is transferred from the compressor to the rotorcraft gearbox by selectively controlling the compressor, the inlet valve and the vent valve to reach and maintain a desired pressure in the rotorcraft gearbox by;

(a) in response to determining that the pressure in the rotorcraft gearbox is greater than a threshold pressure, providing the first input to the compressor to stop supplying the compressed gas to the rotorcraft gearbox and/or the second input to the inlet valve to close the inlet valve, or the third input to the vent valve to open the vent valve, and (b) in response to determining that the temperature in the rotorcraft gearbox exceeds a threshold temperature, providing the third input to the vent valve to open the vent valve, and the second input to the inlet valve to open the inlet valve and/or the first input to the compressor to supply the compressed gas to the rotorcraft gearbox.