Method for the delivery of lubricant to a rotorcraft gearbox

Patent metadata

Field	Value
Publication number	US-9683652-B2
Application number	US-201514693334-A
Country	US
Kind code	B2
Filing date	Apr 22, 2015
Priority date	Apr 22, 2015
Publication date	Jun 20, 2017
Grant date	Jun 20, 2017

Abstract

A rotorcraft includes a body, a rotor blade, and a power train coupled to the body and operable to rotate the rotor blade. The power train includes an engine, a gearbox in mechanical communication with the engine, and a driveshaft in mechanical communication with the gearbox. The rotorcraft also includes a sensor operable to detect a rotorcraft parameter, and a lubrication flow calculation unit operable to receive the rotorcraft parameter, generate the flow rate based on the rotorcraft parameter, and transmit the flow rate to a lubrication system configured to deliver lubricant to the gearbox at the transmitted flow rate.

First claim

What is claimed is:

1. A rotorcraft, comprising:
a body;
a rotor blade;
a power train coupled to the body and operable to rotate the rotor blade, the power train comprising:
an engine;
a gearbox in mechanical communication with the engine; and
a driveshaft in mechanical communication with the gearbox;

a sensor operable to detect a rotorcraft parameter;
a main lubrication system configured to deliver lubricant to the gearbox, the main lubrication system comprising a main lubrication reservoir and a main pressurizing device;
a secondary lubrication system configured to deliver lubricant to the gearbox, the secondary lubrication system comprising a secondary lubrication reservoir and a secondary pressurizing device; and
a lubrication flow calculation unit operable to:
receive the rotorcraft parameter;
generate a flow rate based on the rotorcraft parameter, wherein the flow rate increases the amount of time that the rotorcraft can operate when the gearbox experiences a reduction in lubricant pressure; and
transmit the flow rate to the secondary lubrication system;

wherein one of the primary and secondary lubrication systems delivers lubricant to the gearbox at the generated flow rate.

2. The rotorcraft of claim 1 , wherein the lubrication flow calculation unit generates the flow rate by calculating the flow rate based on a ratio and the rotorcraft parameter.

3. The rotorcraft of claim 1 , wherein the lubrication flow calculation unit generates the flow rate by use of a look-up table, the look-up table having flow rate values for each corresponding rotorcraft parameter value.

4. The rotorcraft of claim 1 , wherein the sensor is a speed sensor configured to detect a rotational speed of the driveshaft, the rotorcraft parameter is the rotational speed of the driveshaft, and the flow rate is generated based on the rotational speed of the driveshaft such that as the rotational speed of the driveshaft reduces, the flow rate is reduced.

5. The rotorcraft of claim 1 , wherein the sensor is a pressure sensor configured to detect a lubricant pressure in the gearbox, and the rotorcraft parameter is the lubricant pressure in the gearbox.

6. The rotorcraft of claim 1 , wherein the sensor is a vibration sensor configured to detect a vibration in the gearbox, and the rotorcraft parameter is the vibration in the gearbox.

7. The rotorcraft of claim 1 , further comprising a second sensor operable to detect a second rotorcraft parameter, wherein the lubrication flow calculation is operable to:
receive the rotorcraft parameter and the second rotorcraft parameter;
generate the flow rate based on the rotorcraft parameter and the second rotorcraft parameter; and
transmit the flow rate to the lubrication system.

8. The rotorcraft of claim 7 , wherein the rotorcraft parameter is a rotational speed of the driveshaft, the second rotorcraft parameter is a temperature of the lubricant in the gearbox, and the flow rate is generated based on the rotational speed of the driveshaft and the temperature of the lubricant in the gearbox.

9. The rotorcraft of claim 1 , wherein the lubrication flow calculation unit transmits the flow rate when an oil pressure of the gearbox is less than a threshold value, and does not transmit the flow rate when the oil pressure of the gearbox is above the threshold value.

10. The rotorcraft of claim 9 , wherein the threshold value is thirty pounds per square inch.

11. The rotorcraft of claim 1 , wherein the secondary lubrication system delivers lubricant to the gearbox at the generated flow rate.

12. A method comprising:
providing a body;
providing a rotor blade;
providing a power train coupled to the body and operable to rotate the rotor blade, the power train comprising:
an engine;
a gearbox in mechanical communication with the engine; and
a driveshaft in mechanical communication with the gearbox;

providing a sensor operable to detect a rotorcraft parameter;
providing a main lubrication system configured to deliver lubricant to the gearbox, the main lubrication system comprising a main lubrication reservoir and a main pressurizing device;
providing a secondary lubrication system configured to deliver lubricant to the gearbox, the secondary lubrication system comprising a secondary lubrication reservoir and a secondary pressurizing device;
receiving the rotorcraft parameter from the sensor;
generating a flow rate based on the rotorcraft parameter, wherein the flow rate increases the amount of time that the rotorcraft can operate when the gearbox experiences a reduction in lubricant pressure; and
instructing one of the primary and secondary lubrication systems to deliver lubricant to the gearbox at the generated flow rate.

13. The method of claim 12 , wherein the sensor is a speed sensor configured to detect a rotational speed of the driveshaft, and the rotorcraft parameter is the rotational speed of the driveshaft.

14. The rotorcraft of claim 12 , wherein the sensor is a pressure sensor configured to detect a lubricant pressure in the gearbox, and the rotorcraft parameter is the lubricant pressure in the gearbox.

15. The method of claim 12 , wherein the sensor is a vibration sensor configured to detect a vibration in the gearbox, and the rotorcraft parameter is the vibration in the gearbox.

16. The method of claim 12 , further comprising:
providing a second sensor operable to detect a second rotorcraft parameter, wherein the step of generating the flow rate is based on the rotorcraft parameter and the second rotorcraft parameter.

17. The method of claim 16 , wherein the rotorcraft parameter is a speed of a mast of the rotorcraft, and the second rotorcraft parameter is a temperature of a gearbox component.

18. The method of claim 12 , wherein instructing a lubrication system to deliver lubricant to the gearbox at the generated flow rate occurs when an oil pressure of the gearbox is less than a threshold value, and the instructing step does not occur when the oil pressure of the gearbox is above the threshold value.

19. The method of claim 18 , wherein the threshold value is thirty pounds per square inch.

20. The method of claim 12 , wherein the instructing step includes instructing the secondary lubrication system to deliver lubricant to the gearbox at the generated flow rate.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Poster Scott

Classifications

• F16H57/0495

  with fixed gear ratio · CPC title

• F16H57/0434

  relating to lubrication supply, e.g. pumps; Pressure control · CPC title

• F16H57/04

  Features relating to lubrication or cooling {or heating} (control of lubrication or cooling in hydrostatic gearing F16H61/4165) · CPC title

• F16H57/0435 Primary

  Pressure control for supplying lubricant; Circuits or valves therefor · CPC title

• B64C27/12

  Rotor drives · CPC title