Mast main bearing lubrication and thermal management

• US 8,915,465 B1
• Filed: 09/07/2011
• Issued: 12/23/2014
• Est. Priority Date: 09/09/2010
• Status: Active Grant

• Current Assignee: Skyworks Global Inc.
• Original Assignee: Groen Brothers Aviation Inc.
• Inventors: van der Westhuizen, Jacob Johannes
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US13/199,721
• Time in Patent Office: 1,203 Days
• Field of Search: 244/6, 244/7.R, 244/7.A, 244/7.C, 244/12.4, 244/17.11, 244/17.25, 384/397, 384/398, 384/412, 384/462, 384/474, 384/606, 415/180, 184/6.12, 184/6.22, 184/7.1
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/58 Transmitting means, e.g. interrelated with initiating means or means acting on blades means acting on blades B64C27/72
• CPC Class Codes: B64C 27/625 including rotating masses or servo rotors
• CPC Class Codes: F01M 11/02 Arrangements of lubricant conduits
• CPC Class Codes: F01M 2001/0253 characterised by the pump driving means
• CPC Class Codes: F01M 5/005 Controlling temperature of lubricant

Abstract

A rotor system is disclosed for a reactive drive rotary wing aircraft. Rigidity of the rotor is enhanced and play between flight controls and the rotor are eliminated by mounting swashplate actuators to a flange rigidly secured to the mast. Thermal management of the rotor is performed in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. Thermal management of a rotor may be performed by oil and air flow.

Claims

1. A rotor system for a rotary wing aircraft the rotor system comprising:

a mast secured to an airframe;

a rotor hub rotatably mounted to the mast;

a bearing interposed between the mast and hub, the bearing comprising rolling elements;

a feed oil line and a return oil line in fluid communication with the bearing; and

a pump positioned to move a fluid in a closed fluid path between the feed oil line and return oil line

a thermal modulator positioned in thermal contact with fluid within the closed fluid path;

at least one valve within the closed fluid path; and

a control system operably coupled to the valve and thermal modulator and configured to activate one or both of the pump and thermal modulator;

the bearing, wherein the rolling elements have a preloaded condition within an operating temperature range; and

the control system, further programmed to activate the thermal modulator to be effective to maintain the preloaded condition of the rolling elements.

2. The rotor system of claim 1, further comprising a thermal sensor in thermal contact with the fluid within the closed fluid path and having an output electrically coupled to the control system, the control system programmed to maintain the temperature of the rolling elements within the operating temperature range according to an output of the thermal sensor.

3. The rotor system of claim 1, wherein the thermal modulator comprises one or more of a heating element and a cooling element.

4. The rotor system of claim 1, wherein the hub defines a bearing seat and wherein the bearing is positioned within the bearing seat, the bearing seat comprising a plurality of oil channels forming a plurality of fluid paths around the bearing.

5. The rotor system of claim 1, wherein the bearing comprises upper and lower bearings and wherein the hub and mast define a fluid path extending between the upper and lower bearings.

6. The rotor system of claim 5, wherein the hub defines a return channel extending between a return port and one of the upper bearing and the lower bearing;

wherein the hub defines a feed channel extending between a feed port and the other of the upper bearing and the lower bearing; and

wherein the feed oil line is coupled to the feed channel and the return oil line is coupled to the return channel.

7. The rotor system of claim 1, wherein the return and feed oil lines are coupled to a rotating portion of a hydraulic rotary union.

8. The rotor system of claim 7, wherein the hydraulic rotary union is positioned within the mast.

9. The rotor system of claim 1, further comprising a first seal positioned to restrict leakage of oil from between the hub and mast.

10. The rotor system of claim 9, further comprising a second seal positioned to restrict leakage of oil from between the hub and mast.

11. The rotor system of claim 9, further comprising:

a compressed air source;

a shroud surrounding the mast, the mast and shroud defining an air channel coupling the compressed air source to the rotor hub;

a mast fairing encircling the mast, the mast fairing having a contour effective to reduce pressure losses of air flowing through the air channel; and

a mounting ring secured to the hub and mast fairing, the first seal and a second seals being captured between the mounting ring and the mast.

12. The rotor system of claim 1, further comprising:

a compressed air source;

an air channel extending between the compressed air source and the rotor hub and defined one of

between a shroud surrounding the mast and the mast, and

by an inner surface of the mast;

the compressed air source, further configured to generate compressed air having a temperature within the operating temperature range; and

wherein the compressed air source is selectively couplable to the air channel upon take off, landing, and hover of an aircraft to which the rotor system is mounted.

13. A method for operating a rotary wing aircraft comprising:

receiving oil from a return oil line and pumping oil to a feed oil line, the feed oil line and return oil line being in fluid communication with a bearing, the bearing being interposed between a mast and a rotor hub, the mast being mounted to an aircraft fuselage and the rotor hub having a plurality of rotor blades secured thereto, the bearing comprising a plurality of rolling elements having a preloaded condition within an operating temperature range; and

modulating a temperature of the oil effective to maintain the plurality of rolling elements in the preloaded condition.

14. The method of claim 13, further comprising:

transmitting compressed air through an air channel into a cavity defined by the rotor hub, the blades defining ducts in fluid communication with the cavity, the air channel defined by the mast and a shroud surrounding the mast, the compressed air having a temperature within the operating temperature range; and

igniting tip jets secured to the blades and in fluid communication with the ducts during at least one of takeoff and landing.

15. The method of claim 14, further comprising:

impelling the airframe forward in sustained longitudinal flight through air having a temperature lower than the operating temperature range; and

the modulating the temperature of the oil effective to maintain the plurality of rolling elements in the preloaded condition comprises heating the oil during sustained longitudinal flight through air having a temperature lower than the operating temperature range.

16. A rotor assembly for a rotary wing aircraft comprising:

a mast adapted to secure to an airframe of the aircraft;

a rotor hub rotatably mounted to the mast;

a bearing interposed between the mast and hub, the bearing comprising rolling elements having a preload within an operating temperature range;

a feed oil port and a return oil port in fluid communication with the bearing;

a first seal positioned to resist leakage of oil from between the hub and mast;

a second seal positioned to resist leakage of oil from between the hub and mast;

a shroud surrounding the mast, the mast and shroud defining an air channel;

a mast fairing encircling the mast, the mast fairing having a contour effective to reduce pressure losses of air flowing within the air channel; and

a mounting ring secured to the hub and mast fairing, the first and second seals being captured between the mounting ring and the mast.

17. The rotor assembly of claim 16, wherein the hub defines a bearing seat, and the bearing is positioned within the bearing seat, and the bearing seat further comprises a plurality of oil channels forming a plurality of fluid paths around the bearing.

18. The rotor assembly of claim 16, wherein the bearing comprises upper and lower bearings and wherein the hub and mast define a fluid path extending between the upper and lower bearings.

19. The rotor assembly of claim 18, wherein the feed oil port and a return oil port are secured to the hub;

and

wherein a feed oil passage extends through the hub from the feed oil port to adjacent one of the upper bearing and the lower bearing; and

wherein a return oil passage extends through the hub from the return oil port to adjacent the other of the upper bearing and the lower bearing.

20. The rotor assembly of claim 16, further comprising:

a hydraulic rotary union comprising a rotating portion and a non-rotating portion;

a feed oil line coupled to the rotating portion of the hydraulic rotary union and the feed oil port; and

a return oil line coupled to the rotating portion of the hydraulic rotary union and the return oil port.

21. The rotor assembly of claim 20, wherein the hydraulic rotary union is positioned within the mast.