Granted Patent B1

US 9,073,631 · App. 13/199,678 · Granted Jul 7, 2015

Inventor: Jacob Johannes van der Westhuizen (South Jordan, UT)

Assignee: GROEN BROTHERS AVIATION, INC.

B64C27/32B64C27/025B64C27/18

Abstract

Claims (58)

1. A rotorcraft comprising:

an airframe;

at least one engine connected to the airframe;

a rotor connected to the airframe and defining axial and radial directions, the rotor comprising

a hub,

a rotor blade having a root and a tip and forming a conduit extending from the root to the tip, and

a feathering spindle connecting the rotor blade to the hub;

a flow of oil passing proximate the feathering spindle;

the flow of oil cooling the feathering spindle during take off and landing of the rotorcraft; and

the flow of oil heating the feathering spindle during travel of the rotorcraft during flight at flight travel altitudes;

wherein the feathering spindle defines an interior cavity extending in the radial direction therethrough; and

wherein the feathering spindle receives and retains the root of the rotor blade within the interior cavity.

2. The rotorcraft of claim 1 , wherein the hub and feathering spindle combine to form an annular cavity therebetween.

3. The rotorcraft of claim 2 , wherein the flow of oil passes into and out of the annular cavity.

4. The rotorcraft of claim 3 , further comprising an oil system containing and motivating the flow of oil.

5. The rotorcraft of claim 4 , wherein the oil system cools the flow of oil during take off and landing of the rotorcraft.

6. The rotorcraft of claim 5 , wherein the oil system heats the flow of oil during travel of the rotorcraft at altitude.

7. The rotorcraft of claim 1 , wherein the feathering spindle comprises at least one bearing interfacing with the hub.

8. The rotorcraft of claim 7 , wherein the flow of oil lubricates the at least one bearing.

9. The rotorcraft of claim 1 , further comprising a flow of compressed air generated by the at least one engine, the flow of compressed air passing through the interior cavity and through the conduit from the root to the tip of the rotor blade.

10. The rotorcraft of claim 9 , wherein the feathering spindle comprises at least one tapered roller bearing interfacing with the hub.

11. The rotorcraft of claim 10 , wherein the feathering spindle further comprises an inboard end and an outboard end, spaced in the radial direction from the inboard end.

12. The rotorcraft of claim 11 , wherein the feathering spindle further comprises a thrust flange positioned proximate the inboard end, the thrust flange comprising a pitch arm extending therefrom.

13. The rotorcraft of claim 12 , wherein the root of the rotor blade extends in the radial direction through the interior cavity and engages the thrust flange.

14. A rotorcraft in one of take off and landing mode, the rotorcraft comprising:

an airframe;

at least one engine connected to the airframe;

a rotor connected to the airframe and defining axial and radial directions, the rotor comprising

a hub,

a rotor blade having a root and a tip and forming a conduit extending from the root to the tip,

a feathering spindle comprising at least one bearing interfacing with the hub,

the feathering spindle defining an interior cavity extending in the radial direction therethrough, and

the feathering spindle receiving and retaining the root of the rotor blade within the interior cavity;

a flow of compressed air generated by the at least one engine;

the flow of compressed air passing through the interior cavity and through the conduit from the root to the tip of the rotor blade;

the flow of compressed air transferring heat to the feathering spindle;

a flow of oil passing proximate the feathering spindle;

the flow of oil lubricating the at least one bearing; and

the flow of oil removing heat from the feathering spindle.

15. A method comprising:

selecting a rotorcraft comprising

an airframe,

at least one engine connected to the airframe, and

a rotor connected to the airframe and defining axial and radial directions, the rotor comprising a hub, a rotor blade having a root and a tip and forming a conduit extending from the root to the tip, and a feathering spindle connecting the rotor blade to the hub, the feathering spindle defining an interior cavity extending in the radial direction therethrough, the feathering spindle receiving and retaining the root of the rotor blade within the interior cavity;

executing, with the rotorcraft, a takeoff;

passing, during the takeoff, a flow of compressed air generated by the at least one engine through the interior cavity and through the conduit from the root to the tip of the rotor blade;

transferring, during the takeoff by the flow of compressed gas, heat to the feathering spindle;

passing, during the takeoff, a flow of oil proximate the feathering spindle;

lubricating, by the flow of oil during the takeoff, the feathering spindle; and

removing, during the takeoff by the flow of oil, heat from the feathering spindle.

16. The method of claim 15 , further comprising:

flying the rotorcraft at a flight travel altitude; and

losing, by the feathering spindle during the flying, heat to the surrounding atmosphere.

17. The method of claim 16 , further comprising:

passing, during the flying, the flow of oil proximate the feathering spindle;

lubricating, by the flow of oil during the flying, the feathering spindle; and

transferring, by the flow of oil during the flying, heat to the feathering spindle.

18. The method of claim 17 , wherein the flying comprises flying the rotorcraft at an advance ratio greater than 0.5.

Assignments (12)

Continuity (37)