System for heat dissipation from an internal actuator in a rotor blade

1. A rotor blade for an aircraft, the rotor blade comprising:

an airfoil skin;

an active element;

an actuator configured to operate the active element; and

a heat pipe configured to promote heat transfer from the actuator to the airfoil skin;

wherein the heat pipe has a slope gradient such that a centrifugal force generated during rotation of the rotor blade promotes travel of a condensed working fluid within the heat pipe to move from a condenser end toward an evaporator end.

2. The rotor blade according to claim 1 , wherein the condenser end of the heat pipe is thermally coupled to a cover, the cover having an exterior surface that forms a portion of the airfoil skin.

3. The rotor blade according to claim 2 , wherein the cover forms part of an upper exterior surface of the airfoil skin.

4. The rotor blade according to claim 2 , wherein the cover forms part of a lower exterior surface of the airfoil skin.

5. The rotor blade according to claim 1 , wherein the heat pipe has a bend approximately mid-length of the heat pipe, such that the condenser end of the heat pipe approximately aligns with a portion of an airfoil surface defined by the airfoil skin.

6. The rotor blade according to claim 1 , wherein the condenser end of the heat pipe is closer to a root end of the rotor blade, as compared to the evaporator end of the heat pipe.

7. The rotor blade according to claim 1 , wherein the evaporator end of the heat pipe is coupled to a heat sink that houses the actuator.

8. The rotor blade according to claim 1 , wherein the condenser end of the heat pipe has a thermal path to the airfoil skin.

9. A system for a rotor blade, the system comprising:

an actuator;

a cover forming a partial airfoil surface of the rotor blade;

a heat pipe having a condenser end and an evaporator end; and

a heat sink in thermal contact with the actuator;

wherein the heat pipe is configured to transfer heat from the actuator to the cover.

10. The system according to claim 9 , wherein the actuator is configured to produce heat during operation.

11. The system according to claim 9 , further comprising:

a trailing edge flap on the rotor blade;

wherein the actuator is configured to produce heat during an actuation of the trailing edge flap.

12. The system according to claim 9 , wherein the actuator includes a linear motor stator.

13. The system according to claim 9 , wherein the evaporator end of the heat pipe is closer to a tip end of the rotor blade as compared to the condenser end of the heat pipe, thereby allowing a centrifugal force to promote transfer of a condensed working fluid from the condenser end to the evaporator end, the centrifugal force being generated by rotation of the rotor blade.

14. The system according to claim 9 , wherein the heat pipe is angled so that a centrifugal force promotes transfer of a condensed working fluid from the condenser end of the heat pipe to the evaporator end of the heat pipe, the centrifugal force being generated by rotation of the rotor blade.

15. The system according to claim 9 , wherein the heat pipe is in thermal contact with a saddle, the saddle being releasably coupled to the cover.

16. The system according to claim 9 , wherein the cover has an exterior surface, the exterior surface being exposed to airflow during operation of the rotor blade, such that the airflow acts to promote heat transfer from the cover to ambient air.

17. The system according to claim 9 , wherein the evaporator end of the heat pipe is located below the condenser end of the heat pipe.