| 发明名称 |
System for heat dissipation from an internal actuator in a rotor blade |
| 摘要 |
A rotor blade for an aircraft includes an airfoil skin, an active element, and an actuator configured to operate the active element. A heat pipe is configured to promote heat transfer from the actuator to the airfoil skin. 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 of the heat pipe toward an evaporator end of the heat pipe. |
| 申请公布号 |
US8926272(B2) |
申请公布日期 |
2015.01.06 |
| 申请号 |
US201113227181 |
申请日期 |
2011.09.07 |
| 申请人 |
Textron Innovations Inc. |
发明人 |
Schank Troy C.;McGlaun Monte A. |
| 分类号 |
B64C27/615;B64C27/72 |
主分类号 |
B64C27/615 |
| 代理机构 |
|
代理人 |
Walton James E.;Harris Brian E. |
| 主权项 |
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. |
| 地址 |
Providence RI US |
