System for heat dissipation from an internal actuator in a rotor blade
US8926272B2 · kind B2 · utility
3Cited by
6References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 7, 2011 |
| Grant date | Jan 6, 2015 |
| Priority date | — |
| Expiry date | May 11, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/30
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.