Fail-safe, anti-icing system for aircraft engines
US4397431A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Nov 2, 1981 |
| Grant date | Aug 9, 1983 |
| Priority date | — |
| Expiry date | Nov 2, 2001 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/0293
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An actuating linkage is provided for use in an aircraft engine having a double door-type particle separator, anti-icing system installed within its air intake ducts. The actuating linkage interconnects the deflecting vane and the bypass door through a coupler link. The deflecting vane is pivotally connected to a linear link which is connected to an actuator link about a pivot point. Movement of the actuator link varies the relative positions of the deflecting vane and the bypass door between ram mode and anti-icing mode positions. The actuating linkage partially balances the aerodynamic forces on the deflecting vane and bypass door so that the input required to operate the anti-icing system may be manually applied by the pilot. The actuating linkage is fail-safe, in that the linkage is operative such that should the actuator link extending to the pilot station fail, the aerodynamic forces on the bypass door cause the deflecting vane and bypass door to be actuated to the anti-icing mode position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.