Fail-safe, anti-icing system for aircraft engines

Details Fail-safe, anti-icing system for aircraft engines Fail-safe, anti-icing system for aircraft engines

1981-11-02

1983-08-09

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft power plants

55306, 60 39092, 60 39093, B64D 3302, F02G 300

Patent

active

043974317

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.

REFERENCES:
patent: 2381705 (1945-08-01), Vokes
patent: 3329377 (1967-07-01), Peterson et al.
patent: 3544045 (1970-12-01), Butscher
patent: 3952972 (1976-04-01), Tedston et al.
patent: 3991782 (1976-11-01), Schwarzler
patent: 4250703 (1981-02-01), Norris et al.
patent: 4346860 (1982-08-01), Tedstone

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