Title: Aircraft engine coupling

Abstract: A torque responsive coupling includes an intermediate coupling member with helical splines thereon selectively engageable with first and second axially spaced helically splined coupling discs connected respectively to an engine power shaft and to a gear reduction input shaft to a propeller. Each of the coupling disc splines is maintained in engagement with the splined portions of the intermediate coupling member by spring means to transmit power from the engine shaft to the propeller and the intermediate coupling member is responsive to a high negative torque from the propeller when the engine fails to shift axially to separate spline teeth for decoupling the engine shaft and propeller and cause a hydraulic lockout system to apply a force on the intermediate coupling member in opposition to the spring means to maintain the spline teeth decoupled to prevent ratcheting therebetween; the hydraulic lockout system includes a single piston unit indexed to control pressure balance ports and an exhaust valve for establishing the opposition force.

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Inventors: Langham, Stephen (Indianapolis, IN, US)

Application Number: 629074
Filing Date: 1975-11-05
Publication_date: 1976-12-14
Assignee: General Motors Corporation (Detroit, MI)
Primary Class(es): 192/46 192/56.32, 192/56.56, 192/91A, 192/104F, 192/114R
Other Classes:
US Patent Ref:

2683512	Jul, 1954	Boice	192/56.
2700443	Jan, 1955	Boice	192/56.
3205986	Sep, 1965	Kramer	192/56.
3225876	Dec, 1965	Dison	192/56.
3249187	May, 1966	McDowall	192/46.
3713518	Jan, 1973	Hawkins	192/46.

Other Refs:
Primary Examiner: Herrmann, Allan D.
Assistant Examiner:
Attorney: Evans; J. C.