Aircraft gas turbine engine backbone deflection control

Details Aircraft gas turbine engine backbone deflection control Aircraft gas turbine engine backbone deflection control

1992-12-04

1994-06-14

Bertsch, Richard A.

Power plants

Combustion products used as motive fluid

Combined with regulation of power output feature

60 3932, 244 54, F02C 720

Patent

active

053199227

ABSTRACT:
A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between axially spaced apart frames connected by the backbone. One embodiment of the invention, for a high bypass ratio turbofan engine, provides a hydraulically powered actuator to produce tensioning forces in cables connected between a fan frame and a turbine frame and the actuator is controlled by the engines digital electronic control system using input signals generated by inlet moment load sensors and/or blade tip clearance sensors.

REFERENCES:
patent: 4022018 (1977-05-01), Tuten et al.
patent: 4266741 (1981-05-01), Murphy
patent: 4428189 (1984-01-01), Greenberg et al.
patent: 4471609 (1984-09-01), Porter et al.
patent: 4603821 (1986-08-01), White

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