Engine power management system

Details Engine power management system Engine power management system

1977-12-27

1980-01-29

Garrett, Robert E.

Power plants

Reaction motor

Interrelated reaction motors

60243, 60 3928R, F02K 312, F02C 904

Patent

active

041854608

ABSTRACT:
An aircraft having two turbine engines is provided with both torque and temperature sensitive electronic circuitry to control the fuel supplied to the turbine engines. Pushbutton switches are provided for the selection of the desired torque level by the pilot. The fuel to either engine is reduced, regardless of output torque and its relationship to the pushbutton values of selected torque, when the engine temperature exceeds a predetermined safety level. Failsafe operation is provided through the use of a main fuel supply path including a manual fuel control valve extending from the fuel pump to the engine fuel nozzles, and a normally closed bypass fuel control line which selectively diverts fuel from the principal path under the control of the temperature and torque responsive electronic circuitry. An electromagnetically operated valve in the bypass line is normally closed and is selectively operated to the desired open condition under the control of the torque and temperature responsive circuitry mentioned above, to reduce fuel supplied to the turbine engines.

REFERENCES:
patent: 2667228 (1954-01-01), Wood et al.
patent: 2977756 (1961-04-01), Stone
patent: 3123974 (1964-03-01), Pearson et al.
patent: 3203179 (1965-08-01), Blackaby
patent: 3514949 (1970-06-01), Fredlake et al.
patent: 3969890 (1976-07-01), Nelson

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