Gas-turbine engine control

Details Gas-turbine engine control Gas-turbine engine control

1980-06-24

1982-08-10

Malzahn, David H.

Boots, shoes, and leggings

60 3928R, F02C 908

Patent

active

043441416

ABSTRACT:
A control system for an aircraft gas-turbine engine has positive and negative acceleration control units. Each control unit has a memory storing values of the maximum or minimum desired rate of change of fuel flow at different speeds beyond which surge or extinction will occur. The control units produce output signals, in accordance with the engine speed and acceleration, for controlling fuel flow so that it follows closely within the surge or extinction curves. The system also has amplitude gates that pass one or the other of these output signals to the engine if the speed of engine demanded by the pilot is such as to cause surge or extinction.

REFERENCES:
patent: 3928962 (1975-12-01), Maker
patent: 3956884 (1976-05-01), Eves
patent: 4006590 (1977-02-01), Itoh
patent: 4077204 (1978-03-01), Itoh
patent: 4142364 (1979-03-01), Wanger

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