Control for gas turbine engine

Details Control for gas turbine engine Control for gas turbine engine

1977-02-01

1979-07-03

Garrett, Robert E.

Power plants

Reaction motor

Method of operation

60236, 60238, 60242, 60243, F02K 302, F02C 908

Patent

active

041596250

ABSTRACT:
Increased thrust during the transonic flight mode of an aircraft powered by a gas turbine engine is realized by a closed loop control that closes the loop on the pressure ratio across the fan by adjusting fuel flow and/or exhaust nozzle area in a turbofan, variable exhaust nozzle installation. Fan pressure ratio is scheduled as a function of corrected fan speed and actual pressure ratio provides an error signal to readjust engine operation to null out this error signal. A turbine inlet temperature limit signal is generated to prevent inadvertent overheating and it or this pressure ratio error signal is selected for providing the lower fuel flow value.

REFERENCES:
patent: 2848870 (1958-08-01), Eastman
patent: 2989849 (1961-06-01), Torell et al.
patent: 3511047 (1970-05-01), Yates
patent: 3764785 (1973-10-01), Harner et al.
patent: 3852956 (1974-12-01), Martin
patent: 3854287 (1974-12-01), Rembold
patent: 3867717 (1975-02-01), Moehring et al.

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