초록 ▼

By utilizing compensating parameters required for steady state operation of a gas turbine engine with processed variables of compressor speed, compressor pressure and altitude a derivative of the variable desired is synthesized and compared to the actual value in a closed-loop system for limiting th

By utilizing compensating parameters required for steady state operation of a gas turbine engine with processed variables of compressor speed, compressor pressure and altitude a derivative of the variable desired is synthesized and compared to the actual value in a closed-loop system for limiting the rate of change of fuel flow in an engine transient condition. In a twin spool engine a function generator responding to speed of the low pressure compressor and altitude generates a signal indicative of rate of change of the speed of the high pressure compressor. The signal is compensated for time constants consistant with the dynamics of the engine and compared with a compensated actual high pressure compressor speed. The error produced with a gain generated from corrected high pressure compressor speed inputs the main electronic digital fuel control.

대표청구항 ▼

The method of controlling a gas turbine engine of the type having a high pressure compressor, a low pressure compressor, a burner, a source of fuel, and a fuel regulator regulating the flow of fuel from said source to said burner, electronically controlling said fuel regulator in response to engine

The method of controlling a gas turbine engine of the type having a high pressure compressor, a low pressure compressor, a burner, a source of fuel, and a fuel regulator regulating the flow of fuel from said source to said burner, electronically controlling said fuel regulator in response to engine operating conditions for controlling the operation of said engine, limiting the rate of change of said regulator for transient conditions of said engine operations by simulating the derivative value of the high pressure compressor, including: calculating the simulated derivative signal by: (a) computing the corrected low and high pressure compressor speeds; (b) generating an output signal that is a function of the corrected low pressure compressor speed and altitude to a value indicative of the rate of change of the high pressure compresser speed; (c) generating a time constant signal that is a function of corrected high pressure compressor speed; (d) multiplying the rate of change of the high pressure compressor speed signal by said time constant signal to obtain a referenced high pressure compressor speed signal; (e) summing the referenced high pressure compressor speed signal and the actual high pressure compressor speed to obtain a first desired high pressure compressor speed signal; (f) generating an output signal as a function of the first desired high pressure compressor speed that is indicative of a second desired rotational speed of the high pressure compressor; and (g) computing an error between the second desired rotational speed of the high pressure compressor and the actual speed of the high pressure compressor after both being compensated for the time constant determined by the dynamics of the engine.