To improve the reliability of stall detection by detecting the stall of a gas turbine in engine on the basis of the intensity of ultraviolet rays to be detected by an augmenter when a burner pressure sensor fails and/or bursts out.
A gas turbine power unit 10 of aircraft, in an engine control 70, monitors a plurality of engine parameters, calculating the control data, and the variable geometry of a fuel flow and an engine is adjusted, thereby realizing the optimum engine operation. It is equipped with a burner pressure sensor 72 of a gas generator and an ultraviolet detector 74 or a misfire detector as a detecting means of the engine parameters. When the burner pressure detected by the burner pressure sensor 72 exceeds a specified range, an engine warning alarm is emitted. When the burner pressure sensor 72 is out order, the intensity of ultraviolet rays in an augmenter 30 is detected by the ultraviolet detector 74, whereby misfire is detected by an increase of intensity of ultraviolet rays due to the misfire of combustion in the augmenter 30.
BROWN DAMON K
HINTON BRUCE S
KELLY JAMES B
