F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
60/151, 60/152
F02C 9/16 (2006.01) F02C 9/52 (2006.01)
Patent
CA 1053915
GAS TURBINE CONTROL Abstract of the Disclosure A fuel and burner variable geometry (BVG) control for a gas turbine engine. Fuel is controlled in response to the product of desired overall fuel-air ratio and a value of air flow derived from gas generator turbine speed. The desired fuel-air ratio is controlled by a speed governor, and by acceleration and deceleration limits varied as a function of measured burner inlet temperature. A compensated turbine inlet temperature (TIT) signal is derived from measurement of actual turbine inlet temperature and acceleration or decele- ration compensation based upon rate of change of the desired fuel-air ratio. The difference between the compensated TIT and the burner inlet temperature (BIT) is the burner tempe- rature rise. The setting of air flow control devices in the com- bustion apparatus (BVG) determines the ratio of primary to total air. The desired ratio to control BVG is computed by dividing burner temperature rise by flame temperature rise. Flame temperature rise is the difference between the desired flame temperature and the measured BIT. The desired flame temperature is scheduled as a function of BIT and BVG. The ratio of primary to total air may be limited temporarily during starting of the engine.
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