Control system for gas turbine combustor

Details Control system for gas turbine combustor Control system for gas turbine combustor

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 9/26 (2006.01)

Patent

CA 2154440

A control system for a gas turbine combustor is disclosed having a flame temperature sensor positioned within an air fuel mixer immediately upstream of the combustion zone, allowing the sensor to observe and measure the ultraviolet energy of the flame at its upstream end. Control means is also provided which receives an electrical signal representative of the measured ultraviolet energy, converts the electrical signal into a temperature representative of the measured ultraviolet energy, compares the measured temperature to a specified temperature range, and sends a signal to a fuel supply and control to adjust fuel flow into the combustor as required. The flame temperature sensor is preferably positioned within a centerbody of the air fuel mixer and aligned with a turbine nozzle at the downstream end of the combustor.

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