Integrated fuel nozzle with feedback control for a gas turbine engine

摘要

A gas turbine engine (10) includes a combustor (16) having a fuel nozzle assembly (24) for delivering fuel to a combustion chamber (20). A sensor (40) is at least partially housed within the fuel nozzle assembly (24) for sensing a parameter associated with the delivery of fuel to the combustion chamber (28). In one example, the sensor (40) is an optical sensor coupled to an optical decoder (42) for ascertaining the parameter. A trim valve (34) is in communication with the fuel nozzle assembly. A controller (44) is in communication with the sensor (40) and is programmed to actuate the trim valve (34) to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor (40) is arranged near a fuel exit (38) of the fuel nozzle assembly. The controller (44) actuates the trim valve (34) for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.