Patent ID: 9366189
Filing Date: 2016-06-14
CPC Classification: F02C,F05D,F23R

Claim Text:
1. A system for reducing pressure oscillations within a gas turbine engine, comprising: at least one fuel injector configured to inject fuel into a combustor; a valve fluidly coupled to the at least one fuel injector, wherein the valve is configured to facilitate fuel flow to the at least one fuel injector while the valve is in an open position, and to block fuel flow to the at least one fuel injector while the valve is in a closed position; and a controller communicatively coupled to the valve, wherein the controller is configured: to send a first control signal instructing the valve to cycle between the open position and the closed position, the first control signal having a first frequency and a first duty cycle while a magnitude of pressure oscillations within the combustor is less than a threshold value, to receive a feedback signal indicative of a magnitude, a phase, and a frequency of pressure oscillations within the combustor; to send a second control signal instructing the valve to cycle between the open position and the closed position, the second control signal having a second frequency and a second duty cycle while the magnitude of the pressure oscillations within the combustor is greater than or equal to the threshold value, wherein to send a second control signal comprises: to adjust the second frequency associated with the second control signal based on the frequency of the pressure oscillations such that the second frequency associated with the second control signal is substantially equal to the frequency of the pressure oscillations within the combustor.