GAS TURBINE ACTIVE COMBUSTION INSTABILITY CONTROL SYSTEM
A turbine active combustion instability control system comprising a primary passage to a combustor of a turbine; a combustor pressure sensor configured to measure dynamic pressure within the combustor; a pilot valve metering fuel flow through a pilot passage to the combustor and comprising a valve seat defining a throat in the pilot passage and a valve plug movable to control fuel flow through the throat, the pilot valve having an inlet passage with a contoured surface to accelerate gas flow through the throat to at least Mach 1; a dynamic linear motor actuator connected to the valve plug and configured to actuate the valve plug at a high frequency; and a controller configured to provide a control signal to the actuator as a function of input from the combustor pressure sensor.
1 . A gas turbine active combustion instability control system comprising:
a primary fuel flow passage to a combustor of a combustion turbine;
a combustor pressure sensor configured to measure a dynamic pressure within said combustor;
a pilot fuel flow passage to said combustor;
a pilot control valve configured to meter fuel flow through said pilot flow passage to said combustor from an upstream side to a downstream side, said pilot control valve comprising:
a pilot metering valve body having a valve seat defining a throat in said pilot flow passage between said upstream side and said downstream side;
a pilot metering valve plug movable relative to said pilot metering valve body from an open position to a closed seated position to control fuel flow through said throat from said upstream side to said downstream side;
said pilot metering valve body having an inlet passage on said upstream side of said throat, said inlet passage having a contoured surface generally angled to narrow toward said throat and to accelerate gas flow through said throat to at least Mach 1;
said pilot metering valve body having an outlet passage on said downstream side of said throat;
a dynamic linear motor actuator connected to said pilot metering valve plug and configured and arranged to actuate said pilot metering valve plug at a high frequency; and
a controller configured and arranged to receive input from said combustor pressure sensor and to provide a control signal to said linear motor actuator as a function of said input from said combustor pressure sensor;
whereby said pilot control valve assembly is configured and arranged to modulate a sonic fuel flow through said throat as a function of said input from said combustor pressure sensor.
2 . The gas turbine active combustion instability control system set forth in claim 1 , wherein said inlet passage comprises a frusto-conical surface.
3 . The gas turbine active combustion instability control system set forth in claim 1 , wherein said actuator comprises a stator and a shaft connected to said pilot metering valve plug for actuating said pilot metering valve plug between said closed position and said open position.
4 . The gas turbine active combustion instability control system set forth in claim 1 , wherein said combustion turbine powers an electric generator.
5 . The gas turbine active combustion instability control system set forth in claim 1 , wherein said controller is located in said linear motor actuator.
6 . A gas turbine active combustion instability control system comprising:
a primary fuel flow passage to a combustor of a combustion turbine;
a combustor diagnostic sensor configured to measure combustion parameters within said combustor;
a pilot fuel flow passage to said combustor;
a pilot control valve configured to meter fuel flow through said pilot flow passage to said combustor from an upstream side to a downstream side, said pilot control valve comprising:
a pilot metering valve body having a valve seat defining a throat in said pilot flow passage between said upstream side and said downstream side;
a pilot metering valve plug movable relative to said pilot metering valve body from an open position to a closed seated position to control fuel flow through said throat from said upstream side to said downstream side;
said pilot metering valve body having an inlet passage on said upstream side of said throat, said inlet passage having a contoured surface generally angled to narrow toward said throat and to accelerate gas flow through said throat to at least Mach 1;
said pilot metering valve body having an outlet passage on said downstream side of said throat;
an actuator connected to said pilot metering valve plug and configured and arranged to actuate said pilot metering valve plug at a high frequency; and
a controller configured and arranged to receive input from said combustor diagnostic sensor and to provide a control signal to said actuator as a function of said input from said combustor diagnostic sensor;
whereby said pilot control valve assembly is configured and arranged to modulate a sonic fuel flow through said throat as a function of said input from said combustor pressure sensor
7 . The gas turbine active combustion instability control system set forth in claim 6 , wherein said actuator is selected from a group consisting of a linear actuator, a rotary actuator, an electro-hydrostatic actuator, an electrohydraulic linear actuator and a hydraulic linear actuator.
8 . The gas turbine active combustion instability control system set forth in claim 6 , wherein said combustor diagnostic sensor comprises a dynamic pressure sensor.