GAS TURBINE ACTIVE COMBUSTION INSTABILITY CONTROL SYSTEM
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United States of America Patent
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Issued Date -
Mar 23, 2017
app pub date -
Sep 20, 2016
filing date -
Sep 21, 2015
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Abstract
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.
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