초록 ▼

A control apparatus of a gas turbine combustor obtains a stable combustion with limited NOx emission through a control of a fuel flow rate according to a turbine output and a control of a flow rate of intake air mixed with the fuel. The control apparatus includes an apparatus for detecting at least

A control apparatus of a gas turbine combustor obtains a stable combustion with limited NOx emission through a control of a fuel flow rate according to a turbine output and a control of a flow rate of intake air mixed with the fuel. The control apparatus includes an apparatus for detecting at least one of the temperature and the humidity of intake air taken into the combustor, an apparatus for determining and storing, in advance, a stable combustion limit line between a stable combustion region and an unstable combustion region, on a plane of coordinates of a ratio of fuel flow rate to an intake air flow rate or an intake air flow rate and the temperature or the humidity of the intake air, on each turbine load, an apparatus for detecting an instant operational point of the combustor on the plane of coordinates, and an apparatus for correcting the intake air flow rate or the ratio of fuel flow rate to the intake air flow rate according to an increase in the detected temperature or humidity so that the instant operational point does not cross the stable combustion limit line.

대표청구항 ▼

A control apparatus of a gas turbine combustor for effecting a stable combustion with limited NOx emission through control of a fuel flow rate in accordance with a turbine output and control of a flow rate of intake air mixed with fuel of the gas turbine combustor, said control apparatus comprising:

A control apparatus of a gas turbine combustor for effecting a stable combustion with limited NOx emission through control of a fuel flow rate in accordance with a turbine output and control of a flow rate of intake air mixed with fuel of the gas turbine combustor, said control apparatus comprising: means for detecting at least one condition of said intake air to be taken into said gas turbine combustor, combustion stability in and NOx emission from the combustor being a function of said condition of the intake air; means for determining and storing, in advance of an operation of said gas turbine combustor, a stable combustion limit line of the gas turbine combustor between a stable combustion region of the gas turbine combustor and an unstable combustion region of the gas turbine combustor and a NOx emission limit line, on a plane of coordinates of a parameter which is a function of at least an intake air flow rate of the intake air and said condition of the intake air, on each turbine output; means for detecting an instant operational point of said gas turbine combustor on said plane of coordinates; and means for correcting a ratio of fuel flow rate to the intake air flow rate in accordance with a change in said detected condition of the intake air so that said instant operational point is kept between said stable combustion limit line and said NOx emission limit line.