초록 ▼

In a control method of a gas turbine engine, an engine controller 4 outputs a combustor power command FD based on an engine condition from an engine condition detector 3. Then, a combustion controller 6 determines each fuel flow rate based on the combustion power command FD. The combustor controller

In a control method of a gas turbine engine, an engine controller 4 outputs a combustor power command FD based on an engine condition from an engine condition detector 3. Then, a combustion controller 6 determines each fuel flow rate based on the combustion power command FD. The combustor controller 6 overrides each fuel flow rate for a certain period, to realize smooth stage-process.

대표청구항 ▼

The invention claimed is: 1. A control method of a gas turbine engine including a combustor having a plurality of main combustion portions and a plurality of pilot combustion portions, an engine condition detector, and a combustor condition detector, comprising the steps of: outputting a combustor

The invention claimed is: 1. A control method of a gas turbine engine including a combustor having a plurality of main combustion portions and a plurality of pilot combustion portions, an engine condition detector, and a combustor condition detector, comprising the steps of: outputting a combustor power command based on an engine condition from the engine condition detector; and carrying out a stage-processing by outputting a fuel flow rate command, the fuel flow rate of the command being obtained by overriding, for a predetermined period, a step flow rate determined based on a combustor condition from the combustor condition detector to a fuel flow rate determined based on the combustor power command. 2. The control method of a gas turbine engine according to claim 1, wherein the main combustion portions are divided into the predetermined number of blocks, and when the fuel flow rate command is output, the fuel flow rate command is respectively output to the main combustion portions of the combustor for every block. 3. The control method of a gas turbine engine according to claim 1, wherein immediately after an ignition of the main combustion portions is detected, the fuel flow rate of the command has a value obtained by subtracting the step flow rate from a fuel flow rate at the detection of the ignition. 4. The control method of a gas turbine engine according to claim 3, wherein the ignition of the main combustion portions is detected based on a pressure variation of the combustor, a temperature of a combustion gas, a brightness of a combustion gas, a wavelength of a combustion gas, a rotational speed of a turbine, or a controlled variable of the engine. 5. A controlling system of a gas turbine engine including a combustor having a plurality of main combustion portions and a plurality of pilot combustion portions, comprising: an engine condition detector; a combustor condition detector; an engine controller for outputting a combustor power command based on an engine condition from the engine condition detector; and a combustor controller for carrying out a stage-processing by outputting a fuel flow rate command, the fuel flow rate of the command being obtained by overriding, for a predetermined period, a step flow rate determined based on a combustor condition from the combustor condition detector to a fuel flow rate determined based on the combustor power command. 6. The controlling system of a gas turbine engine according to claim 5, wherein the combustor controller outputs the fuel flow rate command respectively to the main combustion portions divided into blocks. 7. The controlling system of a gas turbine engine according to claim 5, wherein immediately after an ignition of the main combustion portions is detected, the fuel flow rate of the command has a value obtained by subtracting a step flow rate from a fuel flow rate at the detection of the ignition. 8. The controlling system of a gas turbine engine according to claim 7, wherein the ignition of the main combustion portions is detected based on a pressure variation of the combustor, a temperature of a combustion gas, a brightness of a combustion gas, a wavelength of a combustion gas, a rotational speed of a turbine, or a controlled variable of the engine. 9. A gas turbine engine comprising: a compressor; a turbine; a combustor including a plurality of main combustion portions and a plurality of pilot combustion portions; and a control system of a gas turbine including an engine condition detector, a combustor condition detector, an engine controller for outputting a combustor power command based on an engine condition from the engine condition detector, and a combustor controller for carrying out a stage-processing by outputting a fuel flow rate command, the fuel flow rate of the command being obtained by overriding, for a predetermined period, a step flow rate determined based on a combustor condition from the combustor condition detector to a fuel flow rate determined based on the combustor power command.