JPH0617668A - Ignition/misfire monitoring method for gas turbine engine - Google Patents

Abstract

PURPOSE:To provide the monitoring method capable of correctly checking ignition and monitoring misfire on the real time basis without being affected by the fluctuation of the outside air temperature when a gas turbine engine is started. CONSTITUTION:The ignition and misfire phenomena are detected when the ignited state is compared with the unignited state, i.e., when the temperature difference between the discharge temperature of the compressor of a gas turbine and the exhaust temperature is detected. Multiple preset values of the temperature difference in response to the revolving speed are set for the ignition and misfire phenomena during the start. When the temperature difference is higher than the preset value corresponding to the revolving speed, the state is judged as ignition. When the temperature difference is lower than the preset value, the state is judged as misfire. The feed of fuel is stopped when the state is judged as misfire.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION The present invention relates to a gas turbine engine
The misfire monitoring method can be applied to a gas turbine engine control device of a gas turbine power generator, a surge prevention control device of an industrial compressor, and the like.

[0002]

2. Description of the Related Art For example, Japanese Patent Publication No. 3-55653 is known as a control device for detecting ignition failure at startup of a gas turbine engine and misfire during startup. According to this publication, the control device has an exhaust temperature detection unit that is set to operate at an exhaust temperature that is lower by a certain value than when idling, and a delay unit that delays the operation start of the exhaust temperature detection unit for a certain time at startup, A fuel valve control unit that stops the fuel supply when an exhaust temperature lower than the set value is detected by the exhaust temperature detection unit is provided, and the fuel supply is stopped by performing ignition failure and misfire detection at the exhaust temperature. Further, since the exhaust temperature is originally low at the time of starting, detection of the exhaust temperature is delayed.

[0003]

In the prior art as described above, the exhaust gas temperature during idling varies depending on the intake temperature of the compressor, and therefore varies greatly between summer and winter. Therefore, if the difference between the exhaust temperature at idling and the set value is too small, it causes malfunction, and if it is too large, there is a drawback that it is delayed.

Further, the use of the delay means for delaying the operation start of the exhaust gas temperature detector at the time of starting means that the ignition phenomenon cannot be directly measured by this method. That is, the ignition failure is determined as the ignition failure by catching the phenomenon of misfire. Therefore, there is a drawback in that the phenomenon of abnormal combustion itself, such as misfire after ignition and ignition again, cannot be captured.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a method for monitoring the arrival / misfire of a gas turbine engine, which eliminates the above-mentioned drawbacks.

[0006]

To solve the above-mentioned problems, according to the present invention, the number of revolutions of the gas turbine and the temperature difference between the compressor discharge temperature and the exhaust temperature are detected and the gas turbine is started after the start of the gas turbine. When the number of revolutions is equal to or higher than a predetermined value, the temperature difference is confirmed to be ignition when the temperature is equal to or higher than a predetermined value. There is provided a method for monitoring ignition / misfire of a gas turbine engine, which is characterized by determining ignition failure and misfire when it is low and stopping fuel supply.

[0007]

According to the above means, by detecting the temperature difference between the compressor discharge temperature of the gas turbine and the exhaust temperature, it is possible to catch the phenomenon of ignition or misfire in comparison with the non-ignition state. In addition, by setting the set value of the temperature difference between the compressor discharge temperature and the exhaust temperature according to the number of revolutions, it is possible to judge the ignition and misfire phenomena during startup depending on whether the temperature difference is higher or lower than the set value. I am trying to do it.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is a flow chart of a method for monitoring arrival / misfire according to the present invention, and FIG. 2 shows a starting curve of an emergency power generator. In FIG. 2, (a) shows the relationship between the time axis and the speed-up speed, (b) shows the change between the exhaust temperature and the discharge temperature of the compressor at that time, and (c) shows the ignition determination and misfire at that time. The relationship between the number of revolutions to be judged and the set value is shown.

In determining the ignition / misfire, the rotational speed of the gas turbine, the compressor discharge temperature, and the exhaust temperature are detected. First, in the ignition determination at startup, the rotation speed is, for example, 1
When the temperature difference between the compressor discharge temperature and the exhaust temperature becomes, for example, 500 ° C. or more between 4% and 25%, it is determined that ignition occurs, and if the temperature difference does not become 500 ° C. or more,
When it is determined that ignition has failed, the fuel solenoid valve is closed, the fuel supply is stopped, and the air purge operation for discharging unburned gas is performed. After that, the turbine is once stopped and then restarted again.

After the start-up, if it is determined that ignition has occurred, the misfire monitoring procedure is started. The set value of the temperature difference with respect to the rotation speed is set stepwise in the example of FIG. For example,
When the rotation speed is 25% or more, the temperature difference is 200 ° C, when it is 80% or more, it is 50 ° C, and when it is 95% or more, it is 5 ° C. The set value of the temperature difference with respect to the number of revolutions may be set in a larger number of steps, or may be set continuously instead of in steps.

In the misfire monitoring procedure, if the number of revolutions is 25% or more and the temperature difference is 200 ° C. or less, the misfire state is 200
Ignition is judged to be above ° C. Next, the rotation speed is 80
% Or more and the temperature difference is 50 ° C. or less, there is a misfire, 5
If the temperature is 0 ° C or higher, it is determined that the ignition state is set. If the rotation speed is 95% or more and the temperature difference is 5 ° C. or less, it is determined that the misfire state is present and if the temperature difference is 5 ° C. or more, the ignition state is obtained. In this way, when the temperature difference is lower than the set value at each rotation speed and it is determined that the engine is in the misfire state, the fuel electromagnetic valve is closed, and after restarting the air purge operation, the restart is attempted.

[0012]

According to the present invention, since the rotational speed is incorporated in the temperature difference between the compressor discharge temperature and the exhaust temperature as a criterion, it is possible to quickly and accurately determine the ignition and misfire phenomena during startup. Like

Further, by detecting the temperature difference between the compressor discharge temperature and the exhaust gas temperature, that is, by comparing the ignition / misfire phenomenon with the non-ignition state, there is no influence of the outside air temperature. It is not necessary to change the set value that is the basis of the determination according to the outside air temperature.

[Brief description of drawings]

FIG. 1 is a flow chart showing a procedure of a method for monitoring landing / misfire of a gas turbine engine according to the present invention.

FIG. 2 is an explanatory diagram showing a relationship among a rotation speed, a compressor discharge temperature, an exhaust temperature, and a temperature difference set value at the time of starting the emergency power generation device.

Claims (1)

[Claims] 1. A rotation speed of a gas turbine and a temperature difference between a compressor discharge temperature and an exhaust gas temperature are detected, and the temperature difference is a predetermined value when the rotation speed is a predetermined value or more after the gas turbine is started. When it is above, it is confirmed as ignition, and when this ignition is not confirmed or when the temperature difference is lower than the set value set according to the number of revolutions after confirmation of ignition, it is judged as ignition failure and misfire and the fuel supply is stopped. A method for monitoring the arrival and misfire of a gas turbine engine, characterized by: