JPH0264232A - Monitor display device of gas turbine combustor - Google Patents

Abstract

PURPOSE:To contribute to a rapid maintenance and the reduction of the repair time of a combustor by providing a display device to present a graphic display responding to the combustor position by receiving the output of an operation device and the outputs of temperature sensors. CONSTITUTION:In an exhaust gas flow passage of a gas turbine 4 which furnishes plural combustors 1 arranged in a circular form, plural exhaust gas temperature sensors 2 are arranged in a circular form. The results of the operation device 7 and the outputs of the temperature sensors 2 are given to a CRT device 3. On the graphic screen of the CRT device 3, the dispositions of combustors 1 and the exhaust gas temperatures measured by the temperature sensors 2 in an exhaust duct 5 are displayed. It is made possible to contribute to a rapid maintenance and to the reduction of repairing time of combustors in such a way.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a monitoring and displaying device for a combustor of a gas turbine, and particularly to a monitoring and displaying device suitable for indicating a combustor that is experiencing abnormal combustion.

BACKGROUND OF THE INVENTION A gas turbine combustor is annularly arranged and burns fuel in a plurality of can-shaped combustion liners to produce a generally annular stream of hot gas to drive a turbine.

Because gas turbine combustors are subject to extremely high pressures and temperatures, even relatively minor combustor problems, if left unnoticed, can lead to serious damage to the gas turbine.

For this reason, as a combustion monitoring device, for example,
Those described in No. 2851 and the like are known. This detects the difference between the maximum value and the minimum value of the temperature distribution of gas turbine exhaust gas, and if the difference becomes too wide, it is determined that there is an abnormality in the combustor.

[9! [Problem M to be solved by Akira] In the above conventional technology, among a plurality of combustors arranged in an annular manner,
No consideration was given to identifying which combustor is abnormal, and there was a problem in that in order to identify a malfunctioning combustor, all combustors had to be disassembled and inspected.

An object of the present invention is to display which of a plurality of gas turbine combustors is abnormal, thereby allowing quick maintenance.

[Means for Solving the Problems] In order to achieve the above object, the present invention provides a plurality of exhaust gas temperature detection systems arranged annularly in the exhaust gas flow path of a gas turbine including a plurality of annularly arranged combustors. a calculation means for calculating the rotation angle of the exhaust gas and gas at the temperature detector position as seen from the combustor based on gas turbine operating conditions; and a calculation means that receives the output of the calculation means and the output of each of the temperature sensors. te1
This invention provides a gas turbine combustor monitoring and display device comprising a display 'r stage that graphically displays on a display screen the exhaust gas temperature distribution and the combustor position corrected by the rotation angle. be.

[Operation] Gas exiting the combustor passes through the turbine, passes through the exhaust diffuser, and exits into the exhaust duct. During this time, the gas swirls in the axial direction. The angle is proportional to the gas turbine output, and generally, for example, when the angle is 0° at rated load, it changes to about 100'' at no load.

This turning angle is determined by the gas turbine output and atmospheric temperature.

Approximate calculations can be made from the amount of steam injected into the combustor and the opening of the guide vanes. As a result, the temperature sensor, which is arranged annularly within the exhaust duct, can indicate to which position the gas coming out of the combustor has flowed.

Therefore, by looking at this display, the operator can know which combustor's gas is being measured by the high or low temperature sensor.

As a result, the position of the combustor with an abnormality can be specified.[Embodiment] Hereinafter, an embodiment of the present invention will be described with reference to FIG. 1. ,1
4 is a gas turbine, 6 is an exhaust diffuser, and 5 is an exhaust duct. Reference numeral 2 denotes temperature sensors (thermocouples, etc.) for detecting exhaust temperature, which are arranged in an annular distribution in the exhaust duct.

Now, the cast turbine output L (MW), the atmospheric temperature TA (K
), steam injection amount to the combustor S+ (kg/S), inlet guide y opening α (deg), turbine exhaust pressure PI! The calculation device 7 calculates the gas swirl angle (the angle at which the waste from the combustor swirls as it passes through the gas turbine) δ as a function of 1.
Calculate with.

δ:chi (LITAI SIT (!+ Pgx
) In this example, the following equation was used.

δ= to 1L +, TA+ to 4Sl +, α+LI)
□The method for creating the above formula is based on actual machine tests under various conditions.
The coefficients of the above equation are determined so that the approximate equation fits well. This actual machine calculates the fuel flow rate of one combustor,
This is due to an increase of several to several tens of percent compared to other combustors. This will cause a change in the exhaust gas temperature distribution, and each coefficient in the above equation is determined based on this change.

The calculation result of the calculation device 7 and the output of each thermocouple 2 are C
It is given to the RT device 3. C. On the graphic screen of the RT device 3, the arrangement of the combustor 1 seen from the rear and the exhaust gas temperature determined by each thermocouple 2 of the exhaust duct 5 are displayed. The placement of combustor 1 on the graphic screen is
It is displayed rotated clockwise on the diagram by the angle of rotation δ calculated above.

The exhaust gas temperature measured by each thermocouple 2 is displayed as a circular line graph.

As an example, FIG. 1 shows a case where the temperature of the thermocouple 2 located at position (3) on the lower right side drops to 400° C. or less. At this time, the temperature of the other thermocouple 2 is a normal temperature of 400℃~50℃.
It is between 0℃. In this case, the combustor generating this low temperature gas is determined to be the Nα3 combustor. and generate an alarm.

At the bottom of the screen of CRTliff3 is [Nα3 Nensho Kiijyou! " is displayed.

Note that the circle indicated by a dotted line in the figure is the position of the combustor Nα1 when the rotation angle is 0°.

The above is an explanation when extreme exhaust temperature changes occur, but if the exhaust temperature distribution gradually expands during operation,
By observing the screen of the CRT device 3 over a long period of time, the location of the failure can be estimated. That is, the load changes when starting, stopping, or under other operating conditions with different dates and times. Therefore, the position of the combustor also moves on the graphic screen as the rotation angle changes. At this time, attention is paid to whether the thermocouple exhibiting a slightly abnormal temperature rotates in synchronization with the movement of the combustor. If they rotate synchronously, this is determined to be a failure of the combustor. If the thermocouple 2, which is not synchronized and always at the same position, shows an abnormal temperature, this is determined to be a failure of the thermocouple 2.

Furthermore, if the position of the thermocouple rotates about half way in the middle, it is determined that this is a failure of the turbine 4 or the exhaust differential user 6.

According to this embodiment, the exhaust temperature distribution on the CRT device,
The position of the corresponding combustor can be displayed, the combustor with the abnormality can be identified, and an alarm can also be displayed on the CRT screen. Therefore, operators can identify the malfunctioning combustor without inspecting all combustors.

This has the effect of allowing quick maintenance.

Note that the number of temperature sensors (thermocouples) 2 does not necessarily have to be the same as the number of combustors 1, and it is preferable that practical-L is the same number or more.

In the above embodiment, both the position of the combustor and the temperature detected by each thermocouple are displayed as a pie chart on the graphic screen of the CRT device. It may also be displayed as a Cartesian coordinate graph).

[Effects of the Invention] According to the present invention, it is possible to display and warn which of the plurality of combustions H) of the gas turbine is abnormal. Therefore, it helps to quickly maintain the combustor and shorten repair time! It has the excellent effect of being able to do the following.

[Brief explanation of the drawing]

FIG. 1 is a schematic diagram of an embodiment of the present invention. 1... Combustor 2... Exhaust temperature sensor 3...
・CRT device 4...Gas turbine 5...Exhaust duct 6...Exhaust differential user Figure 1

Claims (1)

[Claims] 1. A plurality of exhaust gas temperature detectors arranged annularly in the exhaust gas flow path of a gas turbine including a plurality of annularly arranged combustors, and the temperature detectors as seen from the combustors. a calculating means for calculating the turning angle of the exhaust gas at the position based on the gas turbine operating conditions; and receiving the output of the calculating means and the output of each of the above-mentioned temperature detectors, and displaying the exhaust gas temperature distribution and the above-mentioned turning on the display screen. A monitoring and display device for a gas turbine combustor, comprising a display means for graphically displaying the combustor position in correspondence with the angle-corrected combustor position. 2. The gas turbine combustor monitoring and display device according to claim 1, wherein the graphic display is a pie chart display. 3. The gas turbine combustor monitoring and display device according to claim 1 or 2, wherein gas turbine output, atmospheric temperature, steam injection amount, inlet guide vane opening, and gas turbine exhaust pressure are used as the gas turbine/operating conditions used in the calculation. .