JPS61197725A - Automatic monitor for starting system in internal-combustion engine - Google Patents

Abstract

PURPOSE:To grasp causes of failure in starting by discriminating abnormality generating portions on the basis of the signals from fuel flow and turbine inlet temperature detecting means before rated rotational frequency is reached after rated starting time. CONSTITUTION:When a command is given to a starting compressor 6, a pneumatic starter 3 begins to rotate the rotatably drive a compressor 1a and a turbine 1b. After rated starting time, when the rotational frequency detected by a rotational frequency detecting means 5 does not reach the rated rotational frequency, a discriminating means 20 discriminates abnormality generating portions on the basis of signals of fuel flow and turbine inlet temperature detecting means 9, 7. Thus, causes of failure in starting can be immediately grasped.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an automatic monitoring device for a starting system in an internal combustion engine, such as a gas turbine.

[Conventional technology]

FIG. 4 is a diagram showing an example of a conventional automatic monitoring device for a gas turbine starting system.
2 is a gas turbine that receives compressed air from the compressor 1a, 11), and a reducer is rotationally driven by a pneumatic starter 3; compressor 1a.

A pneumatic starter that rotationally drives the gas turbine 1b.

4 is a generator disposed coaxially with the compressor 1a, turbine 1b, and reducer 2, and is driven to rotate depending on the output from the turbine 1b; 5Fi is attached to the reducer 2 and controls the speed of the reducer 20; The rotational speed detecting means for detecting and outputting the rotational speed, ie, the tachogenerator 6, is a starting compressor that sends compressed air to the pneumatic starter.

A conventional gas turbine starting system is configured as described above, and when starting a gas turbine engine, first compressed air for starting is sent to the pneumatic starter 3 from the starting compressor 6, and the pneumatic starter 3 is rotated, and the power is transmitted to the turbine shaft through the rotary workpiece speed reducer 2t-. When the compressor 1a and the turbine 1b are driven by the rotation of the turbine shaft, compressed air is supplied from the compressor 1a to the turbine 1b, and at the same time, fuel is supplied from the fuel supply system to the turbine 1b. In particular, the fuel was ignited in the turbine 1b, and the gas turbine engine was put into operation. Note that when the gas turbine engine enters the operating state, the supply of compressed air from the starting compressor 6 to the pneumatic starter 3 is stopped.

In the automatic monitoring device for the gas turbine starting system described above, an electronic circuit control device such as a microcomputer is provided in order to confirm the starting state of the engine.
Based on the detection signal output from the tachogenerator 5, the control device determines whether or not the engine speed has exceeded a certain number of revolutions, and as a result of # determination, it has been recognized that the number of revolutions has exceeded a certain number. After a certain period of time has elapsed from this point, the detection signal from the front ffi/cosienerator 5 is read again to determine whether the starting condition of the engine is good or not.

[Problem that the invention seeks to solve]

By the way, in the automatic monitoring device of the conventional gas turbine starting system as described above, if the detected value output from the tachogenerator 5 reaches the rated rotational speed of the gas turbine engine, the control device will start the engine successfully. If the detected value does not reach the rated rotation speed, it is assumed that the starting operation has not been performed normally, and it is determined that the starting operation has failed (starting congestion). It wasn't. Although it is possible to determine whether the start has been successful or failed, there is a problem in that when it is determined that the start has failed, it is not possible to immediately determine the cause.

The present invention was made to solve such problems, and an object of the present invention is to provide an automatic monitoring system for a gas turbine starting system that can immediately identify the cause of a starting failure when it is determined that the starting failure has occurred. .

[Means for solving problems]

An automatic monitoring device for a starting system in an internal combustion engine according to the present invention includes a fuel flow rate detection means for detecting a fuel flow rate flowing into a turbine from a fuel nozzle, and a temperature detection means for detecting an inlet temperature of the turbine.

When the detected value given from the rotation speed detection means and the rotation speed detection means after the rated starting time has not reached the rated rotation speed, the fuel flow rate detection means and the temperature detection means detect the rotation speed. Identifies the location where an abnormality occurs during startup based on the detection signal of the means.

□Identification means.

[Function] □ In this invention, when the rotation speed detection means outputs a detected value that does not reach the rated rotation speed after the lapse of the rated starting time,
The identification means reads the detection signals from the fuel flow rate detection means and the temperature detection means, and based on these detection signals, identifies where the abnormality that caused the startup failure has occurred.

゛ [Example] Hereinafter, one embodiment of the present invention will be described.

FIG. 1 is an overall configuration diagram of an automatic monitoring device for a gas turbine starting system according to the present invention. As is clear from FIG. 1, this embodiment includes a fuel flow rate detection means 8 for detecting the fuel flow rate flowing into the turbine 1b, and a temperature detection means 8 for detecting the inlet temperature of the turbine 1b. a detection means 1; the turbine; 1. rotation speed detection means 5 for detecting the rotation speed of b, and when the identification means 20 recognizes that the detected value given from the hind limb rotation speed detection means 5 has not reached the rated rotation speed , *It is configured to identify the location where an abnormality occurs at the time of starting based on the detection and signals from the fuel flow rate detection means 9 and the temperature detection means T.

FIG. 2 is a schematic diagram of an automatic monitoring device for a gas turbine starting system used in the embodiment shown in FIG. 1, and 1a to 6 are identical to the conventional device described above.

Reference numeral 7 denotes a temperature detecting means, that is, a turbine inlet temperature detecting device, which is provided at the inlet of the turbine 1b. Reference numeral 8 denotes a fuel nozzle for supplying fuel to the turbine 1b, and 9 is provided in the fuel nozzle FL/8. This is a fuel flow rate detection means for detecting the supplied fuel flow rate, that is, a fuel nozzle inlet flowmeter.

The detection signals outputted from the tachogenerator 5, the turbine inlet temperature detection device T, and the fuel nozzle inlet flow meter 9 described above are applied to an identification means 20, that is, a control unit 20 having a built-in electronic circuit control device such as a microcomputer. Ran. A CPU built into the control unit 20 performs arithmetic and logical operations and comparison operations. Examples of the input information given to the CPU include the following: turbine engine rotation speed information outputted from the generator 5, turbine inlet temperature information outputted from the turbine inlet temperature detection device 7, and fuel nozzle inlet flow meter. 9 outputs fuel flow rate information, etc.

When the CPU receives rotation speed information from the tachogenerator 5 that does not reach the rated starting rotation speed after the rated starting time has elapsed, the CPU reads the turbine inlet temperature information and fuel flow rate information and controls the flow rate to the compressor 1a and the turbine 1b. Determine fuel inflow status. The display output of the CPU is given to one display device 21. The control unit 20 includes a CPU and a storage section, and the storage section contains a control program and stores necessary data. The data stored in the storage section includes, for example, rated starting rotation speed data of the turbine engine, rated starting time data, turbine inlet temperature reference value data, fuel flow rate reference value data, and the like.

The control operation of the above configuration will be explained below mainly with reference to the flowchart shown in FIG.

From the CPU of the control unit 20 to the starting compressor 6
When a drive command signal is outputted to n and the pneumatic starter 3 starts rotating, the rotation of the starter 3 also drives the compressor 1a and the gas turbine 1b to rotate (step 10). As the rotational speed of the gas turbine 1b increases, the rotational speed detection value from the tachogenerator 5 increases, and when compared with the rated starting rotational speed data stored in the storage unit, the detected value reaches the rated value. KotoIk:ia! When it is recognized (step 11), the process moves to step 12. In step 11, after recognizing that the rotation speed detection value that reached the rated starting rotation speed has been output from the tachogenerator 5, it is determined whether the rated starting time has elapsed or not.In step 12), it is determined whether the rated starting time has elapsed. When this is recognized, the process moves to step 13. In step 12, the CPU reads the detected rotational speed value from the tachogenerator 5 at the time when the rated starting time has elapsed, compares the rated value and the detected value in the same way as in step 11, and determines that the detected value is the rated value. It is determined whether or not this has been reached (step 13).

When it is recognized in step 13 that the detected value has reached the rated value, it is determined that the start has been completed and the display is output to the display device 21 (step 14), but when it is recognized that the detected value is not different from the rated value Determined to be a startup failure and proceeded to step 15.
to move to. The CPU reads the detected fuel flow rate output from the fuel nozzle inlet flow meter 9, and compares it with the fuel flow reference value data stored in the storage section (step 15).
When it is recognized that the detected value has not reached the reference value, it is determined that there is an abnormality in the fuel supply system, and a display command signal is output to the display device 21 (step 17). When the CPU recognizes that the inlet temperature has exceeded the reference value, the CPU reads the inlet temperature detection value output from the turbine inlet temperature detection device 7, compares it with the turbine inlet temperature reference value stored in the storage unit (step 16), and determines the detected value. compressor 1 when it recognizes that it has not reached the standard value.
It is determined that the compression failure has occurred due to the abnormality in a, and a command signal is output to the display device 21 to indicate that the compressor abnormality is to be displayed (step 18). When it is recognized in step 16 that the detected inlet temperature value exceeds the inlet temperature reference value, it is determined that an abnormality has occurred in the turbine 1b, and a command signal is output to the display device 21 to indicate that the turbine abnormality is to be displayed (step 19 ).

By the way, in the above description, an automatic monitoring device for a gas turbine starting system was described, but the present invention can also be applied to other diesel equipment having the same engine.

〔Effect of the invention〕

As described above, according to the present invention, when the detected value given by the rotation speed detection means after the lapse of the rated starting time has not reached the rated rotation speed, the identification means detects the fuel flow rate detection value and the temperature detection value. Since the location where an abnormality occurs during starting is identified based on the above, an automatic monitoring device for a starting system in an internal combustion engine can be obtained that can immediately identify the cause of a starting failure when it is determined that the starting has failed.

[Brief explanation of the drawing]

FIG. 1 is an overall configuration diagram of an embodiment of an automatic monitoring device for a starting system in an internal combustion engine according to the present invention, FIG. 2 is a schematic diagram of an automatic monitoring device for a starting system in an internal combustion engine according to the present invention, and FIG. FIG. 2 is a flowchart of the configuration, and FIG. 4 is a schematic diagram of a conventional automatic monitoring device for a starting system in an internal combustion engine (gas turbine) K. In the figure, 1b is a turbine, 5 is a rotation speed detection device (tachogenerator), 7 is a turbine inlet temperature detection device, and 8
9 is a fuel nozzle, 9 is a fuel nozzle inlet flow meter, and 20 is a control unit. Note that the same reference numerals in each figure indicate the same or corresponding parts. 8; Noa CIL/ Figure 2

Claims (1)

[Claims] a fuel flow rate detection means for detecting the fuel flow rate flowing into the turbine from the fuel nozzle; a temperature detection means for detecting the inlet temperature of the turbine; a rotation speed detection means for detecting the rotation speed of the turbine; After that, when it is recognized that the detected value given by the rotational speed detection means does not reach the rated rotational speed, the detection value given from the fuel flow rate detection means and the temperature detection means is determined based on the detection signal given from the fuel flow detection means and the temperature detection means. An automatic monitoring device for a starting system in an internal combustion engine, comprising identification means for identifying a location where an abnormality has occurred.