CN116907862A - Method for processing failure of ignition in starting process of gas turbine - Google Patents
Method for processing failure of ignition in starting process of gas turbine Download PDFInfo
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- CN116907862A CN116907862A CN202310955885.XA CN202310955885A CN116907862A CN 116907862 A CN116907862 A CN 116907862A CN 202310955885 A CN202310955885 A CN 202310955885A CN 116907862 A CN116907862 A CN 116907862A
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- 238000000034 method Methods 0.000 title claims abstract description 65
- 230000008569 process Effects 0.000 title claims abstract description 31
- 238000012545 processing Methods 0.000 title claims description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 124
- 239000000446 fuel Substances 0.000 claims abstract description 100
- 239000007789 gas Substances 0.000 claims abstract description 74
- 239000003345 natural gas Substances 0.000 claims abstract description 62
- 238000001514 detection method Methods 0.000 claims abstract description 34
- 230000000903 blocking effect Effects 0.000 claims abstract description 11
- 239000000203 mixture Substances 0.000 claims description 23
- 238000012360 testing method Methods 0.000 claims description 14
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- 238000010248 power generation Methods 0.000 abstract description 4
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- 238000004458 analytical method Methods 0.000 description 8
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- 238000012423 maintenance Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 4
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010892 electric spark Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 239000004020 conductor Substances 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000006089 photosensitive glass Substances 0.000 description 2
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- 230000002035 prolonged effect Effects 0.000 description 1
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- 230000000630 rising effect Effects 0.000 description 1
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- 238000013024 troubleshooting Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
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- General Physics & Mathematics (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a processing method of failure in ignition during starting of a gas turbine, which is characterized in that relevant operation data and operation curves of the gas turbine are analyzed, and by combining failure in ignition information, the blocking states of a rectifier transformer, a flame detection system, natural gas fuel components, a fuel valve and a fuel pipeline are checked by utilizing a fishbone diagram method, so that the failure cause is found out in time and the failure is processed, and the gas turbine is ensured to be started and connected as soon as possible. The failure ignition processing method can be used for carrying out system detection after failure ignition of the gas turbine unit, quickly determining the cause of failure ignition in the starting process of the gas turbine, solving the problem of low detection efficiency in the existing process of relying on manual experience, shortening the starting time of the gas turbine, promoting the running reliability of the unit, and reducing the power generation electricity consumption and the station service electricity rate.
Description
Technical Field
The invention relates to the field of gas turbine power generation, in particular to a method for processing failure in ignition during the starting process of a gas turbine.
Background
The gas turbine unit has the characteristics of high efficiency, energy saving, high start-stop speed and the like, and plays an important role in saving energy, reducing emission and meeting the peak shaving requirement of a power grid. As a gas turbine unit for peak shaving of a power grid, the gas turbine unit has higher requirements on quick and reliable starting of the unit. The ignition of the gas turbine is one of the most critical steps in the starting process of the gas turbine unit, the unit trips due to ignition failure in the starting process of the gas turbine, the unit can enter an ignition program again after the trip after the unit needs to pass through a purging process for about 15 minutes, the grid-connected time delay of the unit is caused, the power generation gas consumption and the station service power consumption are increased, and the economical efficiency is reduced.
When the ignition failure occurs in the gas turbine, the ignition failure cause needs to be rapidly analyzed and effectively processed, but no complete gas turbine starting process ignition failure fault processing method is available at present, the analysis is performed by relying on experience of field personnel, particularly the level of the field personnel is uneven, the fault processing time is prolonged, and the economic loss of a power plant is increased, so that the analysis of the cause of the gas turbine starting ignition failure and the timely processing of faults are particularly important.
Disclosure of Invention
Aiming at the problems existing in the prior art, the invention provides a method for processing the failure in ignition during the starting process of a heavy-duty gas turbine.
The invention is realized by the following technical scheme:
a method for processing failure of ignition failure in the starting process of a gas turbine comprises the following steps:
the failure of ignition of the gas turbine generates fault alarm, the fault is processed according to the output fault information of the gas turbine control system, and when the fault is processed, the fault alarm still exists, the following process is executed;
determining the working state of an ignition system according to the voltage value of the rectifier transformer and a discharge test;
determining an operating state of a flame detection system based on an operating temperature of the gas turbine;
acquiring the current natural gas fuel composition and comparing the current natural gas fuel composition with the historical fuel composition to determine the state of the current natural gas fuel;
acquiring the IGV ignition opening degree when the ignition fails, and determining the stroke drift state of the fuel valve;
acquiring pressure data of a fuel pipeline, and determining the blocking state of the fuel pipeline according to the pressure data;
detecting the blocking state of the rectifier transformer, the flame detection system, the natural gas fuel component, the fuel valve and the fuel pipeline, and stopping detection and restarting the engine when the failure alarm of the ignition failure of the gas turbine is released.
Preferably, the gas turbine control system output fault information includes warning information of pressure overrun before the fuel control valve during ignition to warm-up and warning information that flame cannot be established during ignition.
Preferably, the method for detecting the overrun of the front pressure of the fuel control valve during the period from ignition to warm-up is as follows:
and acquiring a historical operation curve of the gas turbine unit, determining an actual action value of the front pressure of the fuel control valve when the ignition fails according to the historical operation curve, comparing the actual action value of the front pressure with a set threshold value, and determining the state of the fuel control valve.
Preferably, the detection method for the flame failure during ignition is as follows:
and acquiring the command and feedback data of the fuel control valve to determine the response characteristic of the fuel control valve, and determining whether to recalibrate the fuel control valve according to the response characteristic.
Preferably, the faults of the ignition system comprise a point rectifier transformer fault, an ignition electrode fault and an electrode discharge gap fault;
acquiring input voltage and output voltage of a rectifier transformer, and further determining the state of the rectifier transformer;
acquiring voltage of an ignition electrode, and determining the state of the ignition electrode according to the voltage;
and carrying out a discharge test on the ignition electrode, and determining the state of an electrode discharge gap according to a test result.
Preferably, when the voltage of the ignition electrode is 0, the ignition electrode is disconnected, and when the ignition electrode is infinite, the ignition electrode is shorted.
Preferably, the detection method of the flame detection system is as follows:
and acquiring the exhaust temperature and the inter-wheel temperature of the gas turbine, comparing the exhaust temperature and the inter-wheel temperature with historical values, determining the alarm state of the flame detector, performing a light sensation test on the flame detector, and determining the hardware state of the flame detector.
Preferably, the method for detecting the natural gas fuel component comprises the following steps:
the composition of the current natural gas fuel is analyzed and compared with the normal natural gas composition to determine the state of the current natural gas fuel.
Preferably, the detection method of the fuel valve is as follows:
and acquiring the IGV ignition angle, comparing the IGV ignition angle with a set standard IGV ignition angle, and determining the stroke drift state of the fuel valve so as to obtain the state of the fuel valve.
Preferably, the method for detecting the blocking state of the fuel pipeline is as follows:
and acquiring pressure data of the natural gas loop, comparing the pressure data with a pressure value in a normal state, determining a fuel pipeline blocking state, acquiring an internal image of the natural gas loop when the natural gas loop is blocked, and determining the blocking position of the natural gas loop according to the image.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a method for processing failure in ignition during starting of a heavy-duty gas turbine, which is characterized in that relevant operation data and operation curves of the gas turbine are analyzed, and in combination with failure in ignition information, the state of blockage of a rectifier transformer, a flame detection system, natural gas fuel components, a fuel valve and a fuel pipeline is checked by utilizing a fishbone diagram method, so that the failure cause is found out in time, the failure is processed, and the gas turbine is ensured to be started up and connected as soon as possible. The failure ignition processing method can carry out system detection after failure ignition of the gas turbine unit, quickly determine the cause of failure ignition in the starting process of the gas turbine, solve the problem of low detection efficiency by means of manual experience, shorten the starting time of the gas turbine, and have important significance in promoting the running reliability of the unit, reducing the power generation gas consumption and the station service power consumption and improving the economy.
Drawings
FIG. 1 is a fish bone diagram of analysis of failure cause of ignition failure during startup of a gas turbine according to the present invention;
FIG. 2 is a schematic diagram of a method of handling a failed ignition failure during a gas turbine engine start-up process according to the present invention.
Detailed Description
The invention will now be described in further detail with reference to the accompanying drawings, which illustrate but do not limit the invention.
Referring to fig. 1 and 2, a method for handling failure to ignite during start-up of a gas turbine includes the steps of:
and step 1, performing failure alarm on ignition failure in the starting process of the gas turbine, and acquiring failure alarm information on the ignition failure.
The failure alarm information of the ignition failure comprises alarm information of pressure overrun before a fuel control valve during the period from ignition to warming-up and alarm information that flame cannot be established during the period from ignition.
The detection method for the fuel control valve front pressure overrun alarm information during the period from ignition to warming up is as follows:
according to a historical operation curve of the gas turbine unit, acquiring a front pressure actual action value of the fuel control valve when a fault occurs, comparing the front pressure actual action value with a set threshold value, and determining whether the front pressure actual action value exceeds a threshold value range; acquiring the upstream gas supply pressure of the natural gas, comparing the upstream gas supply pressure with a gas supply pressure threshold value, and determining whether the upstream gas supply pressure of the natural gas exceeds a gas supply pressure threshold value range; meanwhile, whether the instruction data and the feedback data of the fuel control valve are normal or not is detected, the parts corresponding to abnormal data are maintained, whether the fault alarm information is released or not is checked, and after maintenance, the fault alarm information still exists, and then the step 2 is executed;
checking the flame detector for alarm information that a flame cannot be established during ignition? It is checked whether the fuel supply system is normal or not, and whether the ignition plug is operating normally or not.
When the flame detector, the fuel supply system and the spark plug are all in a normal state and the fault alarm information still exists, executing the step 2;
when the fault alarm information is released, the standby group can start to ignite again.
And 2, checking the ignition system, acquiring operation data of the ignition system, and determining the fault of the ignition system by combining the normal operation data.
The ignition system faults comprise a rectifier transformer fault, an ignition electrode open circuit or short circuit and incorrect discharge part gap.
The fault determining method of the rectifier transformer comprises the following steps:
1. the rectifier transformer failure includes the ignition transformer not operating and the boost voltage at the outlet is not satisfactory.
And checking and determining the hardware of the rectifier transformer, determining the reason for the non-working of the fire transformer and carrying out corresponding maintenance.
2. The method for determining the open circuit or short circuit of the ignition electrode is as follows:
the voltage value of the ignition electrode is obtained, when the voltage value of the ignition electrode is 0, the ignition electrode can be determined to have an open circuit phenomenon, the open circuit phenomenon is mainly that the ignition electrode is broken in the overhaul of the gas turbine, when the ignition electrode is infinite, the ignition electrode is indicated to have a short circuit phenomenon, the short circuit phenomenon is mainly that other conductors are in contact with the ignition electrode to cause short circuit, the protection of the electrode is required to be enhanced, the damage in the overhaul process is avoided, and after the overhaul of the gas turbine is finished, the outside of the ignition electrode is required to be inspected so as to avoid the contact of the other conductors with the electrode.
3. The method for determining incorrect discharge site gap is as follows:
improper discharge part gap means that the discharge part electrode gap is too large or too small, so that electric arcs are difficult to generate, a discharge test is conducted on an ignition electrode, whether the discharge part gap is normal or not is determined according to generated electric sparks, and the discharge part gap is adjusted when the discharge part gap is abnormal.
Specifically, if the naked eyes can obviously see the electric spark, the gap is qualified, otherwise, adjustment is needed, and at the same time, after the maintenance of the gas turbine is finished, the discharge test is needed again, so that electrode breakage or discharge part gap change caused by improper installation is eliminated.
And (3) executing the step (3) when the ignition system is in a normal state after fault detection or after fault and maintenance occur and fault alarm information still exists.
And step 3, checking the flame detection system, acquiring operation data of the flame detection system, and determining the fault of the ignition system by combining the normal operation data.
The flame detection system faults include flame detector faults and flame amplifier faults.
1. The flame detector fault comprises hardware fault and photosensitive fault, wherein the hardware fault is that when a fire detection probe is installed, the photosensitive glass sheet is damaged, the photosensitive element is polluted, the sensitivity is reduced, and the photosensitive glass sheet is replaced or cleaned according to the detection condition.
2. The photosensitive fault is that the focus of an alignment aperture of a fire detection detector is displaced, and the detection method comprises the following steps:
and (3) performing a light sensation test on the flame detector, and adjusting the alignment aperture according to data of the light sensation test.
3. Flame amplifier faults include short circuit faults or hardware faults.
And acquiring internal insurance fusing information of the flame amplifier through the voltage value, replacing insurance when the fuse is fused, and replacing the flame amplifier if a working indicator lamp of the flame amplifier is not on after the fuse is replaced.
And (4) executing the step (4) when the flame detection system is in a normal state after fault detection or the fault alarm information still exists after fault and maintenance occur.
And 4, checking the natural gas fuel components, obtaining the natural gas fuel components, comparing the natural gas fuel components with the natural gas fuel components in a normal state, and determining the faults of the natural gas fuel components.
The natural gas fuel composition changes, which results in a natural gas amount which is difficult to match well with the air amount at the ignition speed in daily operation to establish stable ignition mixture, and causes ignition failure.
The natural gas fuel composition is analyzed and compared to the normal state natural gas fuel composition to determine if there is a misfire due to a change in natural gas composition, and if the natural gas fuel composition changes, the gas turbine firing rate is redetermined based on the current natural gas fuel composition, e.g., the gas turbine firing rate may be appropriately reduced to reduce the effects of small changes in natural gas composition. Reducing the ignition speed may also reduce interference with the initial flame. Meanwhile, an online analyzer for natural gas components is additionally arranged on the front-end module of the gas turbine, and analysis data are connected into a fuel monitoring system of the gas turbine so as to know the natural gas components in time.
And 5, checking the fuel valve, and determining the fault of the fuel valve according to the opening degree of the IGV.
The fuel valve failures include fuel valve stroke drift and valve installation errors.
The method for determining the fuel valve stroke drift is as follows:
1. the fuel valve stroke drift can cause a large change in the natural gas to air ratio, resulting in misfire. If the IGV opening degree has larger drift, the IGV angle is actually measured on site after the ignition failure fault occurs and is compared with the system display. If a large offset occurs, the angle of the IGV blade should be adjusted; if drift occurs for the diffusion regulating valve opening setting, valve verification can be performed on each regulating valve periodically to eliminate such reasons.
2. The maintenance method for the valve installation errors is as follows:
the valve installation error can cause the natural gas flow to change under the same valve opening degree after the ignition program is started, so that the ratio of the natural gas to the air is greatly changed to cause ignition failure, and the valve is required to be installed again due to the failure.
And when the fuel valve is in a normal state after fault detection or is in fault and maintained, the fault alarm information still exists, and then the step 6 is executed.
And 6, checking the fuel pipeline, obtaining a pressure value of the fuel pipeline, and determining the blockage fault of the fuel pipeline according to the pressure value.
The fuel pipeline is blocked, the natural gas loop is blocked, the natural gas amount entering the burner is greatly reduced to cause ignition failure, so that the pressure of the fuel pipeline can be changed, the pressure pipeline can be determined to be blocked, and meanwhile, on-site technicians can open observation holes on two sides of the loop, and the observation holes are inspected by using an endoscope to determine the blocking point of the fuel pipeline and dredge the fuel pipeline.
If the reasons of the failure of ignition are found through the steps 2 to 6, the failure is treated in time according to the situation. After the treatment is finished, the standby group can be started again. It should be noted that, in the fault checking and processing process, there is no sequence between the steps 2 to 6, and the sequence can be adjusted in the actual execution, but all the steps are required to be completed.
And 7, executing the step after the fuel pipeline blockage fault is detected and is in a normal state, or after the fault occurs and the maintenance is carried out, the fault alarm information still exists.
And 7, checking whether other faults exist.
And when the other faults do not determine the failure cause of the ignition failure in the steps, analyzing the failure cause by combining the related operation data, the operation curve and the abnormal phenomenon until the failure cause of the ignition failure is determined and the faults are processed in time.
Example 1
A method for processing failure of ignition failure in a starting process of a heavy-duty gas turbine comprises the following steps:
step 1, failure ignition alarming occurs in the starting process of the combustion engine, and faults pointed by an alarming interface are timely checked and processed according to the prompt of the failure ignition alarming interface;
specifically, the ignition failure of a certain gas turbine unit in the starting process is known through an analysis alarm interface, the unit is started until the ignition process is normal, flame stability is built, and the unit ignition is successful. But after ignition is successful for 8s, due to the front p of the fuel control valve 2 High protection action jumps. Therefore, the importance of the check processing should be the fuel control valve pre-pressure p during the period from ignition to warmup 2 Why it is overrun.
By referring to the history, the fuel control valve front pressure p is checked 2 The actual action value is used for eliminating the interference of the fault factors of the measuring points; checking the valve command and feedback conditions; an upstream supply pressure of natural gas is checked for an overrun condition. The fuel valve response characteristic was found to be poor and the operation was retarded during the inspection. And the valve is recalibrated by an maintainer and then returns to normal.
After the fault is removed, restarting the engine and igniting successfully.
Example 2
The embodiment is different from embodiment 1 in that the failure cause of ignition failure cannot be accurately determined through the engine alarm interface, and then the failure check is performed one by one according to steps 2 to 6.
Step 2, check ignition system for failure?
Specifically, the input and output of the rectifier transformer after inspection are normal; checking the ignition electrode visually, wherein the ignition electrode is normal; through discharge tests, electric sparks can be seen, which indicates that the gap of the discharge part is normal. The ignition system was confirmed to be normal.
Step 3, check flame detection system for failure?
Specifically, the flame detector is provided with auxiliary judgment on whether the flame detector is normal or not through the change of parameters such as the exhaust temperature of the combustion engine, the temperature between wheels and the like, the temperature is unchanged through the reference of historical data such as the exhaust temperature of the combustion engine, the temperature between wheels and the like, and fire detection faults are basically eliminated. In addition, the flame detector is subjected to a light sensation test, the fire detection probe is inspected, signal shielding is carried out on the wiring of the flame detection signal cable, heat insulation measures are carried out on the signal cable, and short circuit caused by aging of the cable is prevented. The flame detection system was confirmed to be normal.
Step 4, check natural gas fuel composition change?
Specifically, no anomalies were found on inspection of the natural gas supply system. In addition, a natural gas composition analysis report is recalled and compared to the most recent normal natural gas composition analysis report to determine that the natural gas composition has not changed.
Step 5, check fuel valve failure?
Specifically, the IGV ignition angle is re-measured by using an IGV special angle meter, and compared with a system display, the IGV ignition angle is not deviated; zero calibration and full stroke calibration are performed on the diffusion regulating valve, and no offset condition is found. In addition, the valve supply code discovers that the diffusion regulating valve and the premixing regulating valve are wrongly installed when the regulating valve is replaced in a whole set. The internal structures of the diffusion regulating valve and the premixing regulating valve are the same but have slightly different sizes, so that the natural gas flow changes under the same valve opening degree after the ignition program is started, and the ratio of the natural gas to the air is greatly changed to cause ignition failure. After the fuel valve is found to be installed wrongly, the fuel valve is replaced.
Step 6, check fuel pipe is blocked?
Specifically, the natural gas pipeline was inspected with an endoscope to find that the fuel pipeline was not plugged.
And (3) performing fault investigation one by one through the steps 2 to 6. The ignition failure is determined because the fuel valve is replaced in time due to the fact that the ratio of natural gas to air is greatly changed due to the fact that the fuel valve is installed incorrectly. And after restarting the unit, the ignition is successful.
Example 3
If the cause of the failure in ignition is not found in the steps 1 to 6, further troubleshooting is required in the step 7. The working process of the embodiment is as follows:
step 7, check if there are other faults?
Specifically, the operation data of the unit in the case of failure ignition is analyzed, the comparison of the operation data with the aspects of environmental temperature, gas quality, ignition speed and the like is not common, and the only comparison is that the failure ignition is more occurred under the condition of larger environmental humidity. Therefore, the influence of the environmental humidity is emphasized. Through analysis, other ignition failure faults mainly comprise failure units with large ambient humidity, poor drainage effect of diffusion combustion natural gas pipelines and the like.
For the failure reason, the natural gas diffusion pipeline drainage program is manually executed for 1 time before each time of shutdown of the gas turbine, and the drainage process is confirmed to be effective (based on the rising of the pressure and the liquid level in the drainage box), so that no excessive moisture is generated in the drainage to gas turbine shutdown process; the effectiveness of the diffusion pipeline trap was checked by analyzing the diffusion pipeline trap history operating curve, and it was thought necessary to replace the diffusion combustion natural gas pipeline trap, and then the diffusion combustion natural gas pipeline trap was replaced.
After the treatment, the unit is restarted and ignited successfully.
The above is only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited by this, and any modification made on the basis of the technical scheme according to the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (10)
1. The method for processing the failure of ignition in the starting process of the gas turbine is characterized by comprising the following steps of:
the failure of ignition of the gas turbine generates fault alarm, the fault is processed according to the output fault information of the gas turbine control system, and when the fault is processed, the fault alarm still exists, the following process is executed;
determining the working state of an ignition system according to the voltage value of the rectifier transformer and a discharge test;
determining an operating state of a flame detection system based on an operating temperature of the gas turbine;
acquiring the current natural gas fuel composition and comparing the current natural gas fuel composition with the historical fuel composition to determine the state of the current natural gas fuel;
acquiring the IGV ignition opening degree when the ignition fails, and determining the stroke drift state of the fuel valve;
acquiring pressure data of a fuel pipeline, and determining the blocking state of the fuel pipeline according to the pressure data;
detecting the blocking state of the rectifier transformer, the flame detection system, the natural gas fuel component, the fuel valve and the fuel pipeline, and stopping detection and restarting the engine when the failure alarm of the ignition failure of the gas turbine is released.
2. The method for processing a failure to fire during a start-up of a gas turbine according to claim 1, wherein the failure information output by the gas turbine control system includes an alarm of an excessive pressure before the fuel control valve during ignition to warm-up and an alarm that a flame cannot be established during ignition.
3. The method for handling failed ignition in a gas turbine engine start-up process according to claim 2, wherein the method for detecting an overrun in fuel control valve front pressure during the period from ignition to warm-up is as follows:
and acquiring a historical operation curve of the gas turbine unit, determining an actual action value of the front pressure of the fuel control valve when the ignition fails according to the historical operation curve, comparing the actual action value of the front pressure with a set threshold value, and determining the state of the fuel control valve.
4. The method for handling failure to ignite during start-up of a gas turbine according to claim 2, wherein said method for detecting failure to establish a flame during ignition comprises:
and acquiring the command and feedback data of the fuel control valve to determine the response characteristic of the fuel control valve, and determining whether to recalibrate the fuel control valve according to the response characteristic.
5. The method for handling failed ignition faults during start-up of a gas turbine according to claim 1, wherein said faults of the ignition system include a point rectifier transformer fault, an ignition electrode fault and an electrode discharge gap fault;
acquiring input voltage and output voltage of a rectifier transformer, and further determining the state of the rectifier transformer;
acquiring voltage of an ignition electrode, and determining the state of the ignition electrode according to the voltage;
and carrying out a discharge test on the ignition electrode, and determining the state of an electrode discharge gap according to a test result.
6. The method for processing failure to ignite a gas turbine engine according to claim 5, wherein the voltage of the ignition electrode is 0, the ignition electrode is disconnected, and the ignition electrode is shorted when the ignition electrode is infinite.
7. The method for handling failed ignition in a gas turbine engine start-up process of claim 1, wherein said flame detection system comprises the following steps:
and acquiring the exhaust temperature and the inter-wheel temperature of the gas turbine, comparing the exhaust temperature and the inter-wheel temperature with historical values, determining the alarm state of the flame detector, performing a light sensation test on the flame detector, and determining the hardware state of the flame detector.
8. The method for handling failed ignition in a gas turbine engine start-up process of claim 1, wherein the method for detecting natural gas fuel composition comprises:
the composition of the current natural gas fuel is analyzed and compared with the normal natural gas composition to determine the state of the current natural gas fuel.
9. The method for handling failed ignition in a gas turbine engine start-up process of claim 1, wherein the method for detecting a fuel valve comprises:
and acquiring the IGV ignition angle, comparing the IGV ignition angle with a set standard IGV ignition angle, and determining the stroke drift state of the fuel valve so as to obtain the state of the fuel valve.
10. The method for handling failed ignition in a gas turbine engine start-up process of claim 1, wherein the method for detecting a blocked fuel line condition comprises:
and acquiring pressure data of the natural gas loop, comparing the pressure data with a pressure value in a normal state, determining a fuel pipeline blocking state, acquiring an internal image of the natural gas loop when the natural gas loop is blocked, and determining the blocking position of the natural gas loop according to the image.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310955885.XA CN116907862A (en) | 2023-07-31 | 2023-07-31 | Method for processing failure of ignition in starting process of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310955885.XA CN116907862A (en) | 2023-07-31 | 2023-07-31 | Method for processing failure of ignition in starting process of gas turbine |
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