Combustion stability adjusting system of gas turbine

Abstract

The invention discloses a combustion stability adjusting system of a gas turbine, relates to the technical field of gas turbines, and solves the problem that the original mode of adjusting stability according to a single parameter is relatively large in error, the rotating speed of an impeller is monitored in real time through a parameter monitoring end, and is compared with a set rotating speed; the abnormal operation state of the gas turbine can be quickly and accurately recognized, abnormal signals can be generated in time, time is gained for subsequent adjustment, equipment faults caused by unstable combustion are avoided, the timeliness and accuracy of system fault early warning are greatly improved, the air compression ratio is dynamically adjusted according to the abnormal rotation speed index for the abnormal operation situation, and the working efficiency is improved. And by constructing a standard feature model, comprehensively considering the rotating speed fluctuation amplitude and the adjacent moment change value and scientifically selecting the optimal air compression ratio, it is ensured that the gas turbine runs at the stable rotating speed, the running efficiency and stability of the gas turbine are effectively improved, and the risk of unstable combustion caused by the improper air compression ratio is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly to a combustion stability regulation system for a gas turbine. Background Art

[0002] In the field of energy and power, as an efficient power conversion device, gas turbines are widely used in many scenarios such as power generation, aerospace, and industrial drive. However, during the operation of gas turbines, combustion stability is a key factor affecting their performance, efficiency, and reliability. Traditional methods for regulating the combustion stability of gas turbines mostly rely on control strategies with fixed parameters or the empirical judgment of operators, and it is difficult to accurately adapt to the dynamic changes of gas turbines under complex working conditions.

[0003] In the prior art, the monitoring and regulation of the rotational speed of gas turbines are relatively rough, and only simple threshold alarms can be achieved. It is impossible to accurately identify abnormal combustion states through changes in rotational speed; in terms of the regulation of air compression ratio and fuel intake, there is a lack of a systematic collaborative optimization mechanism, and usually only single parameters are adjusted. It is impossible to comprehensively consider multi-dimensional factors such as the fluctuation amplitude and change trend of rotational speed, resulting in poor regulation effects and easily causing unstable phenomena such as combustion oscillation and flameout, which in turn lead to problems such as equipment failures, energy waste, and increased pollutant emissions. With the growth of energy demand and the continuous improvement of requirements for the operating stability and economy of equipment, there is an urgent need for a combustion stability regulation system that can monitor in real time, analyze intelligently, and regulate accurately to ensure the efficient and stable operation of gas turbines. Summary of the Invention

[0004] In view of the deficiencies of the prior art, the present invention provides a combustion stability regulation system for a gas turbine, which solves the problem of large errors in the original method of adjusting stability based on a single parameter.

[0005] To achieve the above objectives, the present invention is realized through the following technical solutions: A combustion stability regulation system for a gas turbine, comprising:

[0006] A parameter monitoring terminal, which monitors the rotational speed associated with the impeller of the gas turbine in real time, and based on the real-time monitored impeller rotational speed, evaluates whether the gas turbine is operating normally. The specific method is as follows:

[0007] Calibrate the set impeller rotational speed as Z, and then calibrate the real-time monitored rotational speed as S i , where i represents the corresponding moment;

[0008] Compare the real-time monitored rotational speed S i with the calibrated Z for verification, and identify whether the rotational speed S i meets the requirement: S i∈[Z - X1, Z + X1], where X1 is a preset value. If it is satisfied, continuous monitoring is carried out. If not, an abnormal operation signal of the gas turbine is generated and the generated abnormal operation signal of the gas turbine is transmitted into the feature regulation end;

[0009] The feature regulation end, in response to the abnormal operation of the gas turbine, adjusts the air compression ratio of the gas turbine. According to the comprehensive manifestation of the impeller speed after adjustment, the optimal air compression ratio is selected. The specific method is as follows:

[0010] Calibrate the air compression ratio associated with the moment of the abnormal operation signal of the gas turbine as Yb, and identify the speed S i And the abnormal index in the preset interval. If S i Exceeds the preset interval, it represents that there is an abnormal overstate index. If S i Is lower than the preset interval, it represents that there is an abnormal understate index;

[0011] If there is an abnormal overstate index, adjust Yb downward. If there is an abnormal understate index, adjust Yb upward until the adjusted speed S i ∈[Z - X1, Z + X1] and then stop;

[0012] After completing the adjustment process, change the air compression ratio again. After the change is completed, confirm a set of monitoring periods. The monitoring period is a preset period. Determine the speed curve generated by the impeller within the monitoring period. Determine the maximum speed and the minimum speed from the speed curve. Based on the maximum speed and the minimum speed, select the curve feature T1, where T1 = maximum speed - minimum speed. And confirm the speed change value between adjacent moments from the speed curve. The speed change value = |speed at the next moment - speed at the previous moment|. Then select the maximum value from several groups of speed change values as the curve feature T2 of this speed curve. Use: standard feature = T1×C1 + T2×C2 to confirm the standard feature belonging to this speed curve, where C1 and C2 are both preset fixed coefficient factors;

[0013] Adopt the same processing method for the standard feature of the speed curve to confirm the speed curve associated with the next set of monitoring periods and synchronously confirm the corresponding standard feature;

[0014] If the standard feature becomes smaller, continue to change. If the standard feature becomes larger, make the air compression ratio change in the reverse direction. During the change process, it is necessary to control S i Always satisfy: S i ∈[Z - X1, Z + X1]. Select the minimum value associated with the standard feature from several groups of change processes. Denote the air compression ratio associated with the minimum value as the optimal air compression ratio and transmit it into the execution center;

[0015] The parameter analysis terminal determines a set of analysis periods and determines the rotational speed fluctuation characteristics associated with the impeller within the analysis periods. The specific method is as follows:

[0016] Based on the adjustment completion signal, a set of analysis periods are determined. The analysis period is a preset period. The impeller rotational speeds associated with different moments within the analysis periods are determined, and a fluctuation curve regarding the impeller rotational speed is generated.

[0017] Lock the fluctuation points from the fluctuation curve. The trend directions of the line segments before and after the fluctuation points are opposite. Calibrate the partial wavebands between adjacent fluctuation points, and from the multiple sets of calibrated partial wavebands, determine the rotational speed change values at adjacent moments. Assume the rotational speed at the previous set of moments is ZA1, and the rotational speed at the next set of moments is ZA2. Use rotational speed change value = ZA2 - ZA1, perform mean processing on the several sets of rotational speed change values associated with a single set of partial wavebands, confirm the characteristic mean value associated with the corresponding single set of partial wavebands, and calibrate the different characteristic mean values associated with different partial wavebands as JZ k , where k represents different partial wavebands;

[0018] From the confirmed several sets of characteristic mean values, select the minimum characteristic mean value JZ k min and the maximum characteristic mean value JZ k max. Use: JSmax = JZ k min × A1 and JSmin = JZ k max × A1 to determine the minimum control characteristic JSmin and the maximum control characteristic JSmax, where A1 is a preset fixed coefficient factor;

[0019] Based on the determined minimum control characteristic JSmin and the maximum control characteristic JSmax, confirm a set of control intervals [JSmin, JSmax]. During subsequent monitoring processes, control the trend of the fuel intake to change within the control interval. If the rotational speed is greater than Z, control the trend to change downward and stop when the rotational speed is less than Z. If the rotational speed is less than Z, control the trend to change upward and stop when the rotational speed is greater than Z. From the trend change process, determine the single change time and identify the difference between the front and back of the single change time. The difference between the front and back is ≥0. If the difference between the front and back is ≤0.2 seconds, record the rotational speed fluctuation characteristics.

[0020] The real-time control terminal, based on the recorded rotational speed fluctuation characteristics, performs real-time control on the fuel feeding trend of the gas turbine and re-controls the stability of the impeller rotational speed generated by the gas turbine.

[0021] Preferably, the execution center adjusts the original air compression ratio of the gas turbine to this value according to the confirmed optimal air compression ratio. After completing the adjustment process of the optimal air compression ratio, the execution center generates an adjustment completion signal and transmits the generated adjustment completion signal to the parameter analysis terminal.

[0022] Preferably, the rotational speed fluctuation characteristics include specific regulation characteristics with an upward trend and regulation characteristics with a downward trend, and the specific durations of the upward trend change and the downward trend change are confirmed.

[0023] Preferably, the specific method for the real-time regulation terminal to re-control the gas turbine is as follows:

[0024] Based on the recorded rotational speed fluctuation characteristics, after the previous set of trend regulations is completed, based on the recorded specific regulation characteristics of the upward trend change and the downward trend change, the fuel feeding trend is regulated in real time, and the specific regulation duration is the recorded specific durations of the upward trend change and the downward trend change.

[0025] The present invention provides a gas turbine combustion stability regulation system. Compared with the prior art, it has the following beneficial effects:

[0026] By the parameter monitoring terminal, the present invention monitors the impeller rotational speed in real time and compares it with the set rotational speed, can quickly and accurately identify the abnormal operating state of the gas turbine, generate an abnormal signal in time, gain time for subsequent regulation, avoid equipment failures caused by unstable combustion, and greatly improve the timeliness and accuracy of system fault warning;

[0027] For abnormal operating conditions, the characteristic regulation terminal dynamically adjusts the air compression ratio according to the rotational speed abnormality index, and by constructing a standard characteristic model, comprehensively considers the rotational speed fluctuation amplitude and the change value at adjacent moments, and scientifically selects the optimal air compression ratio to ensure the gas turbine operates at a stable rotational speed, effectively improving the operating efficiency and stability of the gas turbine, and reducing the risk of unstable combustion caused by improper air compression ratio;

[0028] After the execution center accurately executes the determined optimal air compression ratio, the parameter analysis terminal and the real-time regulation terminal carry out in-depth regulation in relay. The parameter analysis terminal determines the rotational speed fluctuation characteristics and constructs a fuel intake regulation interval, and the real-time regulation terminal based on this re-controls the fuel feeding trend in real time, forming a collaborative regulation closed loop from the air compression ratio to the fuel intake, further enhancing the operating stability of the gas turbine, effectively reducing the rotational speed fluctuation, ensuring a smooth and efficient combustion process, reducing energy consumption and pollutant emissions, extending the service life of the gas turbine, and improving the overall operating economy and reliability. Description of the Drawings

[0029] Figure 1This is a schematic diagram of the principle framework of the present invention. Specific embodiments

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0031] The first embodiment

[0032] Please refer to Figure 1 , this application provides a gas turbine combustion stability regulation system, including a parameter monitoring end, a feature regulation end, an execution center, a parameter-feature analysis end, and a real-time regulation end. The parameter monitoring end is electrically connected to the input nodes of the feature regulation end or the parameter-feature analysis end respectively, and the feature regulation end, the execution center, and the parameter-feature analysis end are electrically connected in sequence from the output node to the input node, and the parameter-feature analysis end and the real-time regulation end are electrically connected from the output node to the input node;

[0033] Among them, the parameter monitoring end monitors the rotational speed associated with the gas turbine impeller in real time, and based on the real-time monitored rotational speed of the impeller, evaluates whether the gas turbine is operating normally, generates the associated operating signal, and transmits the real-time monitored operating signal into the feature regulation end. When it starts to operate, its rotational speed belongs to the set rotational speed. In the actual regulation process, it is necessary to control the rotational speed of the impeller to operate in a constant state, that is, to keep the corresponding air compression ratio and the gas intake per unit time both constant, to monitor the rotational speed of the impeller in real time, so as to achieve a better monitoring effect;

[0034] Among them, the specific method of evaluation is:

[0035] Calibrate the set rotational speed of the impeller as Z (that is, the rotational speed set by the corresponding operator, which is the corresponding rotational speed that the gas turbine needs to reach), and then calibrate the real-time monitored rotational speed as S i , where i represents the corresponding moment;

[0036] Compare the real-time monitored rotational speed S i with the calibrated Z for verification, and identify whether the rotational speed S i meets: S i∈[Z - X1, Z + X1], where X1 is a preset value, and its specific value is determined by the operator according to experience. If it is satisfied, continuous monitoring is carried out. If not, an abnormal operation signal of the gas turbine is generated and transmitted to the feature regulation end. Among them, when the specific monitored speed is within the corresponding interval, it means that the corresponding gas turbine is operating normally. Otherwise, it means that the corresponding gas turbine is operating abnormally. When operating with all parameters in the calibrated state, if the generated speed far exceeds the set specific speed, it means there are specific problems that require feature regulation.

[0037] For the feature regulation end, in case of abnormal operation of the gas turbine, it adjusts the air compression ratio of the gas turbine. According to the comprehensive manifestation of the impeller speed after adjustment, the optimal air compression ratio is selected and the selected optimal air compression ratio is executed through the execution center. The specific method for selection is as follows:

[0038] Calibrate the air compression ratio associated with the abnormal operation signal of the gas turbine at the corresponding moment as Yb, and identify the speed S i And the abnormal index of the preset interval. If S i Exceeds the preset interval, it means there is an abnormal overstate index. If S i Is lower than the preset interval, it means there is an abnormal understate index;

[0039] If there is an abnormal overstate index, adjust Yb downward. If there is an abnormal understate index, adjust Yb upward until the adjusted speed S i ∈[Z - X1, Z + X1] and then stop;

[0040] After completing the adjustment process, change the air compression ratio again (either upward or downward). After the change is completed, confirm a monitoring period, and the monitoring period is a preset period, generally taking 1 min. Determine the speed curve generated by the impeller within the monitoring period (the horizontal axis of this curve is the time line, and the vertical axis is the corresponding speed parameter. The speed parameters corresponding to different time points are different, so a corresponding speed curve will be generated). Determine the maximum speed and the minimum speed from the speed curve. Based on the maximum speed and the minimum speed, select the curve feature T1, where T1 = maximum speed - minimum speed. And confirm the speed change value between adjacent moments from the speed curve, where the speed change value = |speed at the latter moment - speed at the former moment|. Then select the maximum value from several groups of speed change values as the curve feature T2 of this speed curve. Use: standard feature = T1 × C1 + T2 × C2 to confirm the standard feature belonging to this speed curve, where C1 and C2 are both preset fixed coefficient factors, and their specific values are determined by the operator according to experience;

[0041] Adopt the same processing method for the standard characteristics of the rotational speed curve, confirm the rotational speed curve associated with the next monitoring period, and synchronously confirm the corresponding standard characteristics;

[0042] If the standard characteristic becomes smaller, it continues to change. If the standard characteristic becomes larger, the air compression ratio is changed in the reverse direction. During the change process, S needs to be controlled i Always satisfy: S i ∈[Z - X1, Z + X1]. From several groups of change processes, select the minimum value associated with the standard characteristic, record the air compression ratio associated with the minimum value as the optimal air compression ratio, and transmit it to the execution center.

[0043] The execution center adjusts the original air compression ratio of the gas turbine to this value according to the confirmed optimal air compression ratio. After the execution center completes the adjustment process of the optimal air compression ratio, it generates an adjustment completion signal and transmits the generated adjustment completion signal to the parameter analysis terminal, ensuring that the gas turbine is in the optimal operating state and not affected by the specific air compression ratio, facilitating the subsequent actual combustion process to achieve the optimal combustion treatment effect. And in this numerical state, the corresponding rotational speed fluctuation is in the lowest state, which can initially guarantee its stability.

[0044] Among them, the parameter analysis terminal, based on the received adjustment completion signal, re - determines a set of analysis periods and determines the rotational speed fluctuation characteristics associated with the impeller within the analysis period. In this determination process, it is to facilitate the subsequent regulation of the unit intake of the gas volume to ensure the actual regulation process. The specific method for determining the characteristics is as follows:

[0045] Based on the adjustment completion signal, determine a set of analysis periods. The analysis period is a preset period, which is determined by the operator in advance according to experience, generally taking 3 minutes. Determine the impeller rotational speeds associated with different times within the analysis period and generate a fluctuation curve of the impeller rotational speed. The horizontal axis of the fluctuation curve is the time line, and the vertical axis is the rotational speed value;

[0046] Lock the fluctuation points from the fluctuation curve. The trend directions of the line segments before and after the fluctuation points are opposite. For the marked fluctuation points, when the front - end fluctuation segment trends upward, the trend of the rear - end fluctuation segment is downward; when the front - end fluctuation segment trends downward, the trend of the rear - end fluctuation segment is upward. Mark the partial wave segments between adjacent fluctuation points, and from the marked multiple groups of partial wave segments, determine the rotational speed change values at adjacent times. Assume the rotational speed at the previous group of times is ZA1, and the rotational speed at the next group of times is ZA2. Use rotational speed change value = ZA2 - ZA1, perform mean processing on the several groups of rotational speed change values associated with a single group of partial wave segments, confirm the characteristic mean value associated with the corresponding single group of partial wave segments, and mark the different characteristic mean values associated with different partial wave segments as JZ k, where k represents different partial frequency bands;

[0047] From several groups of confirmed characteristic means, select the minimum characteristic mean JZ k min and the maximum characteristic mean JZ k max, and adopt: JSmax = JZ k min × A1 and JSmin = JZ k max × A1 to determine the minimum value JSmin of the regulation characteristic and the maximum value JSmax of the regulation characteristic, where A1 is a preset fixed coefficient factor, and its specific value is determined by the operator according to experience, and generally takes the value (-1.763);

[0048] Based on the determined minimum value JSmin of the regulation characteristic and the maximum value JSmax of the regulation characteristic, confirm a set of regulation intervals [JSmin, JSmax]. In the subsequent monitoring process, control the trend of the fuel feed rate to change within the regulation interval. If the rotational speed is greater than Z, control the trend to change downward and stop when the rotational speed is less than Z. If the rotational speed is less than Z, control the trend to change upward and stop when the rotational speed is greater than Z. From the process of trend change, determine the single change time (that is, the single time when the trend becomes larger or the single time when the trend becomes smaller), identify the difference before and after the single change time, and the difference before and after is ≥0. If the difference before and after is ≤0.2 seconds, record the rotational speed fluctuation characteristics;

[0049] The rotational speed fluctuation characteristics include the specific regulation characteristics of the upward trend change and the regulation characteristics of the downward trend change, and confirm the specific duration of the upward trend change and the specific duration of the downward trend change;

[0050] Its real-time regulation end, based on the recorded rotational speed fluctuation characteristics, performs real-time regulation on the fuel feeding trend of the gas turbine, and re-controls the stability of the impeller rotational speed generated by the gas turbine, so as to achieve a more stable regulation effect. The specific method of re-control is as follows:

[0051] Based on the recorded rotational speed fluctuation characteristics, after the previous group of trend regulations is completed, based on the specific regulation characteristics of the upward trend change and the downward trend change recorded, perform real-time regulation on the fuel feeding trend, and the specific duration of the regulation is the specific duration of the upward trend change and the downward trend change recorded.

[0052] Some data in the above formula are all numerically calculated after removing their dimensions, and the content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0053] The above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present invention can be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention.

Claims

1. A gas turbine combustion stability regulation system, characterized in that Including: A parameter monitoring end that monitors the rotational speed associated with the gas turbine impeller in real time and evaluates whether the gas turbine is operating normally based on the real-time monitored impeller rotational speed; A characteristic regulation end that adjusts the air compression ratio of the gas turbine in case of abnormal operation of the gas turbine and selects the optimal air compression ratio according to the comprehensive manifestation of the impeller rotational speed after adjustment; A parameter-characteristic analysis end that determines a set of analysis periods and determines the rotational speed fluctuation characteristics associated with the impeller within the analysis periods; A real-time regulation end that, based on the recorded rotational speed fluctuation characteristics, regulates the fuel feeding trend of the gas turbine in real time and re-controls the stability of the impeller rotational speed generated by the gas turbine.

2. The combustion stability regulation system of a gas turbine according to claim 1, characterized in that, The specific method for the parameter monitoring end to evaluate whether the gas turbine is operating normally is: Calibrate the set impeller speed as Z, and then calibrate the speed monitored in real time as S i , where i represents the corresponding moment; Compare the real-time monitored rotational speed S i with the calibrated Z for verification, and identify the rotational speed S i to determine whether it satisfies: S i ∈[Z - X1, Z + X1], where X1 is a preset value. If it satisfies, continue to monitor; if not, generate an abnormal operation signal of the gas turbine and transmit the generated abnormal operation signal of the gas turbine to the characteristic regulation terminal.

3. A gas turbine combustion stability regulation system according to claim 2, characterized in that, The specific method for the characteristic regulation end to adjust the air compression ratio of the gas turbine is: Calibrate the air compression ratio associated with the abnormal signal of the gas turbine operation at the corresponding moment as Yb, and identify the rotational speed S i and the abnormal indicators within the preset range. If S i exceeds the preset range, it represents the existence of abnormal overstate indicators. If S i is lower than the preset range, it represents the existence of abnormal understate indicators; If there is an abnormal overstate index, adjust Yb downward; if there is an abnormal understate index, adjust Yb upward until the adjusted rotational speed S i stops when it ∈ [Z - X1, Z + X1].

4. A gas turbine combustion stability regulation system according to claim 3, characterized in that The specific method for the characteristic regulation end to select the optimal air compression ratio is: After completing the adjustment process, change the air compression ratio again. After the change is completed, confirm a set of monitoring periods, where the monitoring period is a preset period. Determine the rotational speed curve generated by the impeller within the monitoring period, determine the maximum rotational speed and the minimum rotational speed from the rotational speed curve, and based on the maximum rotational speed and the minimum rotational speed, select the curve characteristic T1, where T1 = maximum rotational speed - minimum rotational speed. Also, confirm the rotational speed change value between adjacent moments from the rotational speed curve, where the rotational speed change value = |rotational speed at the next moment - rotational speed at the previous moment|. Then select the maximum value from several groups of rotational speed change values as the curve characteristic T2 of this rotational speed curve. Use: standard characteristic = T1×C1 + T2×C2 to confirm the standard characteristic belonging to this rotational speed curve, where C1 and C2 are both preset fixed coefficient factors; Use the same processing method for the standard characteristics of the rotational speed curve to confirm the rotational speed curve associated with the next set of monitoring periods and synchronously confirm the corresponding standard characteristics; If the standard feature becomes smaller, it changes continuously. If the standard feature becomes larger, the air compression ratio changes in the opposite direction. During the change process, S needs to be controlled. i It always satisfies: S i ∈[Z - X1, Z + X1]. From several groups of change processes, select the minimum value associated with the standard feature. Denote the air compression ratio associated with the minimum value as the optimal air compression ratio and transmit it to the execution center.

5. A gas turbine combustion stability regulation system according to claim 4, characterized in that, The execution center adjusts the original air compression ratio of the gas turbine to this value according to the confirmed optimal air compression ratio. After completing the adjustment process of the optimal air compression ratio, the execution center generates an adjustment completion signal and transmits the generated adjustment completion signal into the parameter-characteristic analysis end.

6. A gas turbine combustion stability regulation system according to claim 1, characterized in that, The specific method for the parameter-characteristic analysis end to determine the rotational speed fluctuation characteristics is: According to the adjustment completion signal, determine a set of analysis periods, where the analysis period is a preset period. Determine the impeller rotational speeds associated with different moments within the analysis period and generate a fluctuation curve of the impeller rotational speed; Lock the fluctuation points from within the fluctuation curve, where the trend directions of the line segments before and after the fluctuation points are opposite. Calibrate the partial wavebands between adjacent fluctuation points, and from the multiple sets of calibrated partial wavebands, determine the rotational speed variation values at adjacent times. Assume the rotational speed at the previous set of times is ZA1, and assume the rotational speed at the next set of times is ZA2. Use the rotational speed variation value = ZA2 - ZA1, perform a mean processing on several sets of rotational speed variation values associated with a single set of partial wavebands, confirm the characteristic mean value associated with the corresponding single set of partial wavebands, and calibrate the different characteristic mean values associated with different partial wavebands as JZ k , where k represents different partial wavebands; From several groups of confirmed characteristic means, select the minimum characteristic mean JZ k min and the maximum characteristic mean JZ k max, and adopt: JSmax = JZ k min × A1 and JSmin = JZ k max × A1 to determine the minimum value JSmin of the control characteristic and the maximum value JSmax of the control characteristic, where A1 is a preset fixed coefficient factor; According to the determined minimum regulation characteristic JSmin and maximum regulation characteristic JSmax, confirm a set of regulation intervals [JSmin, JSmax]. In the subsequent monitoring process, control the trend of the fuel intake to change within the regulation interval. If the rotational speed is greater than Z, control the trend to change downward and stop when the rotational speed is less than Z. If the rotational speed is less than Z, control the trend to change upward and stop when the rotational speed is greater than Z. From the trend change process, determine the single change time and identify the difference before and after the single change time, where the difference before and after ≥ 0. If the difference before and after ≤ 0.2 seconds, record the rotational speed fluctuation characteristics.

7. A gas turbine combustion stability regulation system according to claim 6, characterized in that, The rotational speed fluctuation characteristics include specific regulation characteristics with an upward trend and regulation characteristics with a downward trend, and the specific durations of the upward trend change and the downward trend change are confirmed.

8. A gas turbine combustion stability regulation system according to claim 1, characterized in that, The specific method of re-controlling the gas turbine by the real-time control end is as follows: Based on the recorded rotational speed fluctuation characteristics, after the previous set of trend regulations is completed, based on the specific regulation characteristics of the upward trend and the downward trend recorded, the fuel feeding trend is regulated in real time, and the specific regulation duration is the specific durations of the upward trend change and the downward trend change recorded.

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