A method and system for active flame stabilization control of a marine derivative gas turbine

Abstract

This invention relates to the field of gas turbine combustion control, specifically disclosing an active combustion stabilization control method and system for aero-derivative gas turbines. The method includes: constructing multi-parameter flameout-prone parameters, establishing combustion oscillation criteria, adjusting flame temperature in a graded, stepped manner according to combustion mode, offset reduction and risk recurrence locking after stabilization, and automatic control exit when exceeding limits. It also includes supporting functional modules for parameter acquisition, risk assessment, and adjustment execution. This invention solves the problems of lag response, insufficient prediction accuracy, difficulty in adapting to transient operation under wide operating conditions, and susceptibility to flameout and combustion oscillation in existing fixed-threshold PID control. It improves the combustion stability of aero-derivative gas turbines under transient operating conditions, achieving millisecond-level flameout warning and accurate oscillation prediction, thus achieving synergistic optimization of safety, emission performance, and economy.

Description

Technical Field

[0001] This invention relates to the field of gas turbine combustion control technology, specifically to an active combustion stabilization control method and system for an aero-derivative gas turbine. Background Technology

[0002] Gas turbines derived from aero-engines have become core equipment in distributed energy and emergency power generation due to their high power density, rapid start-stop characteristics, and low-emission combustion technology. However, in new power systems, gas turbines, as the main force in peak shaving and frequency regulation, need to operate under frequent varying operating conditions. This exacerbates the inherent contradiction between the wide-condition transient adaptability and low stability margin of their combustion systems. Frequent operation under varying operating conditions causes significant fluctuations in the combustion chamber equivalence ratio, which can easily induce thermoacoustic oscillations and flame instability, leading to a significantly increased probability of flameout.

[0003] Existing control strategies based on fixed-threshold PID feedback are insufficient to meet the millisecond-level flameout protection requirements of aero-derivative gas turbines due to response delays and the lack of consideration for the dynamic effects of environmental parameters (altitude, humidity) and fuel composition. Furthermore, the nonlinear characteristics of the turbulence-chemical reaction coupling effect within the combustion chamber prevent traditional offline calibration models from accurately predicting transient flameout boundaries. Therefore, there is an urgent need to develop a flameout prevention control algorithm that integrates real-time multi-parameter sensing (pressure pulsation spectrum, environmental parameters, fuel characteristics) and dynamic flameout boundary prediction to address the flameout instability problem of aero-derivative gas turbines during transient operation under wide operating conditions and achieve synergistic optimization of combustion stability and emission performance. Summary of the Invention

[0004] To address the aforementioned problems in the prior art, this invention provides an active combustion stabilization control method and system for aero-derivative gas turbines, which solves the problems of delayed response and insufficient prediction accuracy in the prior art, and achieves synergistic optimization of combustion stability and emission performance under wide load and rapid transient conditions.

[0005] To achieve the above objectives, this invention proposes an active combustion stabilization control method for aero-derivative gas turbines, comprising the following steps: S1. Obtain the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, and high-pressure compressor pressure ratio, and construct the flameout parameters under different combustion modes respectively. S2. Obtain the combustion pressure pulsation signal in the combustion chamber and construct a combustion oscillation criterion; S3. Determine the risk of flameout based on the flameout parameters. When there is a risk of flameout, apply positive stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. S4. Determine the risk of combustion oscillation based on the combustion oscillation criterion. When there is a risk of combustion oscillation, apply a negative stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. S5. When stable operation is continuously detected for a preset time, the flame temperature adjustment bias is automatically and gradually reduced; if the risk of flameout or combustion oscillation is detected again during the reduction process, the initial flame temperature adjustment bias value is reapplied and locked. S6. When the combustion pressure pulsation or flameout parameter is lower than the active combustion stabilization control algorithm's action reference value, and the flame temperature adjustment increment is not zero, the algorithm input is automatically cleared and the control is exited.

[0006] Preferably, in S1, the flameout parameters include: The percentage of the actual low-pressure turbine inlet temperature dispersion rate under different combustion modes relative to the maximum dispersion rate; The percentage of actual high-pressure compressor venting volume to the maximum allowable venting volume under different combustion modes; The percentage of CO or unburned hydrocarbon content relative to the maximum permissible CO or unburned hydrocarbon content under different combustion modes; The percentage of the high-pressure compressor outlet pressure to the high-pressure compressor outlet pressure when the compressor is about to shut down under different combustion modes.

[0007] Preferably, in step S2, the combustion oscillation criterion includes: The collected combustion pressure pulsation signal is subjected to multi-cycle averaging and smoothing processing. The rate of change and acceleration of the combustion pressure pulsation after averaging and smoothing processing are calculated. The combustion pressure pulsation signal after 1 second is predicted by Taylor expansion. Set high alarm values, high limits, and high-high limits for combustion pressure pulsation under different combustion modes. When the predicted combustion pressure pulsation signal exceeds the high limit, it is determined that there is a risk of combustion oscillation. The positive step adjustment is to apply an adjustment amount of 12°C at a time interval of 1 second, and the negative step adjustment is to apply an adjustment amount of -6°C at a time interval of 1 second.

[0008] Preferably, in step S3, the risk of flameout is determined by combining four flameout-prone parameters. When any one of the parameters exceeds the corresponding threshold, it is determined that there is a risk of flameout. Adjustments based on the unit's combustion mode include: In B or lower-level combustion mode, adjust the total temperature of the main ring combustion flame; Adjust the outer ring combustion flame temperature in BC / 2 or BC combustion mode; In AB combustion mode, adjust the inner ring combustion flame temperature; In ABC combustion mode, the combustion flame temperature of both the outer and inner rings is adjusted simultaneously.

[0009] Preferably, in step S5, the preset time is 120 seconds. When stable operation is detected for 120 seconds, the flame temperature adjustment bias automatically and gradually fades. If the risk of flameout or combustion oscillation reappears during the fading process, the initial flame temperature adjustment bias value takes effect again and is continuously locked.

[0010] Preferably, it also includes: based on the unit's operating conditions, combustion pressure pulsation, and flameout parameters, combined with the high alarm value, high limit value, very high limit value, and over-limit duration of combustion pressure pulsation and flameout parameters under different combustion modes, taking at least one of the following protective measures according to protection priority: emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm.

[0011] An active combustion stabilization control system for an aero-derivative gas turbine, employing any one of the active combustion stabilization control methods for an aero-derivative gas turbine, comprising: The parameter acquisition module is used to acquire the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, high-pressure compressor pressure ratio, and combustion chamber combustion pressure pulsation signal. The flameout risk assessment module is used to assess the flameout risk based on flameout parameters under different combustion modes. The combustion oscillation detection module is used to determine the risk of combustion oscillation based on combustion pressure pulsation signals. The graded flame temperature regulation module is used to output positive or negative stepped flame temperature regulation commands according to the combustion mode of the unit when there is a risk of flameout or combustion oscillation. The stability locking and bias management module is used to output a command for automatic gradual reduction of flame temperature adjustment bias when stable operation is continuously detected for a preset time; if the risk of flameout or combustion oscillation is detected again during the reduction process, a command is output to reapply the initial bias value and lock it continuously. The algorithm management module is used to automatically clear the algorithm input and exit control when the combustion pressure pulsation or flameout parameter is lower than the action reference value and the flame temperature adjustment increment is not zero. The protection measures execution module outputs execution signals for emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm according to priority based on the unit's operating conditions, combustion pressure pulsation, and the duration of exceeding the limits of the flameout parameters.

[0012] Preferably, the parameter acquisition module includes: a dispersion calculation unit connected to multiple low-pressure turbine inlet temperature thermocouples, a venting volume calculation unit connected to the high-pressure compressor exhaust valve, variable bypass exhaust valve and outlet exhaust valve, a CO or unburned hydrocarbon content monitoring unit connected to the turbine outlet, and a flameout boundary prediction model unit constructed based on the high-pressure compressor characteristic curve, used to output the high-pressure compressor outlet pressure when approaching flameout.

[0013] Preferably, the combustion oscillation judgment module includes: a filter that performs multi-cycle averaging and smoothing processing on the combustion pressure pulsation signal, a differentiator that calculates the rate of change and acceleration of change, and a predictor that predicts the signal after 1 second using Taylor expansion; the graded flame temperature adjustment module triggers negative adjustment based on the predicted signal exceeding the high limit set under different combustion modes.

[0014] Preferably, the stability locking and bias management module is equipped with a 120-second timer. When no risk of flameout or combustion oscillation is detected for 120 seconds, the bias is triggered to gradually fade. When the graded flame temperature adjustment module detects a risk again during the fading process, it restores the initial bias value and maintains the lock.

[0015] Therefore, this invention proposes an active combustion stabilization control method and system for aero-derivative gas turbines, with the following beneficial effects: (1) By real-time monitoring of parameters such as low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO / unburned hydrocarbon content and high-pressure compressor pressure ratio, a flameout criterion for different combustion modes was constructed. This can detect flameout trends in a timely manner and continuously adjust the flame temperature through a graded flame temperature adjustment strategy, effectively reducing the risk of flameout. (2) By real-time monitoring of combustion pressure pulsation parameters and combining them with a graded flame temperature regulation strategy, the risk of combustion oscillation is effectively reduced; (3) Through a two-minute stable operation lock-in mechanism and automatic reduction of flame temperature offset, the optimal combustion state is gradually restored after the risk is eliminated, avoiding long-term efficiency loss caused by traditional methods.

[0016] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0017] Figure 1 This is a flowchart of the method of the present invention; Figure 2 This is a system structure block diagram of the present invention. Detailed Implementation

[0018] To make the technical solutions, advantages, and objectives of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below. The described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the described embodiments of the present invention without creative effort are within the protection scope of this application.

[0019] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention pertains.

[0020] like Figures 1-2 As shown, this invention provides an active combustion stabilization control method and system for aero-derivative gas turbines.

[0021] An active combustion stabilization control method for an aero-derivative gas turbine includes the following steps: S1. Obtain the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, and high-pressure compressor pressure ratio, and construct the flameout parameters under different combustion modes respectively. The parameters for flameout include: The percentage of the actual low-pressure turbine inlet temperature dispersion rate under different combustion modes relative to the maximum dispersion rate; The percentage of actual high-pressure compressor venting volume to the maximum allowable venting volume under different combustion modes; The percentage of CO or unburned hydrocarbon content relative to the maximum permissible CO or unburned hydrocarbon content under different combustion modes; The percentage of the high-pressure compressor outlet pressure to the high-pressure compressor outlet pressure when the compressor is about to shut down under different combustion modes.

[0022] S2. Acquire combustion pressure pulsation signals in the combustion chamber and construct combustion oscillation criteria; the combustion oscillation criteria include: The collected combustion pressure pulsation signal is subjected to multi-cycle averaging and smoothing processing. The rate of change and acceleration of the combustion pressure pulsation after averaging and smoothing processing are calculated. The combustion pressure pulsation signal after 1 second is predicted by Taylor expansion. Set high alarm values, high limits, and high-high limits for combustion pressure pulsation under different combustion modes. When the predicted combustion pressure pulsation signal exceeds the high limit, it is determined that there is a risk of combustion oscillation. Positive step adjustment applies a 12°C adjustment at 1-second intervals, while negative step adjustment applies a -6°C adjustment at 1-second intervals.

[0023] S3. Determine the risk of flameout based on the flameout parameters. When there is a risk of flameout, apply positive stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. The risk of engine shutdown is determined by combining four parameters that indicate a risk of engine shutdown. When any one of these parameters exceeds the corresponding threshold, an engine shutdown risk is identified.

[0024] S4. Determine the risk of combustion oscillation based on the combustion oscillation criterion. When there is a risk of combustion oscillation, apply negative stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. Adjusting the combustion mode of the unit includes: In B or lower-level combustion mode, adjust the total temperature of the main ring combustion flame; Adjust the outer ring combustion flame temperature in BC / 2 or BC combustion mode; In AB combustion mode, adjust the inner ring combustion flame temperature; In ABC combustion mode, the combustion flame temperature of both the outer and inner rings is adjusted simultaneously.

[0025] S5. When stable operation is continuously detected for a preset time, the flame temperature adjustment bias is automatically and gradually reduced; if the risk of flameout or combustion oscillation is detected again during the reduction process, the initial flame temperature adjustment bias value is reapplied and locked. The preset time is 120 seconds. When stable operation is detected for 120 seconds, the flame temperature adjustment bias will automatically and gradually fade away. If the risk of flameout or combustion oscillation reappears during the fading process, the initial flame temperature adjustment bias value will take effect again and be continuously locked.

[0026] S6. When the combustion pressure pulsation or flameout parameter is lower than the active combustion stabilization control algorithm's action reference value, and the flame temperature adjustment increment is not zero, the algorithm input is automatically cleared and the control is exited.

[0027] An active combustion stabilization control method for an aero-derivative gas turbine further includes: based on the unit's operating conditions, combustion pressure pulsation, and flameout parameters, combined with the high alarm value, high limit value, high-high limit value, and over-limit duration of combustion pressure pulsation and flameout parameters under different combustion modes, taking at least one of the following protective measures according to protection priority: emergency shutdown, stepping to core idle speed, combustion mode downgrading, or alarm.

[0028] An active combustion stabilization control system for an aero-derivative gas turbine includes: The parameter acquisition module is used to acquire the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, high-pressure compressor pressure ratio, and combustion chamber combustion pressure pulsation signal. The parameter acquisition module includes: a dispersion calculation unit connected to multiple low-pressure turbine inlet temperature thermocouples; a venting volume calculation unit connected to the high-pressure compressor exhaust valve, variable bypass exhaust valve, and outlet exhaust valve; a CO or unburned hydrocarbon content monitoring unit connected to the turbine outlet; and a flameout boundary prediction model unit based on the high-pressure compressor characteristic curve, used to output the high-pressure compressor outlet pressure when approaching flameout.

[0029] The flameout risk assessment module is used to assess the flameout risk based on flameout parameters under different combustion modes. The combustion oscillation detection module is used to determine the risk of combustion oscillation based on combustion pressure pulsation signals. The combustion oscillation judgment module includes: a filter that performs multi-cycle averaging and smoothing processing on the combustion pressure pulsation signal, a differentiator that calculates the rate of change and acceleration of change, and a predictor that predicts the signal after 1 second using Taylor expansion; the graded flame temperature adjustment module triggers negative adjustment based on the predicted signal exceeding the high limit set under different combustion modes.

[0030] The graded flame temperature regulation module is used to output positive or negative stepped flame temperature regulation commands according to the combustion mode of the unit when there is a risk of flameout or combustion oscillation. The stability locking and bias management module is used to output a command for automatic gradual reduction of flame temperature adjustment bias when stable operation is continuously detected for a preset time; if the risk of flameout or combustion oscillation is detected again during the reduction process, a command is output to reapply the initial bias value and lock it continuously. The stability lock-in and bias management module is equipped with a 120-second timer. When no risk of flameout or combustion oscillation is detected for 120 seconds, the bias is triggered to gradually fade. When the graded flame temperature adjustment module detects the risk again during the fading process, it restores the initial bias value and maintains the lock-in.

[0031] The algorithm management module is used to automatically clear the algorithm input and exit control when the combustion pressure pulsation or flameout parameter is lower than the action reference value and the flame temperature adjustment increment is not zero. The protection measures execution module outputs execution signals for emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm according to priority based on the unit's operating conditions, combustion pressure pulsation, and the duration of exceeding the limits of the flameout parameters.

[0032] This embodiment takes a certain type of aero-derivative gas turbine as the object. The gas turbine supports multiple combustion modes such as B, BC / 2, BC, AB, and ABC. It is equipped with 8 low-pressure turbine inlet temperature thermocouples, a high-pressure compressor 8th stage exhaust valve, a variable bypass exhaust valve and an outlet exhaust valve, as well as a combustion chamber pressure pulsation sensor.

[0033] Under a certain variable load condition, the unit switches from BC mode to AB mode. The control system executes the following steps in real time: The inlet temperature measurements of eight low-pressure turbines are collected in real time. The collected measurements are sorted by high and low and their quality is judged. Outliers are removed, and the dispersion and dispersion change rate of the low-pressure turbine inlet temperature are calculated.

[0034] Based on a pre-built database of the relationship between combustion modes and the maximum rate of change of dispersion, the percentage of the actual rate of change of dispersion under the current mode relative to the maximum rate of change of dispersion is obtained and used as the first parameter for flameout.

[0035] Simultaneously, the gas release volume through the 8th stage exhaust valve, variable bypass exhaust valve, and outlet exhaust valve of the high-pressure compressor is calculated in real time. The maximum allowable gas release volume is calculated based on the inlet air temperature and equivalent speed of the high-pressure compressor. The percentage of the actual gas release volume to the maximum allowable gas release volume is used as the second flameout parameter.

[0036] Real-time monitoring of CO or unburned hydrocarbon content at turbine outlet; construction of a database relating combustion mode to CO or unburned hydrocarbon content; obtaining the percentage of CO or unburned hydrocarbon content relative to the maximum allowable content as the flameout parameter.

[0037] A flameout boundary prediction model is constructed based on the high-pressure compressor characteristic curve. The high-pressure compressor pressure ratio at the flameout boundary under the current equivalent speed and equivalent flow rate is predicted. The high-pressure compressor outlet pressure at the flameout boundary is calculated based on the high-pressure compressor inlet pressure. The percentage of the actual outlet pressure to the flameout outlet pressure is obtained as the flameout parameter four.

[0038] The combustion chamber combustion pressure pulsation signal is acquired in real time. The sampled signal is then subjected to multi-cycle averaging and smoothing. The rate of change and acceleration of the combustion pressure pulsation after averaging and smoothing are calculated. The combustion pressure pulsation signal after 1 second is predicted using Taylor expansion. High alarm values, high limits, and ultra-high limits for combustion pressure pulsation are set for different combustion modes.

[0039] The risk of flameout is assessed by combining four parameters to predict flameout. When a risk of flameout is detected, since the unit is currently in AB combustion mode, a positive adjustment of 12°C is applied to the inner ring combustion flame temperature, and the inner ring combustion flame temperature is continuously adjusted at 1-second intervals until the risk of flameout is eliminated.

[0040] When a combustion oscillation risk is determined based on the combustion oscillation criterion (the predicted combustion pressure pulsation signal exceeds the upper limit), if the unit is in BC mode, an adjustment of -6°C is applied to the outer ring combustion flame temperature, and the total temperature of the outer ring combustion flame is continuously adjusted at 1-second intervals until the combustion oscillation risk is eliminated.

[0041] When stable operation is detected for 120 seconds (two minutes), the flame temperature regulation bias automatically and gradually fades. If a risk of flameout or combustion oscillation reappears during the fading process, the initial flame temperature regulation bias value is reinstated and continuously locked to ensure the safe and stable operation of the unit.

[0042] When the combustion pressure pulsation or flameout parameter is lower than the active combustion stabilization control algorithm's action reference value, and the combustion flame temperature adjustment increment of the inner ring, outer ring, or main ring is not zero, the algorithm input is automatically cleared, and the algorithm automatically exits control.

[0043] Protection measures: Based on the unit's operating conditions, combustion pressure pulsation, and flameout parameters, and considering the high alarm values, high limits, very high limits, and over-limit durations of combustion pressure pulsation and flameout parameters under different combustion modes, take at least one of the following measures according to protection priority: emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm.

[0044] The system for implementing the above method includes: a parameter acquisition module, a flameout risk judgment module, a combustion oscillation judgment module, a graded flame temperature adjustment module, a stability locking and bias management module, an algorithm management module, and a protection measure execution module.

[0045] The parameter acquisition module includes a dispersion calculation unit connected to the inlet temperature thermocouples of the eight low-pressure turbines, a gas release calculation unit connected to the eighth-stage exhaust valve, variable bypass exhaust valve, and outlet exhaust valve of the high-pressure compressor, a CO or unburned hydrocarbon content monitoring unit connected to the turbine outlet, and a flameout boundary prediction model unit based on the characteristic curve of the high-pressure compressor.

[0046] The combustion oscillation judgment module includes a filter that performs multi-cycle averaging and smoothing processing on the combustion pressure pulsation signal, a differentiator that calculates the rate of change and acceleration, and a predictor that predicts the signal one second later using Taylor expansion. The stability locking and bias management module is equipped with a 120-second timer.

[0047] Therefore, this invention provides an active combustion stabilization control method and system for aero-derivative gas turbines, solving the technical problems of existing control strategies such as slow response, insufficient prediction accuracy, and difficulty in adapting to the high risk of flameout and combustion oscillation caused by transient operation under wide operating conditions. By integrating multi-parameter flameout tendency criteria and combustion oscillation criteria, millisecond-level early warning of flameout trends and accurate prediction of combustion oscillations are achieved, significantly improving combustion stability under transient conditions. A graded flame temperature stepwise adjustment strategy is adopted to simultaneously reduce the risk of flameout and oscillation; and through stable operation locking and automatic bias fading mechanisms, the optimal combustion state is gradually restored after the risk is eliminated, avoiding the long-term efficiency loss caused by traditional fixed bias, and achieving synergistic optimization of combustion stability, safety, and economy under wide load and rapid transient conditions.

[0048] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A method for active combustion stabilization control of an aero-derivative gas turbine, characterized in that, Includes the following steps: S1. Obtain the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, and high-pressure compressor pressure ratio, and construct the flameout parameters under different combustion modes respectively. S2. Obtain the combustion pressure pulsation signal in the combustion chamber and construct a combustion oscillation criterion; S3. Determine the risk of flameout based on the flameout parameters. When there is a risk of flameout, apply positive stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. S4. Determine the risk of combustion oscillation based on the combustion oscillation criterion. When there is a risk of combustion oscillation, apply a negative stepwise adjustment to at least one of the main ring combustion flame temperature, outer ring combustion flame temperature, or inner ring combustion flame temperature according to the combustion mode of the unit. S5. When stable operation is continuously detected for a preset time, the flame temperature adjustment bias will automatically and gradually decrease. If a risk of flameout or combustion oscillation is detected again during the flameout process, the initial flame temperature regulation bias value is reapplied and locked. S6. When the combustion pressure pulsation or flameout parameter is lower than the active combustion stabilization control algorithm's action reference value, and the flame temperature adjustment increment is not zero, the algorithm input is automatically cleared and the control is exited.

2. The active combustion stabilization control method for an aero-derivative gas turbine according to claim 1, characterized in that, In S1, the flameout parameters include: The percentage of the actual low-pressure turbine inlet temperature dispersion rate under different combustion modes relative to the maximum dispersion rate; The percentage of actual high-pressure compressor venting volume to the maximum allowable venting volume under different combustion modes; The percentage of CO or unburned hydrocarbon content relative to the maximum permissible CO or unburned hydrocarbon content under different combustion modes; The percentage of the high-pressure compressor outlet pressure to the high-pressure compressor outlet pressure when the compressor is about to shut down under different combustion modes.

3. The active combustion stabilization control method for an aero-derivative gas turbine according to claim 1, characterized in that, In S2, the combustion oscillation criterion includes: The collected combustion pressure pulsation signal is subjected to multi-cycle averaging and smoothing processing. The rate of change and acceleration of the combustion pressure pulsation after averaging and smoothing processing are calculated. The combustion pressure pulsation signal after 1 second is predicted by Taylor expansion. Set high alarm values, high limits, and high-high limits for combustion pressure pulsation under different combustion modes. When the predicted combustion pressure pulsation signal exceeds the high limit, it is determined that there is a risk of combustion oscillation. The positive step adjustment is to apply an adjustment amount of 12°C at a time interval of 1 second, and the negative step adjustment is to apply an adjustment amount of -6°C at a time interval of 1 second.

4. The active combustion stabilization control method for an aero-derivative gas turbine according to claim 1, characterized in that, In S3, the risk of flameout is determined by combining four flameout-prone parameters. When any one of the parameters exceeds the corresponding threshold, it is determined that there is a risk of flameout. Adjustments based on the unit's combustion mode include: In B or lower-level combustion mode, adjust the total temperature of the main ring combustion flame; Adjust the outer ring combustion flame temperature in BC / 2 or BC combustion mode; In AB combustion mode, adjust the inner ring combustion flame temperature; In ABC combustion mode, the combustion flame temperature of both the outer and inner rings is adjusted simultaneously.

5. The active combustion stabilization control method for an aero-derivative gas turbine according to claim 1, characterized in that, In S5, the preset time is 120 seconds. When stable operation is detected for 120 seconds, the flame temperature adjustment bias automatically and gradually fades. If the risk of flameout or combustion oscillation reappears during the fading process, the initial flame temperature adjustment bias value takes effect again and is continuously locked.

6. The active combustion stabilization control method for an aero-derivative gas turbine according to claim 1, characterized in that, Also includes: Based on the unit's operating conditions, combustion pressure pulsation, and flameout parameters, and considering the high alarm values, high limits, very high limits, and over-limit durations of combustion pressure pulsation and flameout parameters under different combustion modes, at least one of the following protective measures is taken according to protection priority: emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm.

7. An active combustion stabilization control system for an aero-derivative gas turbine, employing the active combustion stabilization control method for an aero-derivative gas turbine as described in any one of claims 1-6, characterized in that, include: The parameter acquisition module is used to acquire the low-pressure turbine inlet temperature dispersion, high-pressure compressor exhaust volume, CO or unburned hydrocarbon content, high-pressure compressor pressure ratio, and combustion chamber combustion pressure pulsation signal. The flameout risk assessment module is used to assess the flameout risk based on flameout parameters under different combustion modes. The combustion oscillation detection module is used to determine the risk of combustion oscillation based on combustion pressure pulsation signals. The graded flame temperature regulation module is used to output positive or negative stepped flame temperature regulation commands according to the combustion mode of the unit when there is a risk of flameout or combustion oscillation. The stability locking and bias management module is used to output a command for the flame temperature adjustment bias to gradually fade away when stable operation is continuously detected for a preset time. If a risk of flameout or combustion oscillation is detected again during the decay process, an instruction to reapply the initial bias value and remain locked is output. The algorithm management module is used to automatically clear the algorithm input and exit control when the combustion pressure pulsation or flameout parameter is lower than the action reference value and the flame temperature adjustment increment is not zero. The protection measures execution module outputs execution signals for emergency shutdown, stepping to core idle speed, combustion mode downgrade, or alarm according to priority based on the unit's operating conditions, combustion pressure pulsation, and the duration of exceeding the limits of the flameout parameters.

8. The active combustion stabilization control system for an aero-derivative gas turbine according to claim 7, characterized in that, The parameter acquisition module includes: a dispersion calculation unit connected to multiple low-pressure turbine inlet temperature thermocouples, a gas release calculation unit connected to the high-pressure compressor exhaust valve, variable bypass exhaust valve and outlet exhaust valve, a CO or unburned hydrocarbon content monitoring unit connected to the turbine outlet, and a flameout boundary prediction model unit based on the high-pressure compressor characteristic curve, used to output the high-pressure compressor outlet pressure when approaching flameout.

9. The active combustion stabilization control system for an aero-derivative gas turbine according to claim 7, characterized in that, The combustion oscillation judgment module includes: a filter that performs multi-cycle averaging and smoothing processing on the combustion pressure pulsation signal, a differentiator that calculates the rate of change and acceleration of change, and a predictor that predicts the signal after 1 second using Taylor expansion; the graded flame temperature adjustment module triggers negative adjustment based on the predicted signal exceeding the high limit set under different combustion modes.

10. The active combustion stabilization control system for an aero-derivative gas turbine according to claim 7, characterized in that, The stability locking and bias management module is equipped with a 120-second timer. When no risk of flameout or combustion oscillation is detected for 120 seconds, the bias is triggered to gradually fade. When the graded flame temperature adjustment module detects a risk again during the fading process, it restores the initial bias value and maintains the lock.

Images