A control method and system for a combustion engine

Abstract

The application relates to a control method and system of a combustion engine and relates to the field of combustion engine control. The method comprises the following steps: acquiring first temperature values of multiple positions on an exhaust section cross section collected multiple times in a preset time period and an oscillation waveform diagram of multiple dynamic pressure sensors on a combustion chamber shell of the combustion engine, each position on the exhaust section cross section corresponding to a burner; generating a temperature field of the exhaust section cross section about each collection based on the first temperature values of the multiple positions collected multiple times; judging whether there is an abnormal position in the multiple positions based on the first temperature values of the multiple positions; if there is an abnormal position, determining a combustion abnormality degree in the combustion chamber based on the temperature field, the number of the abnormal positions and the oscillation waveform diagram of the multiple dynamic pressure sensors; and controlling the combustion engine load to be reduced based on the combustion abnormality degree. The application realizes more convenient checking of the combustion abnormality in the combustion chamber and accurate control of the combustion engine operation according to the combustion abnormality.

Description

Technical Field

[0001] This application relates to the field of gas turbine control, and in particular to a gas turbine control method and system. Background Technology

[0002] Gas turbine power generation, also known as gas turbine generator, is a method of generating electricity by using a gas turbine to drive a generator. It is one of the most important power generation technologies today, playing a crucial role in peak shaving, emergency response, and clean energy supplementation in modern power systems. A gas turbine typically consists of three main parts: a compressor, a combustion chamber, and a turbine. The compressor draws in and compresses air, increasing its pressure and temperature. The combustion chamber includes multiple annularly arranged burners where high-pressure air mixes with injected fuel (such as natural gas, diesel, or syngas) and ignites, producing high-temperature, high-pressure gas. This high-temperature, high-pressure gas expands in the turbine, impacting the turbine blades and causing the turbine to rotate at high speed, thereby driving an external generator to produce electricity.

[0003] Because gas turbines contain numerous burners within their combustion chambers, carbon buildup and blockages can occur after prolonged operation. These issues can lead to incomplete and unstable combustion, resulting in unstable power generation, overheating and damage to hot-channel components, and severe pressure fluctuations in the combustion chamber causing mechanical vibration and component damage. Furthermore, the enclosed nature of the gas turbine during operation makes it difficult to monitor combustion conditions and promptly detect anomalies. When combustion anomalies occur, it is challenging to precisely reduce the turbine load to mitigate the abnormalities and attempt to eliminate combustion instability. Therefore, finding a more convenient way to detect combustion anomalies and accurately control the gas turbine's operation based on these anomalies becomes a significant challenge. Summary of the Invention

[0004] In order to more conveniently detect combustion abnormalities in the combustion chamber and accurately control the operation of the gas turbine based on the combustion abnormalities, this application provides a control method and system for a gas turbine.

[0005] In a first aspect, this application provides a control method for a gas turbine, employing the following technical solution: A control method for a gas turbine, comprising: The system acquires the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, which are collected multiple times within a preset time period. Each location on the exhaust section cross-section corresponds to a burner. The temperature field of the exhaust section section with respect to each acquisition time is generated based on the first temperature values ​​of multiple locations collected multiple times, and the presence of abnormal locations among the multiple locations is determined based on the first temperature values ​​of the multiple locations. If an abnormal location is found, the degree of combustion abnormality in the combustion chamber is determined based on the temperature field, the number of abnormal locations, and the oscillation waveforms of multiple dynamic pressure sensors. The gas turbine load is reduced based on the degree of combustion anomaly.

[0006] By adopting the above technical solution, obtaining the first temperature values ​​at multiple locations on the exhaust section cross-section can characterize the combustion status of each burner in the combustion chamber to a certain extent. This facilitates subsequent judgment of whether there are abnormal locations, i.e., abnormal burners, on the exhaust section cross-section based on the first temperature values ​​at multiple locations. Obtaining the oscillation waveforms of multiple dynamic pressure sensors can reveal the vibration and oscillation of the burners during combustion, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber. The temperature field of the exhaust section cross-section is generated based on the first temperature value at each temperature acquisition. The temperature field records the temperature performance and distribution of the exhaust section cross-section at each temperature acquisition, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber based on the temperature field. If abnormal locations exist, it indicates that there is an abnormality in the combustion operation of the combustion chamber. The temperature field and the oscillation waveforms of multiple dynamic pressure sensors are key factors affecting the degree of combustion abnormality in the combustion chamber. Moreover, the more abnormal locations there are, the higher the degree of abnormality in the combustion chamber. Therefore, by comprehensively analyzing the number of abnormal locations, the temperature field, and the oscillation waveforms, the degree of combustion abnormality in the combustion chamber can be accurately determined. After accurately determining the degree of combustion abnormality, the load of the gas turbine can be precisely controlled and reduced based on the degree of combustion abnormality, so as to attempt to eliminate unstable combustion and reduce damage to gas turbine components by reducing the combustion intensity.

[0007] In another possible implementation, determining whether there are abnormal locations among the plurality of locations based on the first temperature values ​​of the plurality of locations includes: Determine the first temperature variance for each location within a preset time period; Determine whether a target first temperature value exists at each location. The target first temperature value is a first temperature value that is not within a preset temperature range. The preset temperature range is the operating temperature range within the exhaust section when the gas turbine is running normally. If a first target location exists, then determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period, where the first target location is the location where the target first temperature value exists; From the target first temperature value, a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range are determined; Determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range; Determine the second average value of all the second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range; Anomalies at each first target location are determined based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference. If an outlier reaches the first target position of the preset outlier threshold, then an outlier position is determined to exist.

[0008] In another possible implementation, the degree of combustion anomaly within the combustion chamber is determined based on the temperature field, the number of abnormal locations, and oscillation waveforms from multiple dynamic pressure sensors, including: Calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range, wherein the preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally; The number of second target locations in each temperature field is determined, and outliers in each temperature field are determined based on the temperature range, the second temperature variance, and the number of second target locations. Determine the sum of outliers in the entire temperature field, and determine the degree of the first sub-combustion anomaly based on the sum of outliers and the number of outlier locations; The degree of second sub-combustion anomaly is determined based on the oscillation waveforms of the multiple dynamic pressure sensors; The degree of combustion abnormality in the combustion chamber is determined based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

[0009] In another possible implementation, determining the degree of the second sub-combustion anomaly based on the oscillation waveforms of the plurality of dynamic pressure sensors includes: The oscillation waveform of each dynamic pressure sensor is converted into a spectrum. Determine the target frequency that matches the preset characteristic frequency from the spectrum; Determine the amplitude corresponding to each target frequency, and identify the target candidate frequencies whose amplitude reaches the preset amplitude threshold corresponding to the target frequency; Determine a second ratio between the number of target candidate frequencies and the total number of target frequencies; The number of target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode is determined, and a third ratio of the number of target frequencies to the number of preset characteristic frequencies in each oscillation mode is determined. The oscillation modes include longitudinal modes along the length of the combustion chamber, tangential modes along the circumferential direction of the combustion chamber cross-section, and radial modes along the radial direction of the combustion chamber cross-section. The hazard value of each oscillation mode at the location of each dynamic pressure sensor is determined based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode. The combustion anomaly value at the location of each dynamic pressure sensor is determined based on the hazard value of each oscillation mode and the second ratio. The second sub-combustion anomaly degree is obtained by summing the combustion anomaly values ​​at all locations of the dynamic pressure sensors.

[0010] In another possible implementation, determining the hazard value of each oscillation mode at the location of each dynamic pressure sensor based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode includes: The maximum amplitude is determined from the amplitudes of all target candidate frequencies corresponding to each oscillation mode, and the average amplitude of all target candidate frequencies corresponding to each oscillation mode is determined. The baseline hazard value for each oscillation mode is calculated based on the maximum amplitude, average amplitude, corresponding third ratio, and their respective weights. The hazard value of each oscillation mode is determined based on the baseline hazard value of each oscillation mode and the preset hazard coefficient corresponding to each oscillation mode.

[0011] In another possible implementation, controlling the reduction of the gas turbine load based on the degree of combustion anomaly includes: The degree of combustion abnormality is substituted into a first preset function to obtain the fuel flow reduction value. The first preset function is a function that calculates the fuel flow reduction value based on the degree of combustion abnormality. The degree of combustion abnormality is substituted into a second preset function to obtain the compressor pressure reduction value. The second preset function is a function that calculates the compressor pressure reduction value based on the degree of combustion abnormality. The gas turbine is controlled to operate according to the decrease in fuel flow and pressure to reduce the load.

[0012] In another possible implementation, the method further includes: The output displays the location of the anomaly.

[0013] Secondly, this application provides a control system for a gas turbine, which adopts the following technical solution: A control system for a gas turbine, comprising: The data acquisition module is used to acquire the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, which are collected multiple times within a preset time period. Each location on the exhaust section cross-section corresponds to a burner. An abnormal location judgment module is used to generate the temperature field of the exhaust section section with respect to each acquisition based on the first temperature values ​​of multiple locations collected multiple times, and to judge whether there is an abnormal location among the multiple locations based on the first temperature values ​​of the multiple locations. The combustion anomaly determination module is used to determine the degree of combustion anomaly in the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms of multiple dynamic pressure sensors when an anomaly location exists. The load control module is used to control the reduction of the gas turbine load based on the degree of combustion abnormality.

[0014] By adopting the above technical solution, the data acquisition module obtains first temperature values ​​at multiple locations on the exhaust section cross-section, which can characterize the combustion status of each burner in the combustion chamber to a certain extent. This facilitates the subsequent anomaly location judgment module in determining whether there are any abnormal locations, i.e., abnormal burners, on the exhaust section cross-section based on the first temperature values ​​at multiple locations. The data acquisition module obtains oscillation waveforms from multiple dynamic pressure sensors, which can reveal the vibration and oscillation of the burner during combustion, thus facilitating subsequent analysis of the degree of combustion anomaly in the combustion chamber. A temperature field of the exhaust section cross-section is generated based on the first temperature values ​​at each temperature acquisition. This temperature field records the temperature performance and distribution of the exhaust section cross-section at each temperature acquisition, thereby enabling... The degree of combustion abnormality in the combustion chamber is then analyzed based on the temperature field. If there are abnormal locations, it indicates that there is an abnormality in the combustion operation of the combustion chamber. The temperature field and the oscillation waveforms of multiple dynamic pressure sensors are key factors affecting the degree of combustion abnormality in the combustion chamber. Moreover, the more abnormal locations there are, the higher the degree of abnormality in the combustion chamber. Therefore, the combustion abnormality determination module can accurately determine the degree of combustion abnormality in the combustion chamber by comprehensively analyzing the number of abnormal locations, the temperature field, and the oscillation waveforms. After accurately determining the degree of combustion abnormality, the load control module can precisely control and reduce the load of the gas turbine according to the degree of combustion abnormality, so as to try to eliminate unstable combustion and reduce damage to the gas turbine components by reducing the combustion intensity.

[0015] In another possible implementation, when the abnormal location determination module determines whether there is an abnormal location among the plurality of locations based on the first temperature value of the plurality of locations, it is specifically used for: Determine the first temperature variance for each location within a preset time period; Determine whether a target first temperature value exists at each location. The target first temperature value is a first temperature value that is not within a preset temperature range. The preset temperature range is the operating temperature range within the exhaust section when the gas turbine is running normally. If a first target location exists, then determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period, where the first target location is the location where the target first temperature value exists; From the target first temperature value, a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range are determined; Determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range; Determine the second average value of all the second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range; Anomalies at each first target location are determined based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference. If an outlier reaches the first target position of the preset outlier threshold, then an outlier position is determined to exist.

[0016] In another possible implementation, when determining the degree of combustion anomaly in the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms of multiple dynamic pressure sensors, the combustion anomaly determination module is specifically used for: Calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range, wherein the preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally; The number of second target locations in each temperature field is determined, and outliers in each temperature field are determined based on the temperature range, the second temperature variance, and the number of second target locations. Determine the sum of outliers in the entire temperature field, and determine the degree of the first sub-combustion anomaly based on the sum of outliers and the number of outlier locations; The degree of second sub-combustion anomaly is determined based on the oscillation waveforms of the multiple dynamic pressure sensors; The degree of combustion abnormality in the combustion chamber is determined based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

[0017] In another possible implementation, when determining the degree of combustion anomaly based on the oscillation waveforms of the plurality of dynamic pressure sensors, the combustion anomaly determination module is specifically used for: The oscillation waveform of each dynamic pressure sensor is converted into a spectrum. Determine the target frequency that matches the preset characteristic frequency from the spectrum; Determine the amplitude corresponding to each target frequency, and identify the target candidate frequencies whose amplitude reaches the preset amplitude threshold corresponding to the target frequency; Determine a second ratio between the number of target candidate frequencies and the total number of target frequencies; The number of target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode is determined, and a third ratio of the number of target frequencies to the number of preset characteristic frequencies in each oscillation mode is determined. The oscillation modes include longitudinal modes along the length of the combustion chamber, tangential modes along the circumferential direction of the combustion chamber cross-section, and radial modes along the radial direction of the combustion chamber cross-section. The hazard value of each oscillation mode at the location of each dynamic pressure sensor is determined based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode. The combustion anomaly value at the location of each dynamic pressure sensor is determined based on the hazard value of each oscillation mode and the second ratio. The second sub-combustion anomaly degree is obtained by summing the combustion anomaly values ​​at all locations of the dynamic pressure sensors.

[0018] In another possible implementation, when the combustion anomaly determination module determines the hazard value of each oscillation mode at the location of each dynamic pressure sensor based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode, it is specifically used for: The maximum amplitude is determined from the amplitudes of all target candidate frequencies corresponding to each oscillation mode, and the average amplitude of all target candidate frequencies corresponding to each oscillation mode is determined. The baseline hazard value for each oscillation mode is calculated based on the maximum amplitude, average amplitude, corresponding third ratio, and their respective weights. The hazard value of each oscillation mode is determined based on the baseline hazard value of each oscillation mode and the preset hazard coefficient corresponding to each oscillation mode.

[0019] In another possible implementation, the load control module, when the gas turbine load is reduced based on the control, is specifically used for: The degree of combustion abnormality is substituted into a first preset function to obtain the fuel flow reduction value. The first preset function is a function that calculates the fuel flow reduction value based on the degree of combustion abnormality. The degree of combustion abnormality is substituted into a second preset function to obtain the compressor pressure reduction value. The second preset function is a function that calculates the compressor pressure reduction value based on the degree of combustion abnormality. The gas turbine is controlled to operate according to the decrease in fuel flow and pressure to reduce the load.

[0020] In another possible implementation, the control system of the gas turbine further includes: The output module is used to display the location of the abnormality.

[0021] Thirdly, this application provides an electronic device that adopts the following technical solution: An electronic device comprising: At least one processor; Memory; At least one application, wherein the at least one application is stored in memory and configured to be executed by at least one processor, the at least one configuration being for: executing a control method for a gas turbine as shown in any possible implementation of the first aspect.

[0022] Fourthly, this application provides a computer-readable storage medium, which adopts the following technical solution: A computer-readable storage medium that, when the computer program is executed in a computer, causes the computer to perform a control method for a gas turbine as described in any one of the first aspects.

[0023] In summary, this application includes at least one of the following beneficial technical effects: Acquiring the first temperature values ​​at multiple locations on the exhaust section cross-section can characterize the combustion status of each burner in the combustion chamber to a certain extent. This facilitates subsequent determination of whether there are abnormal locations, i.e., abnormal burners, on the exhaust section cross-section based on the first temperature values ​​at multiple locations. Acquiring the oscillation waveforms of multiple dynamic pressure sensors can reveal the vibration and oscillation of the burners during combustion, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber. The temperature field of the exhaust section cross-section at each temperature acquisition is generated based on the first temperature value at each acquisition. The temperature field records the temperature performance and distribution of the exhaust section cross-section at each temperature acquisition, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber based on the temperature field. If abnormal locations exist, it indicates that there is an abnormality in the combustion operation of the combustion chamber. The temperature field and the oscillation waveforms of multiple dynamic pressure sensors are key factors affecting the degree of combustion abnormality in the combustion chamber. Moreover, the more abnormal locations there are, the higher the degree of abnormality in the combustion chamber. Therefore, by comprehensively analyzing the number of abnormal locations, the temperature field, and the oscillation waveforms, the degree of combustion abnormality in the combustion chamber can be accurately determined. After accurately determining the degree of combustion abnormality, the load of the gas turbine can be precisely controlled to reduce the combustion abnormality, thereby attempting to eliminate unstable combustion and reduce damage to gas turbine components by reducing the combustion intensity. Attached Figure Description

[0024] Figure 1 This is a schematic flowchart of a gas turbine control method according to an embodiment of this application.

[0025] Figure 2 This is a schematic diagram of the control system of a gas turbine according to an embodiment of this application.

[0026] Figure 3This is a schematic diagram of the structure of an electronic device according to an embodiment of this application. Detailed Implementation

[0027] The present application will be further described in detail below with reference to the accompanying drawings.

[0028] After reading this specification, those skilled in the art may make modifications to this embodiment without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this application.

[0029] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0030] Furthermore, the term "and / or" in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. Additionally, the character " / " in this article, unless otherwise specified, generally indicates that the preceding and following related objects have an "or" relationship.

[0031] The embodiments of this application will now be described in further detail with reference to the accompanying drawings.

[0032] This application provides a control method for a gas turbine, executed by an electronic device. This electronic device can be a server or a terminal device. The server can be a standalone physical server, a server cluster or distributed system composed of multiple physical servers, or a cloud server providing cloud computing services. The terminal device can be a smartphone, tablet, laptop, desktop computer, etc., but is not limited to these. The terminal device and the server can be directly or indirectly connected via wired or wireless communication. This application does not impose any limitations on this. Figure 1 As shown, the method includes steps S101, S102, S103, and S104, wherein, S101, acquire the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, collected multiple times within a preset time period.

[0033] Each position on the exhaust section cross-section corresponds to a burner.

[0034] For this embodiment, the preset time period can be the past 8 hours, the past 24 hours, etc., set by the staff according to requirements. Due to the high temperature, high pressure, high flow rate, and chemically corrosive environment inside the combustion chamber, conventional thermometers cannot be used for long-term reliable measurement. Therefore, staff install a large number of thermocouples (usually 20-40 or more) around the exhaust section after the turbine, forming a "thermocouple rake" or array. The high-temperature gas generated by each combustion chamber flows into a specific area (fan-shaped area) of the turbine and eventually flows to the corresponding position in the exhaust section. If a combustion abnormality occurs in a combustion chamber, resulting in an excessively high or low outlet temperature, this abnormal temperature field will be transmitted to the exhaust section and detected by the thermocouples at the corresponding positions. Electronic equipment is connected to these thermocouples through wires, thereby obtaining the first temperature values ​​at multiple positions on the cross-section of the exhaust section within the preset time period. These first temperature values ​​are used to determine whether there are abnormal positions on the cross-section of the exhaust section. If there are abnormal positions, the burner corresponding to the abnormal position has a combustion abnormality.

[0035] Multiple high-frequency dynamic pressure sensors are installed at equal angles on the combustion chamber shell, for example, one sensor every 90°. Through cooling and mounting structures, the sensing surface (diaphragm) of the high-frequency dynamic pressure sensor is in communication with the high-pressure combustion gas inside the combustion chamber. The high-frequency dynamic pressure sensor is neither completely inside nor completely outside the shell, but rather a through-mounted design. Combustion instability in the combustion chamber (such as oscillating combustion) is usually closely related to localized overheating (high-temperature points), and a fault in each burner may trigger pressure pulses at a specific frequency. By analyzing the spectrum and amplitude of the pressure oscillations collected by each dynamic pressure sensor, the degree of combustion anomaly in the combustion chamber can be easily determined. Electronic equipment is connected to each high-frequency dynamic pressure sensor via wires to obtain the oscillation waveform of each sensor; the oscillation distribution diagram shows the change of the voltage signal output by the high-frequency dynamic pressure sensor over time.

[0036] S102, generate the temperature field of the exhaust section section with respect to each acquisition based on the first temperature values ​​of multiple locations collected multiple times, and determine whether there are abnormal locations among the multiple locations based on the first temperature values ​​of multiple locations.

[0037] In this embodiment, thermocouples collect temperature data at regular time intervals, such as every second. The electronic device generates a temperature field corresponding to each temperature acquisition based on the positions of all thermocouples collected within a preset time period, arranged in a ring. The temperature field characterizes the temperature performance and distribution across the exhaust section cross-section at each temperature acquisition point, and the temperature performance and distribution of the temperature field, to a certain extent, characterize the degree of combustion abnormality in the combustion chamber. The first temperature value at each location within the preset time period characterizes the temperature change at each location within the preset time period. Therefore, the electronic device can determine whether there are abnormal locations with abnormal temperature performance by analyzing the first temperature value at each location.

[0038] S103, if there are abnormal locations, the degree of combustion abnormality in the combustion chamber is determined based on the temperature field, the number of abnormal locations, and the oscillation waveforms of multiple dynamic pressure sensors.

[0039] In this embodiment, if the electronic device detects an abnormal location, it indicates an abnormal combustion condition in the combustion chamber. The temperature field characterizes the temperature performance and distribution on the exhaust section cross-section during each temperature acquisition, and the temperature performance and distribution of the temperature field, to a certain extent, characterize the degree of combustion abnormality in the combustion chamber. A greater number of abnormal locations indicates a greater number of abnormal burners in the combustion chamber, thus indicating a greater degree of combustion abnormality. The oscillation waveform of each dynamic pressure sensor records the oscillation at different locations in the combustion chamber when combustion is abnormal; for example, amplitude and frequency reflect the combustion abnormality. Therefore, the oscillation waveform records the combustion abnormality in the combustion chamber. In summary, the electronic device can accurately determine the degree of combustion abnormality in the combustion chamber by comprehensively analyzing the number of abnormal locations, the temperature field, and the oscillation waveform. If no abnormal location is found, it indicates that the combustion operation in the combustion chamber is good, and no further steps are performed.

[0040] S104 controls the reduction of gas turbine load based on the degree of combustion abnormality.

[0041] In the embodiments of this application, after the electronic device accurately determines the degree of combustion abnormality, it can accurately determine the amount of load reduction required for the gas turbine based on the degree of combustion abnormality. Then, the electronic device controls the gas turbine to reduce the load, thereby attempting to eliminate the combustion abnormality. Furthermore, reducing the load can effectively minimize damage to the gas turbine components caused by abnormal combustion. Load reduction can be achieved by the electronic device controlling a decrease in fuel flow and a decrease in press pressure.

[0042] One possible implementation of this application embodiment is that step S102 determines whether there are abnormal locations among the multiple locations based on the first temperature values ​​at multiple locations. Specifically, this includes steps S1021 (not shown in the figure), S1022 (not shown in the figure), S1023 (not shown in the figure), S1024 (not shown in the figure), S1025 (not shown in the figure), S1026 (not shown in the figure), S1027 (not shown in the figure), and S1028 (not shown in the figure). S1021, Determine the first temperature variance for each location within a preset time period.

[0043] In this embodiment of the application, the electronic device calculates the first temperature variance of each temperature acquisition location within a preset time period using a variance calculation formula. The first temperature variance characterizes the stability of the temperature performance at each location within the preset time period. The larger the first temperature variance at a location, the more unstable the temperature performance at that location, and the greater the likelihood that the location is an abnormal location.

[0044] S1022, determine whether the target first temperature value exists at each location.

[0045] The target first temperature value is the first temperature value that is not in the preset temperature range, and the preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally.

[0046] In the embodiments of this application, the electronic device compares the first temperature value within a preset time period at each location with a preset temperature range to determine whether a target first temperature value exists at each location. If a target first temperature value exists, it also indicates that the corresponding burner may have an abnormal combustion situation, and thus it indicates that such a location is more likely to be an abnormal location.

[0047] S1023, if a first target location exists, determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period.

[0048] The first target location is the location where the first target temperature value exists.

[0049] In this embodiment of the application, if the electronic device determines that a target first temperature value exists at certain locations, then these locations belong to the first target locations. The electronic device divides the number of target first temperature values ​​at each first target location by the total number of temperature acquisitions within a preset time period to obtain a first ratio. The larger the first ratio, the higher the proportion of target first temperature values, and the greater the probability that the location belongs to the first target location or is an abnormal location.

[0050] S1024, determine a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range from the target first temperature value.

[0051] In this embodiment of the application, the electronic device compares each target first temperature value at each first target location with the lower limit of a preset temperature range to determine a first candidate temperature value that is lower than the lower limit. Similarly, the electronic device compares each target first temperature value at each first target location with the upper limit of the preset temperature range to determine a second candidate temperature value that is higher than the upper limit.

[0052] S1025, determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range.

[0053] In this embodiment of the application, the electronic device calculates a first average value for all first candidate temperature values ​​at each first target location using an average value calculation formula. The first average value represents the overall level of all first candidate temperature values. Then, the electronic device subtracts the lower limit of a preset temperature range from the first average value to obtain a first difference value. The absolute value of the first difference value is then taken as the absolute value of the first difference value. The larger the absolute value of the first difference value, the greater the difference between the first candidate temperature value and the lower limit of the preset temperature range, and the greater the possibility that it belongs to an abnormal location.

[0054] S1026, determine the second average value of all second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range.

[0055] In this embodiment of the application, the electronic device calculates a second average value for all second candidate temperature values ​​at each first target location using an average value calculation formula. The second average value represents the overall level of all second candidate temperature values. Then, the electronic device subtracts the upper limit of a preset temperature range from the second average value to obtain a second difference value. The absolute value of the second difference value is then taken as the absolute value of the second difference value. The larger the absolute value of the second difference value, the greater the difference between the second candidate temperature value and the upper limit of the preset temperature range, and the greater the possibility that it belongs to an abnormal location.

[0056] S1027, determine the outlier value of each first target location based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference.

[0057] In summary, for the embodiments of this application, the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference are all key factors characterizing that each first target location belongs to an abnormal location. Therefore, the staff sets corresponding weights for the above four factors, including the first temperature variance, and stores them in the electronic device. The electronic device normalizes the above four factors, including the first temperature variance, respectively, using a preset normalization formula. Then, the electronic device calls the corresponding weights to perform weighted calculations on the above four normalized values ​​to obtain the abnormal value characterizing the degree of abnormality of each first target location.

[0058] S1028, if there is an outlier at the first target position that reaches the preset outlier threshold, then an outlier position is determined to exist.

[0059] In the embodiments of this application, a preset outlier threshold is used as the dividing point for whether the outlier is too high. The electronic device compares the outlier at each first target location with the preset outlier threshold. If there is a first target location that reaches the preset outlier threshold, it also indicates that there is an outlier location among the multiple temperature acquisition locations, and thus indicates that there is an abnormal combustion situation in the combustion chamber.

[0060] One possible implementation of this application embodiment involves determining the degree of combustion abnormality in the combustion chamber in step S103 based on the temperature field, the number of abnormal locations, and the oscillation waveforms of multiple dynamic pressure sensors. Specifically, this includes steps S1031 (not shown in the figure), S1032 (not shown in the figure), S1033 (not shown in the figure), S1034 (not shown in the figure), and S1035 (not shown in the figure). S1031, calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range.

[0061] The preset temperature range is the operating temperature range within the exhaust section when the gas turbine is running normally.

[0062] In this embodiment, after determining the temperature field at each temperature acquisition time, the electronic device calculates the temperature range by subtracting the maximum and minimum values ​​of the first temperature value for each temperature field using a range formula. A larger temperature range indicates a greater difference between the highest and lowest temperatures within the temperature field, thus indicating a greater degree of combustion abnormality in the combustion chamber at the time of temperature acquisition. The electronic device then calculates the second temperature variance for each temperature field using a variance calculation formula. A larger second temperature variance indicates greater temperature diversity and instability within the same temperature field, further indicating a greater degree of combustion abnormality in the combustion chamber at the time of temperature acquisition. Finally, the electronic device filters out positions in each temperature field that are not within the preset temperature range for the first temperature value, obtaining the second target position in each temperature field.

[0063] S1032, determine the number of second target locations in each temperature field, and determine the outliers of each temperature field based on the temperature range, the second temperature variance, and the number of second target locations.

[0064] In this embodiment, the electronic device counts the positions of first temperature values ​​in each temperature field that are not within a preset temperature range, thus obtaining the number of second target positions in each temperature field. A higher number of second target positions in each temperature field indicates a greater degree of combustion anomaly in the combustion chamber at the time of temperature acquisition. In summary, the number of second target positions, the temperature range, and the second temperature variance are all key factors affecting the degree of anomaly in each temperature field. The operator assigns corresponding weights to the number of second target positions, the temperature range, and the second temperature variance, and stores these weights in the electronic device. The electronic device normalizes these weights, and then uses the normalized values ​​to perform a weighted calculation to obtain the anomaly value for each temperature field. The anomaly value for each temperature field represents the degree of combustion anomaly in the combustion chamber at the corresponding temperature acquisition time.

[0065] S1033, determine the sum of outliers in the entire temperature field, and determine the degree of first sub-combustion anomaly based on the sum of outliers and the number of outlier locations.

[0066] In this embodiment, the electronic device sums the outliers of the entire temperature field to obtain a total outlier. The larger the total outlier, the greater the degree of combustion abnormality in the combustion chamber within a preset time period. In summary, the total outlier and the number of second target locations are key factors affecting the degree of combustion abnormality in the combustion chamber from the perspective of exhaust temperature performance. Therefore, the operator assigns corresponding weights to the total outlier and the number of outlier locations and stores them in the electronic device. The electronic device normalizes the total outlier and the number of outlier locations to obtain normalized values. The electronic device then uses the corresponding weights to perform a weighted calculation on these two normalized values ​​to obtain the first sub-combustion abnormality degree, which characterizes the degree of combustion abnormality in the combustion chamber from the perspective of exhaust temperature performance.

[0067] S1034, the degree of second sub-combustion anomaly is determined based on the oscillation waveform diagram of multiple dynamic pressure sensors.

[0068] In the embodiments of this application, since the oscillation waveform of each dynamic pressure sensor records the combustion oscillation at different positions of the combustion chamber shell, the electronic device can accurately determine the second sub-combustion anomaly degree, which characterizes the degree of combustion anomaly in terms of combustion chamber oscillation, by analyzing the oscillation waveform of each dynamic pressure sensor.

[0069] S1035, determine the degree of combustion abnormality in the combustion chamber based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

[0070] In this embodiment, the operator assigns weights to the first and second sub-combustion anomaly degrees and stores them in an electronic device. After determining the first and second sub-combustion anomaly degrees, the electronic device normalizes them. Then, it calculates a weighted average of the two normalized values ​​using their respective weights to obtain the combustion anomaly degree within the combustion chamber. A more accurate analysis of the combustion anomaly degree is achieved by comprehensively considering both the exhaust temperature and combustion oscillations within the combustion chamber.

[0071] One possible implementation of this application embodiment is that step S1034, which determines the degree of second sub-combustion anomaly based on the oscillation waveforms of multiple dynamic pressure sensors, specifically includes steps Sa (not shown in the figure), Sb (not shown in the figure), Sc (not shown in the figure), Sd (not shown in the figure), Se (not shown in the figure), Sf (not shown in the figure), Sg (not shown in the figure), and Sh (not shown in the figure), wherein... Sa converts the oscillation waveform of each dynamic pressure sensor into a spectrum.

[0072] In the embodiments of this application, the oscillation waveform of each dynamic pressure sensor in the electronic device is transformed from the time domain to the frequency domain spectrum using a fast Fourier transform.

[0073] Sb determines the target frequency that matches the preset characteristic frequency from the spectrum.

[0074] In the embodiments of this application, healthy combustion has low and smooth background noise, while combustion abnormalities (instability) produce sharp peaks at one or more specific frequency points. Each combustion chamber design has its inherent acoustic modes (such as longitudinal and tangential modes), corresponding to one or more characteristic frequencies. These frequencies can be known in advance through calculation and experimentation (for example, the characteristic frequencies of combustion instability in a certain type of gas turbine may be 280Hz and 450Hz). Operators can conduct advance experiments and calculations on the gas turbine combustion chamber to obtain the oscillation frequencies when combustion abnormalities occur, and then store these frequencies in the electronic equipment to obtain preset characteristic frequencies. After determining the spectrum of each dynamic pressure sensor, the electronic equipment filters out target frequencies that match the preset characteristic frequencies.

[0075] Sc determines the amplitude corresponding to each target frequency and identifies the target candidate frequencies whose amplitude reaches the preset amplitude threshold corresponding to the target frequency.

[0076] In this embodiment, the electronic device extracts the amplitude corresponding to each target frequency of each dynamic pressure sensor from the spectrum. A preset amplitude threshold serves as the dividing point between whether combustion abnormalities occur in the combustion chamber at the target frequency. The amplitude at which combustion abnormalities occur differs at different preset characteristic frequencies; therefore, different preset characteristic frequencies correspond to different preset amplitude thresholds. The electronic device compares each target frequency with its corresponding preset amplitude threshold to determine the target candidate frequency that reaches the corresponding preset amplitude threshold. A target candidate frequency whose amplitude reaches the preset amplitude threshold indicates the presence of a combustion abnormality, and the greater the hazard of the combustion abnormality, the more severe the problem.

[0077] Sd is a second ratio that determines the number of target candidate frequencies to the total number of target frequencies.

[0078] In the embodiments of this application, the electronic device counts the target frequencies (i.e., target candidate frequencies) of each dynamic pressure sensor that reach the preset amplitude threshold, and obtains the number of target frequencies that reach the preset amplitude threshold. Then, the electronic device divides this number by the total number of target frequencies to obtain a second ratio. The larger the second ratio, the larger the proportion of frequencies with combustion abnormalities and the greater the degree of combustion abnormality in the combustion chamber.

[0079] Se determines the number of target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode, and determines a third ratio between the number of target frequencies and the number of preset characteristic frequencies in each oscillation mode.

[0080] The oscillation modes include longitudinal modes along the length of the combustion chamber, tangential modes along the circumferential direction of the combustion chamber cross-section, and radial modes along the radial direction of the combustion chamber cross-section.

[0081] For the embodiments of this application, the combustion oscillation modes of the combustion chamber can be divided into the following three categories, each containing multiple frequencies. First is the longitudinal mode, in which pressure waves oscillate back and forth along the length of the combustion chamber (from the fuel nozzle to the turbine inlet), typically with one to three characteristic frequencies. Significant low-order mode frequencies include 1L (first order): the entire combustion chamber acts like a bellows, expanding and contracting simultaneously. This is the most common and also the most dangerous unstable mode, usually with the lowest frequency; 2L (second order): the combustion chamber forms two parts along its length, one with high pressure and the other with low pressure; 3L (third order): and so on, forming more complex waveforms. The longitudinal modes have lower frequencies, typically in the low to mid-frequency range (e.g., tens of Hz to 300 Hz), but possess enormous energy and are the most destructive.

[0082] Tangential mode pressure waves propagate along the circumference of the combustion chamber's cross-section. This can be imagined as sound waves "rotating" within the annular cavity. Because the combustion chamber is annular, tangential modes typically appear in pairs (clockwise and counterclockwise), resulting in a greater number of characteristic frequencies. Two to four pairs are usually observed, such as 1T (first-order tangential), 2T (second-order tangential), and so on. The frequencies of the tangential modes are higher than those of the longitudinal modes, typically in the range of several hundred Hz.

[0083] Radial modal pressure waves oscillate along the radius of the combustion chamber cross-section, typically exhibiting one or two significant radial modal characteristic frequencies. The characteristic frequencies of the radial modes are usually the highest, often in the high-frequency range, such as above 1000 Hz.

[0084] The electronic device counts the target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode to obtain the target number. Then, it divides the target number for each oscillation mode by the number of preset characteristic frequencies for each oscillation mode to obtain a third ratio. The larger the third ratio for a certain oscillation mode, the greater the harm of that oscillation mode.

[0085] Sf, based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode, determines the hazard value of each oscillation mode at the location of each dynamic pressure sensor.

[0086] In summary, for the embodiments of this application, the third ratio of each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode are key factors characterizing the hazard level of each oscillation mode at the location of each dynamic pressure sensor. Therefore, the electronic device can accurately determine the hazard value of each oscillation mode at the location of each dynamic pressure sensor by comprehensively analyzing the third ratio of each oscillation mode and the amplitude of the target candidate frequency.

[0087] Sg determines the combustion anomaly value at the location of each dynamic pressure sensor based on the hazard value of each oscillation mode and a second ratio.

[0088] In this embodiment, the electronic device sums the hazard values ​​of each oscillation mode of each dynamic pressure sensor to obtain a total hazard value. This total hazard value characterizes the degree of combustion anomaly in the combustion chamber at the location of each dynamic pressure sensor. In summary, both the hazard value and the second ratio are key factors characterizing the degree of combustion anomaly in the combustion chamber at the location of each dynamic pressure sensor. Therefore, the operator assigns corresponding weights to the total hazard value and the second ratio and stores them in the electronic device. The electronic device normalizes the total hazard value and the second ratio corresponding to each dynamic pressure sensor. Then, the electronic device uses the corresponding weights to perform a weighted calculation on the normalized values ​​to obtain the combustion anomaly value at the location of each dynamic pressure sensor.

[0089] Sh, the second sub-combustion anomaly degree is obtained by summing the combustion anomaly values ​​at all locations of the dynamic pressure sensors.

[0090] In the embodiments of this application, the electronic device can obtain the second sub-combustion anomaly degree by summing the combustion anomaly values ​​at the locations of all dynamic pressure sensors. The second sub-combustion anomaly value can characterize the overall combustion anomaly degree of the combustion chamber as reflected in the combustion oscillation aspect.

[0091] One possible implementation of this application embodiment involves determining the hazard value of each oscillation mode at the location of each dynamic pressure sensor in step Sf based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode. This specifically includes steps one, two, and three. Step 1: Determine the maximum amplitude from the amplitudes of all target candidate frequencies corresponding to each oscillation mode, and determine the average amplitude of all target candidate frequencies corresponding to each oscillation mode.

[0092] In this embodiment of the application, the target candidate frequency is the frequency of combustion abnormality. The electronic device filters out the maximum amplitude among all target candidate frequencies. The maximum amplitude represents the maximum degree of combustion abnormality for each oscillation mode. The electronic device calculates the average amplitude of all target candidate frequencies for each oscillation mode using an average value calculation formula. The average amplitude represents the overall level of amplitude at the frequency of combustion abnormality in each oscillation mode. The higher the average amplitude, the greater the degree of combustion abnormality represented by the oscillation mode.

[0093] Step 2: Calculate the baseline hazard value for each oscillation mode based on the maximum amplitude, average amplitude, corresponding third ratio, and their respective weights.

[0094] In summary, for the embodiments of this application, the maximum amplitude, average amplitude, and third ratio corresponding to each oscillation mode are key factors characterizing the degree of hazard of each oscillation mode. Therefore, the staff sets corresponding weights for the maximum amplitude, average amplitude, and third ratio and stores them in the electronic device. The electronic device normalizes the maximum amplitude, average amplitude, and third ratio to obtain their corresponding normalized values. The electronic device then calls their respective weights to perform weighted calculations on the normalized values ​​to obtain the benchmark hazard value for each oscillation mode.

[0095] Step 3: Determine the hazard value of each oscillation mode based on the baseline hazard value of each oscillation mode and the preset hazard coefficient corresponding to each oscillation mode.

[0096] In this embodiment, since different oscillation modes correspond to different levels of hazard, the operator sets a preset hazard coefficient for each oscillation mode. The hazard levels of the three oscillation modes, from highest to lowest, are: longitudinal mode > tangential mode > radial mode. The preset hazard coefficient set by the operator for the longitudinal mode can be 1.8, for the tangential mode can be 1.5, and for the radial mode can be 1.2. The electronic device multiplies the baseline hazard value of each oscillation mode by the corresponding preset hazard coefficient to obtain the hazard value of each oscillation mode. By proportionally multiplying the preset hazard coefficients of each oscillation mode, the hazard value of each true mode becomes more realistic and accurate.

[0097] One possible implementation of this application embodiment is that step S104 controls the reduction of the gas turbine load based on the degree of combustion abnormality, specifically including steps S1041 (not shown in the figure), S1042 (not shown in the figure), and S1043 (not shown in the figure), wherein... S1041, The degree of combustion abnormality is input into the first preset function to obtain the fuel flow reduction value.

[0098] The first preset function is a function that calculates the reduction in fuel flow based on the degree of combustion anomaly.

[0099] In the embodiments of this application, the first preset function can be obtained in advance by the staff based on a large number of experiments and calculations and stored in the electronic device. After the electronic device determines the degree of combustion abnormality, it calls the first preset function and substitutes the value representing the degree of combustion abnormality into the first preset function to calculate the fuel flow reduction value.

[0100] S1042, the degree of combustion abnormality is input into the second preset function to obtain the compressor pressure reduction value.

[0101] The second preset function is a function that calculates the pressure reduction of the compressor based on the degree of combustion abnormality.

[0102] In this embodiment of the application, the second preset function can also be obtained in advance by the staff based on a large number of experiments and calculations and stored in the electronic device. After the electronic device determines the degree of combustion abnormality, it calls the second preset function and substitutes the value representing the degree of combustion abnormality into the second preset function to calculate the pressure reduction value.

[0103] S1043 controls the gas turbine to operate according to the decrease in fuel flow and pressure to reduce the load.

[0104] In the embodiments of this application, the electronic device obtains the fuel flow reduction value and the compressor pressure reduction value based on the degree of combustion abnormality, and then obtains the load reduction strategy. The electronic device outputs control signals to the fuel flow pump and the compressor according to the determined fuel flow reduction value and pressure reduction value, so that the fuel flow pump and the compressor operate according to the load reduction strategy, thereby achieving the effect of reducing the gas turbine load. Reducing the gas turbine load can reduce the damage of combustion abnormality to gas turbine components and can attempt to eliminate the combustion abnormality.

[0105] In one possible implementation of this application embodiment, step S105 (not shown in the figure) is included after step S104, wherein... S105, output displays the location of the abnormality.

[0106] In this embodiment of the application, the electronic device can store an arrangement diagram of each burner in the combustion chamber. After determining an abnormal location, the electronic device identifies the burner corresponding to the abnormal location and marks it, for example, by using a different color than other normally operating burners. Then, the electronic device outputs the marked arrangement diagram to a display device such as a monitor for display, so that staff can promptly and intuitively know the abnormal location and the burner corresponding to the abnormal location.

[0107] The above embodiments describe a gas turbine control method from the perspective of process flow. The following embodiments describe a gas turbine control system 20 from the perspective of virtual module or virtual unit. For details, please refer to the following embodiments.

[0108] This application provides a control system 20 for a gas turbine, such as... Figure 2 As shown, a control system 20 for a gas turbine may specifically include: The data acquisition module 201 is used to acquire the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, which are collected multiple times within a preset time period. Each location on the exhaust section cross-section corresponds to a burner. The abnormal location judgment module 202 is used to generate the temperature field of the exhaust section section with respect to each acquisition based on the first temperature values ​​of multiple locations collected multiple times, and to judge whether there is an abnormal location among the multiple locations based on the first temperature values ​​of multiple locations. Combustion anomaly determination module 203 is used to determine the degree of combustion anomaly in the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms of multiple dynamic pressure sensors when an anomaly location exists. The load control module 204 is used to control the reduction of the gas turbine load based on the degree of combustion abnormality.

[0109] This application discloses a control system 20 for a gas turbine. The data acquisition module 201 acquires first temperature values ​​at multiple locations on the exhaust section cross-section, which can characterize the combustion status of each burner in the combustion chamber to a certain extent. This facilitates the subsequent abnormal location judgment module 202 in determining whether there are abnormal locations, i.e., abnormal burners, on the exhaust section cross-section based on the first temperature values ​​at multiple locations. The data acquisition module 201 acquires oscillation waveforms from multiple dynamic pressure sensors, which can reveal the vibration and oscillation of the burners during combustion, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber. The abnormal location judgment module 202 generates a temperature field of the exhaust section cross-section at each temperature acquisition based on the first temperature value at each acquisition. The temperature field records the temperature of the exhaust section cross-section at each temperature acquisition. The temperature performance and distribution of the combustion chamber are analyzed to determine the degree of combustion abnormality. If there are abnormal locations, it indicates that there is an abnormality in the combustion operation of the combustion chamber. The temperature field and the oscillation waveforms of multiple dynamic pressure sensors are key factors affecting the degree of combustion abnormality in the combustion chamber. The more abnormal locations there are, the higher the degree of abnormality in the combustion chamber. Therefore, the combustion abnormality determination module 203 can accurately determine the degree of combustion abnormality in the combustion chamber by comprehensively analyzing the number of abnormal locations, temperature field and oscillation waveforms. After accurately determining the degree of combustion abnormality, the load control module 204 can precisely control and reduce the load of the gas turbine according to the degree of combustion abnormality, so as to try to eliminate unstable combustion and reduce damage to the gas turbine components by reducing the combustion intensity.

[0110] In one possible implementation of this application embodiment, when the abnormal location determination module 202 determines whether there is an abnormal location among multiple locations based on the first temperature values ​​of multiple locations, it is specifically used for: Determine the first temperature variance for each location within a preset time period; Determine whether a target first temperature value exists at each location. The target first temperature value is the first temperature value that is not in the preset temperature range. The preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally. If a first target location exists, then determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period. The first target location is the location where the target first temperature value exists. From the target first temperature value, determine a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range; Determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range; Determine the second average value of all the second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range; The outlier value of each first target location is determined based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference; If an outlier reaches the first target position of the preset outlier threshold, then an outlier position is determined to exist.

[0111] In one possible implementation of this application embodiment, when the combustion anomaly determination module 203 determines the degree of combustion anomaly in the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms of multiple dynamic pressure sensors, it is specifically used for: Calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range. The preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally. Determine the number of second target locations in each temperature field, and determine the outliers of each temperature field based on the temperature range, the second temperature variance, and the number of second target locations; Determine the sum of outliers in the entire temperature field, and determine the degree of the first sub-combustion anomaly based on the sum of outliers and the number of outlier locations; The degree of second-stage combustion anomaly is determined based on the oscillation waveforms from multiple dynamic pressure sensors; The degree of combustion abnormality in the combustion chamber is determined based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

[0112] In one possible implementation of this application embodiment, when determining the degree of combustion anomaly based on the oscillation waveform diagrams of multiple dynamic pressure sensors, the combustion anomaly determination module 203 is specifically used for: The oscillation waveform of each dynamic pressure sensor is converted into a spectrum. Identify the target frequency that matches the preset characteristic frequency from the spectrum diagram; Determine the amplitude corresponding to each target frequency, and identify the target candidate frequencies whose amplitude reaches the preset amplitude threshold corresponding to the target frequency; Determine a second ratio between the number of candidate target frequencies and the total number of target frequencies; The number of target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode is determined, and a third ratio of the number of target frequencies to the number of preset characteristic frequencies in each oscillation mode is determined. The oscillation modes include longitudinal modes along the length of the combustion chamber, tangential modes along the circumferential direction of the combustion chamber cross-section, and radial modes along the radial direction of the combustion chamber cross-section. The hazard value of each oscillation mode at the location of each dynamic pressure sensor is determined based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode. The combustion anomaly value at the location of each dynamic pressure sensor is determined based on the hazard value of each oscillation mode and the second ratio. The second sub-combustion anomaly degree is obtained by summing the combustion anomaly values ​​at all locations of the dynamic pressure sensors.

[0113] In one possible implementation of this application embodiment, when the combustion anomaly determination module 203 determines the hazard value of each oscillation mode at the location of each dynamic pressure sensor based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode, it is specifically used for: The maximum amplitude is determined from the amplitudes of all target candidate frequencies corresponding to each oscillation mode, and the average amplitude of all target candidate frequencies corresponding to each oscillation mode is determined. The baseline hazard value for each oscillation mode is calculated based on the maximum amplitude, average amplitude, corresponding third ratio, and their respective weights. The hazard value of each oscillation mode is determined based on the baseline hazard value of each oscillation mode and the preset hazard coefficient corresponding to each oscillation mode.

[0114] In one possible implementation of this application embodiment, the load control module 204, when controlling the reduction of the gas turbine load, is specifically used for: The degree of combustion abnormality is substituted into the first preset function to obtain the fuel flow reduction value. The first preset function is a function that calculates the fuel flow reduction value based on the degree of combustion abnormality. The degree of combustion anomaly is substituted into the second preset function to obtain the compressor pressure reduction value. The second preset function is a function that calculates the compressor pressure reduction value based on the degree of combustion anomaly. The gas turbine is controlled to operate according to the decrease in fuel flow and pressure to reduce the load.

[0115] In one possible implementation of this application embodiment, the control system 20 of a gas turbine further includes: The output module is used to display the location of the abnormality.

[0116] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the control system 20 of a gas turbine described above can be referred to the corresponding process in the foregoing method embodiments, and will not be repeated here.

[0117] This application provides an electronic device, such as... Figure 3 As shown, Figure 3The illustrated electronic device 30 includes a processor 301 and a memory 303. The processor 301 and the memory 303 are connected, for example, via a bus 302. Optionally, the electronic device 30 may also include a transceiver 304. It should be noted that in practical applications, the transceiver 304 is not limited to one type, and the structure of this electronic device 30 does not constitute a limitation on the embodiments of this application.

[0118] Processor 301 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this application. Processor 301 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0119] Bus 302 may include a pathway for transmitting information between the aforementioned components. Bus 302 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 302 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 3 The symbol is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0120] The memory 303 may be a ROM (Read Only Memory) or other type of static storage device capable of storing static information and instructions, RAM (Random Access Memory) or other type of dynamic storage device capable of storing information and instructions, or an EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium capable of carrying or storing desired program code in the form of instructions or data structures and accessible by a computer, but not limited thereto.

[0121] The memory 303 is used to store application code that executes the solution of this application, and its execution is controlled by the processor 301. The processor 301 is used to execute the application code stored in the memory 303 to implement the content shown in the foregoing method embodiments.

[0122] Electronic devices include, but are not limited to: mobile terminals such as mobile phones, laptops, digital radio receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), and in-vehicle terminals (such as in-vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Servers can also be included. Figure 3 The electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0123] This application provides a computer-readable storage medium storing a computer program, which, when run on a computer, enables the computer to execute the corresponding content in the aforementioned method embodiments. Compared with related technologies, the first temperature values ​​obtained at multiple locations on the exhaust section cross-section in this application embodiment can characterize the combustion status of each burner in the combustion chamber to a certain extent, thereby facilitating subsequent determination of whether there are abnormal locations, i.e., abnormal burners, on the exhaust section cross-section based on the first temperature values ​​at multiple locations. Obtaining the oscillation waveforms of multiple dynamic pressure sensors can reveal the vibration and oscillation of the burner during combustion, thus facilitating subsequent analysis of the degree of combustion abnormality in the combustion chamber. A temperature field of the exhaust section cross-section is generated based on the first temperature values ​​at each temperature acquisition, recording the temperature performance and distribution of the exhaust section cross-section at each temperature acquisition, thereby facilitating... The degree of combustion abnormality in the combustion chamber is then analyzed based on the temperature field. If there are abnormal locations, it indicates that there is an abnormality in the combustion operation of the combustion chamber. The temperature field and the oscillation waveforms of multiple dynamic pressure sensors are key factors affecting the degree of combustion abnormality in the combustion chamber. Moreover, the more abnormal locations there are, the higher the degree of abnormality in the combustion chamber. Therefore, the degree of combustion abnormality in the combustion chamber can be accurately determined by comprehensively analyzing the number of abnormal locations, the temperature field, and the oscillation waveforms. After accurately determining the degree of combustion abnormality, the load of the gas turbine can be precisely controlled to reduce the combustion abnormality, so as to try to eliminate unstable combustion and reduce damage to the gas turbine components by reducing the combustion intensity.

[0124] It should be understood that although the steps in the flowcharts of the accompanying figures are shown sequentially as indicated by the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the accompanying figures may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times, and their execution order is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the sub-steps or stages of other steps.

[0125] The above are only some embodiments of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A control method for a gas turbine, characterized in that, include: The system acquires the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, which are collected multiple times within a preset time period. Each location on the exhaust section cross-section corresponds to a burner. The temperature field of the exhaust section section with respect to each acquisition time is generated based on the first temperature values ​​of multiple locations collected multiple times, and the presence of abnormal locations among the multiple locations is determined based on the first temperature values ​​of the multiple locations. If an abnormal location is found, the degree of combustion abnormality in the combustion chamber is determined based on the temperature field, the number of abnormal locations, and the oscillation waveforms of multiple dynamic pressure sensors. The gas turbine load is reduced based on the degree of combustion anomaly.

2. The control method for a gas turbine according to claim 1, characterized in that, The step of determining whether there are abnormal locations among the multiple locations based on the first temperature values ​​of the multiple locations includes: Determine the first temperature variance for each location within a preset time period; Determine whether a target first temperature value exists at each location. The target first temperature value is a first temperature value that is not within a preset temperature range. The preset temperature range is the operating temperature range within the exhaust section when the gas turbine is running normally. If a first target location exists, then determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period, where the first target location is the location where the target first temperature value exists; From the target first temperature value, a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range are determined; Determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range; Determine the second average value of all the second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range; Anomalies at each first target location are determined based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference. If an outlier reaches the first target position of the preset outlier threshold, then an outlier position is determined to exist.

3. A control method for a gas turbine according to claim 1 or 2, characterized in that, The degree of combustion anomaly within the combustion chamber is determined based on the temperature field, the number of abnormal locations, and the oscillation waveforms from multiple dynamic pressure sensors, including: Calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range, wherein the preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally; The number of second target locations in each temperature field is determined, and outliers in each temperature field are determined based on the temperature range, the second temperature variance, and the number of second target locations. Determine the sum of outliers in the entire temperature field, and determine the degree of the first sub-combustion anomaly based on the sum of outliers and the number of outlier locations; The degree of second sub-combustion anomaly is determined based on the oscillation waveforms of the multiple dynamic pressure sensors; The degree of combustion abnormality in the combustion chamber is determined based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

4. The control method for a gas turbine according to claim 3, characterized in that, The determination of the degree of the second sub-combustion anomaly based on the oscillation waveform diagram of the multiple dynamic pressure sensors includes: The oscillation waveform of each dynamic pressure sensor is converted into a spectrum. Determine the target frequency that matches the preset characteristic frequency from the spectrum diagram; Determine the amplitude corresponding to each target frequency, and identify the target candidate frequencies whose amplitude reaches the preset amplitude threshold corresponding to the target frequency; Determine a second ratio between the number of target candidate frequencies and the total number of target frequencies; The number of target candidate frequencies whose amplitude reaches the corresponding preset amplitude threshold in each oscillation mode is determined, and a third ratio of the number of target frequencies to the number of preset characteristic frequencies in each oscillation mode is determined. The oscillation modes include longitudinal modes along the length of the combustion chamber, tangential modes along the circumferential direction of the combustion chamber cross-section, and radial modes along the radial direction of the combustion chamber cross-section. The hazard value of each oscillation mode at the location of each dynamic pressure sensor is determined based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode. The combustion anomaly value at the location of each dynamic pressure sensor is determined based on the hazard value of each oscillation mode and the second ratio. The second sub-combustion anomaly degree is obtained by summing the combustion anomaly values ​​at all locations of the dynamic pressure sensors.

5. The control method for a gas turbine according to claim 4, characterized in that, The determination of the hazard value of each oscillation mode at the location of each dynamic pressure sensor based on the third ratio corresponding to each oscillation mode and the amplitude of the target candidate frequency corresponding to each oscillation mode includes: The maximum amplitude is determined from the amplitudes of all target candidate frequencies corresponding to each oscillation mode, and the average amplitude of all target candidate frequencies corresponding to each oscillation mode is determined. The baseline hazard value for each oscillation mode is calculated based on the maximum amplitude, average amplitude, corresponding third ratio, and their respective weights. The hazard value of each oscillation mode is determined based on the baseline hazard value of each oscillation mode and the preset hazard coefficient corresponding to each oscillation mode.

6. The control method for a gas turbine according to claim 1, characterized in that, The method of controlling the reduction of gas turbine load based on the degree of combustion anomaly includes: The degree of combustion abnormality is substituted into a first preset function to obtain the fuel flow reduction value. The first preset function is a function that calculates the fuel flow reduction value based on the degree of combustion abnormality. The degree of combustion abnormality is substituted into a second preset function to obtain the compressor pressure reduction value. The second preset function is a function that calculates the compressor pressure reduction value based on the degree of combustion abnormality. The gas turbine is controlled to operate according to the decrease in fuel flow and pressure to reduce the load.

7. The control method for a gas turbine according to claim 1, characterized in that, The method further includes: The output displays the location of the anomaly.

8. A control system for a gas turbine, characterized in that, include: The data acquisition module is used to acquire the first temperature values ​​at multiple locations on the exhaust section cross-section and the oscillation waveforms of multiple dynamic pressure sensors on the gas turbine combustion chamber shell, which are collected multiple times within a preset time period. Each location on the exhaust section cross-section corresponds to a burner. An abnormal location judgment module is used to generate the temperature field of the exhaust section section with respect to each acquisition based on the first temperature values ​​of multiple locations collected multiple times, and to judge whether there is an abnormal location among the multiple locations based on the first temperature values ​​of the multiple locations. The combustion anomaly determination module is used to determine the degree of combustion anomaly in the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms of multiple dynamic pressure sensors when an anomaly location exists. The load control module is used to control the reduction of the gas turbine load based on the degree of combustion abnormality.

9. The control method for a gas turbine according to claim 8, characterized in that, When the abnormal location determination module determines whether there is an abnormal location among the multiple locations based on the first temperature value of the multiple locations, it is specifically used for: Determine the first temperature variance for each location within a preset time period; Determine whether a target first temperature value exists at each location. The target first temperature value is a first temperature value that is not within a preset temperature range. The preset temperature range is the operating temperature range within the exhaust section when the gas turbine is running normally. If a first target location exists, then determine the first ratio of the number of target first temperature values ​​at each first target location to the total number of collections within a preset time period, where the first target location is the location where the target first temperature value exists; From the target first temperature value, a first candidate temperature value that is lower than the lower limit of the preset temperature range and a second candidate temperature value that is higher than the upper limit of the preset temperature range are determined; Determine the first average value of all first candidate temperature values, and calculate the absolute value of the first difference between the first average value and the lower limit of the preset temperature range; Determine the second average value of all the second candidate temperature values, and calculate the absolute value of the second difference between the second average value and the upper limit of the preset temperature range; Anomalies at each first target location are determined based on the first temperature variance, the first ratio, the absolute value of the first difference, and the absolute value of the second difference. If an outlier reaches the first target position of the preset outlier threshold, then an outlier position is determined to exist.

10. A control method for a gas turbine according to claim 8 or 9, characterized in that, When determining the degree of combustion anomaly within the combustion chamber based on the temperature field, the number of anomaly locations, and the oscillation waveforms from multiple dynamic pressure sensors, the combustion anomaly determination module is specifically used for: Calculate the temperature range and the second temperature variance in each temperature field, and determine the second target position where the first temperature value in each temperature field is not in the preset temperature range, wherein the preset temperature range is the operating temperature range in the exhaust section when the gas turbine is running normally; The number of second target locations in each temperature field is determined, and outliers in each temperature field are determined based on the temperature range, the second temperature variance, and the number of second target locations. Determine the sum of outliers in the entire temperature field, and determine the degree of the first sub-combustion anomaly based on the sum of outliers and the number of outlier locations; The degree of second sub-combustion anomaly is determined based on the oscillation waveforms of the multiple dynamic pressure sensors; The degree of combustion abnormality in the combustion chamber is determined based on the degree of the first sub-combustion abnormality and the degree of the second sub-combustion abnormality.

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