A method and system for automatic combustion adjustment of an e-class heavy-duty gas turbine

Abstract

The application relates to a method and system for automatically adjusting the combustion of an E-class heavy-duty gas turbine, wherein the method comprises the following steps: acquiring actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value and actual CO emission of each flame in a secondary combustion chamber of a burner respectively; and adjusting fuel distribution ratios of a primary gas valve and a secondary gas valve according to the flame intensity, the turbine pressure ratio and the exhaust gas temperature, the generator load and the NOx emission value and the CO emission respectively to maintain a premixed stable combustion working condition. Through the application, real-time combustion adjustment of the gas turbine is realized without relying on combustion pulsation pressure monitoring, and the problems that the gas turbine cannot perform real-time combustion adjustment, combustion components are easily damaged and the service life of equipment is shortened are solved.

Description

Technical Field

[0001] This application relates to the field of equipment status control technology, and in particular to a method and system for automatic combustion adjustment applicable to Class E heavy-duty gas turbines. Background Technology

[0002] Gas turbines have numerous advantages in the field of power generation and are a major core equipment for my country's energy development. They are a major power equipment integrating many high-end design, materials, and manufacturing technologies, and are an important symbol of a country's scientific and technological level, military strength, and even comprehensive national power. Currently, there are more than 30 9E heavy-duty gas turbines in China, making them one of the main types of turbines.

[0003] The 9E heavy-duty gas turbine employs premixed combustion to reduce NOx emissions. However, the stable combustion window of premixed combustion is narrow, making it prone to deviations in combustion conditions, abnormal emission levels and combustion stability, and even hot-end component burnout accidents, especially after atmospheric temperature changes or equipment maintenance. Therefore, combustion adjustments are necessary during seasonal transitions or after equipment maintenance to bring combustion back within safe and stable boundaries and ensure emissions meet requirements. In related technologies, gas turbine combustion adjustments are performed according to a schedule or after maintenance, which cannot provide real-time optimization and can easily lead to damage to combustion components and shortened equipment lifespan. Domestic patents disclose several methods for dry, low-NOx combustion adjustment and condition diagnosis in gas turbines, including a quantitative method for heavy-duty gas turbines for periodic manual combustion adjustments. However, this method lacks real-time optimization capabilities and has certain limitations.

[0004] There is no effective solution yet to address the problem that gas turbines cannot adjust combustion in real time, which can easily lead to damage to combustion components and shorten equipment lifespan. Summary of the Invention

[0005] This application provides a method and system for automatic combustion adjustment of Class E heavy-duty gas turbines, which at least solves the problem in the related art that gas turbines cannot perform real-time combustion adjustment, which easily leads to damage to combustion components and shortened equipment life.

[0006] In a first aspect, embodiments of this application provide a method for automatic combustion adjustment applicable to Class E heavy-duty gas turbines, the method comprising:

[0007] The actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission amount of each flame in the secondary combustion chamber of the burner are obtained respectively.

[0008] The fuel distribution ratios of the primary and secondary gas valves are adjusted according to the flame intensity, turbine pressure ratio, exhaust gas temperature, generator load and NOx emission value, and CO emission amount, respectively, to maintain a stable premixed combustion condition.

[0009] In some embodiments, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the flame intensity, the process including:

[0010] Based on preset intensity boundary values, intensity percentage action coefficients, and intensity bias, the flame intensity value is adjusted. The final flame intensity value is determined according to the adjusted flame intensity value and the preset intensity correction coefficient. Based on the final flame intensity value, the adjustment value of the fuel distribution ratio is determined.

[0011] Wherein, the strength boundary value ranges from 0 to 100; the strength percentage effect coefficient ranges from 0 to 20; the strength bias ranges from -15 to 15; and the strength correction coefficient ranges from -1 to 1.

[0012] In some embodiments, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the turbine pressure ratio and the flue gas temperature. The process includes:

[0013] The normal operating value of the exhaust gas temperature is determined based on the turbine pressure ratio. Based on the normal operating temperature value and the actual exhaust gas temperature, the final exhaust gas temperature is determined based on the preset temperature boundary value, temperature action coefficient, temperature offset, and temperature correction coefficient. Based on the final exhaust gas temperature, the adjustment value of the fuel distribution ratio is determined.

[0014] Wherein, the temperature boundary value ranges from 0 to 300; the temperature action coefficient ranges from 0 to 30; the temperature offset ranges from -15 to 15; and the temperature correction coefficient ranges from 0 to 1.

[0015] In some embodiments, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the generator load and NOx emission values. The process includes:

[0016] The normal operating value of NOx emissions is determined based on the generator load. Based on the normal operating value of NOx emissions and the actual NOx emission value, the final NOx emission value is determined based on the preset NOx boundary value, NOx action coefficient, NOx bias and NOx correction coefficient. Based on the final NOx emission value, the adjustment value of the fuel distribution ratio is determined.

[0017] Wherein, the NOX boundary value ranges from 0 to 25; the NOX action coefficient ranges from 0 to 35; the NOX bias ranges from -15 to 15; and the NOX correction coefficient ranges from 0 to 1.

[0018] In some embodiments, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the CO emission level, the process including:

[0019] Based on preset emission thresholds, emission percentage action coefficients, and emission bias, the CO emissions are adjusted. The final CO emissions are determined based on the adjusted CO emissions and preset emission correction coefficients. Based on the final CO emissions, the adjustment value of the fuel allocation ratio is determined.

[0020] Wherein, the range of the emission boundary value is greater than or equal to 0 and less than or equal to 45; the range of the emission percentage effect coefficient is greater than 0 and less than or equal to 55; the range of the emission bias is greater than or equal to -15 and less than or equal to 15; and the range of the emission correction coefficient is greater than or equal to -1 and less than or equal to 1.

[0021] Secondly, embodiments of this application provide a system for automatic combustion adjustment applicable to Class E heavy-duty gas turbines, the system comprising:

[0022] The acquisition module is used to acquire the actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission of each flame in the secondary combustion chamber of the burner.

[0023] The adjustment module is used to adjust the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity, the turbine pressure ratio and the exhaust gas temperature, the generator load and NOx emission value, and the CO emission amount, respectively, in order to maintain the premixed stable combustion condition.

[0024] In some embodiments, the adjustment module adjusts the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity, the process including:

[0025] Based on preset intensity boundary values, intensity percentage action coefficients, and intensity bias, the flame intensity value is adjusted. The final flame intensity value is determined according to the adjusted flame intensity value and the preset intensity correction coefficient. Based on the final flame intensity value, the adjustment value of the fuel distribution ratio is determined.

[0026] Wherein, the strength boundary value ranges from 0 to 100; the strength percentage effect coefficient ranges from 0 to 20; the strength bias ranges from -15 to 15; and the strength correction coefficient ranges from -1 to 1.

[0027] In some embodiments, in the adjustment module, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the turbine pressure ratio and the flue gas temperature. The process includes:

[0028] The normal operating value of the exhaust gas temperature is determined based on the turbine pressure ratio. Based on the normal operating temperature value and the actual exhaust gas temperature, the final exhaust gas temperature is determined based on the preset temperature boundary value, temperature action coefficient, temperature offset, and temperature correction coefficient. Based on the final exhaust gas temperature, the adjustment value of the fuel distribution ratio is determined.

[0029] Wherein, the temperature boundary value ranges from 0 to 300; the temperature action coefficient ranges from 0 to 30; the temperature offset ranges from -15 to 15; and the temperature correction coefficient ranges from 0 to 1.

[0030] Thirdly, embodiments of this application provide an electronic device, including a memory and a processor, characterized in that the memory stores a computer program, and the processor is configured to run the computer program to execute the method for automatic combustion adjustment applicable to Class E heavy-duty gas turbines.

[0031] Fourthly, embodiments of this application provide a storage medium storing a computer program, wherein the computer program is configured to execute the method for automatic combustion adjustment applicable to Class E heavy-duty gas turbines during runtime.

[0032] Compared to related technologies where gas turbines cannot adjust combustion in real time, leading to damage to combustion components and shortened equipment lifespan, this application's embodiment obtains the actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission of each flame in the secondary combustion chamber of the burner. Then, based on these parameters, the fuel distribution ratio of the primary and secondary gas valves is adjusted to maintain stable premixed combustion conditions. This solves the problem of gas turbines being unable to adjust combustion in real time, which easily leads to damage to combustion components and shortened equipment lifespan. Attached Figure Description

[0033] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0034] Figure 1 This is a schematic diagram of an automatic combustion adjustment method for a Class E heavy-duty gas turbine according to the first embodiment of this application;

[0035] Figure 2 This is a structural block diagram of a system for automatic combustion adjustment of a Class E heavy-duty gas turbine according to a second embodiment of this application;

[0036] Figure 3 This is a schematic diagram of a fuel valve according to a second embodiment of this application;

[0037] Figure 4 This is a schematic diagram of the internal structure of an electronic device according to an embodiment of this application. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this application clearer, the application is described and illustrated below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments provided in this application without inventive effort are within the scope of protection of this application.

[0039] Obviously, the accompanying drawings described below are merely some examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without any inventive effort. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this application, any changes to design, manufacturing, or production based on the technical content disclosed in this application are merely conventional technical means and should not be construed as insufficient disclosure of the content of this application.

[0040] In this application, the reference to "embodiment" means that a specific feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0041] Unless otherwise defined, the technical or scientific terms used in this application shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms “a,” “an,” “an,” “the,” and similar words used in this application do not indicate quantity limitation and may indicate singular or plural. The terms “comprising,” “including,” “having,” and any variations thereof used in this application are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or device that includes a series of steps or modules (units) is not limited to the listed steps or units, but may also include steps or units not listed, or may include other steps or units inherent to these processes, methods, products, or devices. The terms “connected,” “linked,” “coupled,” and similar words used in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. “Multiple” used in this application refers to two or more. “And / or” describes the relationship between related objects, indicating that three relationships may exist; for example, “A and / or B” can represent: A alone, A and B simultaneously, and B alone. The character " / " generally indicates that the preceding and following objects are in an "or" relationship. The terms "first," "second," and "third" used in this application are merely to distinguish similar objects and do not represent a specific ordering of the objects.

[0042] The purpose of this invention is to overcome the domestic technological gap and propose an automatic combustion adjustment method for E-class heavy-duty gas turbines for the DLN1.0 combustion system. This method reduces nitrogen oxide emissions from the gas turbine in real time while avoiding combustion oscillations, thus maintaining stable combustion in the gas turbine. Figure 1 This is a schematic diagram of an automatic combustion adjustment method for a Class E heavy-duty gas turbine according to the first embodiment of this application, as shown below. Figure 1 As shown, the process includes the following steps:

[0043] Step S101: Obtain the actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission of each flame in the secondary combustion chamber of the burner.

[0044] In step S102, the fuel distribution ratio of the primary gas valve and the secondary gas valve is adjusted according to the flame intensity, turbine pressure ratio and exhaust gas temperature, generator load and NOx emission value, and CO emission amount, respectively, in order to maintain the premixed stable combustion condition.

[0045] Through the above steps S101 to S102, compared with the problem in related technologies that gas turbines cannot perform real-time combustion adjustment, which easily leads to damage to combustion components and shortened equipment life, the embodiments of this application obtain the actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission of each flame in the secondary combustion chamber of the burner; and then adjust the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity, turbine pressure ratio and exhaust gas temperature, generator load and NOx emission value, and CO emission, respectively, to maintain a stable premixed combustion condition. This solves the problem that gas turbines cannot perform real-time combustion adjustment, which easily leads to damage to combustion components and shortened equipment life. It realizes real-time combustion adjustment of the gas turbine without relying on combustion pulsation pressure monitoring, and ensures that combustion is carried out within a safe and stable boundary even when the atmospheric temperature changes greatly, and ensures that pollutant emission indicators do not exceed the standard.

[0046] In some embodiments, the process of adjusting the fuel distribution ratio according to the flame temperature includes adjusting the flame intensity value based on a preset intensity boundary value, an intensity percentage action coefficient, and an intensity bias; determining the final flame intensity value based on the adjusted flame intensity value and a preset intensity correction coefficient; and determining the adjustment value of the fuel distribution ratio based on the final flame intensity value.

[0047] For example, an adaptive flame intensity adjustment loop can be designed; when the gas turbine is in premixed stable combustion condition, the fuel distribution ratio is adaptively adjusted according to the flame intensity of the four flame detectors in the secondary combustion chamber of the burner, and the calculation formula is Formula 1:

[0048] Formula 1

[0049] In the formula, FL represents the strength of 4 flame detectors; This is the flame intensity adaptive intensity correction coefficient. ; This is the percentage effect coefficient of flame intensity. ; For bias, ; For flame intensity adaptive boundary, .

[0050] via rate Output after limitation .

[0051] In some embodiments, the process of adjusting the fuel distribution ratio based on the turbine pressure ratio and the exhaust gas temperature includes: determining an operating temperature value for the exhaust gas based on the turbine pressure ratio; determining a final exhaust gas temperature based on the operating temperature value and the actual exhaust gas temperature, using a preset temperature boundary value, a temperature action coefficient, a temperature offset, and a temperature correction coefficient; and determining an adjustment value for the fuel distribution ratio based on the final exhaust gas temperature.

[0052] For example, an adaptive adjustment loop for exhaust gas temperature can be designed; when the gas turbine is in a premixed stable operating condition, the fuel distribution ratio is adaptively adjusted based on the exhaust gas temperature and the design or normal operating value of the exhaust gas temperature calculated under the operating conditions. The calculation formula is Formula 2:

[0053] Formula 2

[0054]

[0055] In the formula, This is the actual turbine pressure ratio; To and The function between these parameters is used to calculate the design or normal operating value of the flue gas temperature. , , These are the coefficients to be determined; This refers to the actual exhaust gas temperature. This is the adaptive intensity correction coefficient for flue gas temperature. ; For the adaptive boundary of flue gas temperature, ; This is the coefficient of influence for flue gas temperature. , For bias, .

[0056] via rate Output after limitation .

[0057] In some embodiments, the process of adjusting the fuel allocation ratio based on the generator load and NOx emission value includes: determining the normal operating value of NOx emission based on the generator load; determining the final NOx emission value based on the normal operating value of NOx emission and the actual NOx emission value, using preset NOx boundary values, NOx action coefficients, NOx bias, and NOx correction coefficients; and determining the adjustment value of the fuel allocation ratio based on the final NOx emission value.

[0058] For example, an adaptive NOx emission adjustment loop can be designed; when the gas turbine is in premixed stable operating condition, the fuel distribution ratio is adaptively adjusted according to the gas turbine load and NOx emission value. The calculation formula is as follows:

[0059] Formula 3

[0060]

[0061] In the formula, For gas turbine generator load; To and The function between these parameters is used to calculate the normal operating value of NOx emissions as the load changes; , , These are the coefficients to be determined; This represents the actual NOx emissions. This is the adaptive intensity correction factor for NOx emissions. ; For NOx emission adaptive boundary, ; This is the NOx emission impact factor. , For bias, .

[0062] via rate Output after limitation .

[0063] In some embodiments, the process of adjusting the fuel allocation ratio based on CO emissions includes adjusting the CO emissions based on preset emission boundary values, emission percentage action coefficients, and emission bias; determining the final CO emissions based on the adjusted CO emissions and preset emission correction coefficients; and determining the adjustment value of the fuel allocation ratio based on the final CO emissions.

[0064] For example, an adaptive adjustment loop for CO emissions can be designed; when the gas turbine is in premixed stable combustion condition, the fuel distribution ratio is adaptively adjusted according to the CO emissions, and the calculation formula is as follows:

[0065] Formula 4

[0066] In the formula, CO represents CO emissions; This is an adaptive intensity correction factor for CO emissions. ; This is the percentage effect factor for CO emissions. ; For bias, ; For the adaptive boundary of CO emission intensity, .

[0067] via rate Output after limitation .

[0068] This embodiment also provides a system for automatic combustion adjustment applicable to Class E heavy-duty gas turbines. Figure 2 This is a structural block diagram of a system for automatic combustion adjustment of a Class E heavy-duty gas turbine according to a second embodiment of this application. Figure 3 This is a schematic diagram of a fuel valve according to a second embodiment of this application, as shown below. Figure 2 and Figure 3 As shown, the system includes a flame intensity adaptive adjustment algorithm module, a flue gas temperature adaptive adjustment algorithm module, a NOx emission adaptive adjustment algorithm module, and a CO emission adaptive adjustment algorithm module. The system adjusts the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity, turbine pressure ratio, flue gas temperature, generator load, NOx emission value, and CO emission amount, respectively, in order to maintain the premixed stable combustion condition.

[0069] In conjunction with the above-described method for automatic combustion adjustment of a Class E heavy-duty gas turbine, this application embodiment can provide a storage medium for implementation. The storage medium stores a computer program; when executed by a processor, the computer program implements any of the above-described methods for automatic combustion adjustment of a Class E heavy-duty gas turbine.

[0070] In one embodiment, a computer device is provided, which may be a terminal. The computer device includes a processor, memory, a network interface, a display screen, and input devices connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, it implements a method for automatic combustion adjustment applicable to Class E heavy-duty gas turbines. The display screen may be a liquid crystal display (LCD) or an e-ink display. The input devices may be a touch layer covering the display screen, buttons, a trackball, or a touchpad mounted on the computer device casing, or an external keyboard, touchpad, or mouse.

[0071] In one embodiment, Figure 4 This is a schematic diagram of the internal structure of an electronic device according to an embodiment of this application, such as... Figure 4 As shown, an electronic device is provided, which can be a server, and its internal structure diagram can be as follows. Figure 4 As shown, the electronic device includes a processor, a network interface, internal memory, and non-volatile memory connected via an internal bus. The non-volatile memory stores the operating system, computer programs, and a database. The processor provides computing and control capabilities, the network interface communicates with external terminals via a network, the internal memory provides an environment for the operation of the operating system and computer programs, the computer programs are executed by the processor to implement a method for automatic combustion adjustment applicable to Class E heavy-duty gas turbines, and the database stores data.

[0072] Those skilled in the art will understand that Figure 4 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the electronic device to which the present application is applied. The specific electronic device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0073] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. This computer program can be stored in a non-volatile computer-readable storage medium. When executed, the computer program can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), RAMbus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0074] Those skilled in the art should understand that, for the sake of brevity, not all possible combinations of the various technical features in the above embodiments have been described. However, as long as there is no contradiction in the combination of these technical features, they should all be considered to be within the scope of this specification.

[0075] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A method for automatic combustion adjustment of a heavy-duty gas turbine suitable for E-class, characterized in that, The method comprises: respectively acquiring actual flame intensity, actual turbine pressure ratio and exhaust gas temperature, actual generator load and NOx emission value, and actual CO emission amount of each flame in the secondary combustion chamber of the combustor; respectively according to the flame intensity, the turbine pressure ratio and the exhaust gas temperature, the generator load and the NOx emission value, and the CO emission amount, adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve to maintain the premixed stable combustion condition, wherein according to the flame intensity, the process of adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve comprises: based on the preset intensity boundary value, the intensity percentage action coefficient and the intensity bias, adjusting the flame intensity value, determining the final flame intensity value according to the adjusted flame intensity value and the preset intensity correction coefficient, and based on the final flame intensity value, determining the adjustment value of the fuel distribution ratio, wherein the adjustment value satisfies the following formula: wherein, is an adjustment value for the fuel distribution ratio, FL is the intensity of the 4 flames; K FAT0 is a flame intensity self-adaptation intensity correction coefficient, K FAT1 is a flame intensity self-adaptation intensity correction coefficient, K FAT0 is a flame intensity self-adaptation intensity correction coefficient, K FAT1 ∈[-1, 1]; K M is a flame intensity self-adaptation intensity correction coefficient, K N is a flame intensity self-adaptation intensity correction coefficient, K M is a flame intensity self-adaptation intensity correction coefficient, K N ∈(0, 20]; K0, K1 are biases, K0, K1 ∈[-15, 15]; N, M are flame intensity self-adaptation boundaries, M, N ∈[0, 100].

2. The method of claim 1, wherein, according to the turbine pressure ratio and the exhaust gas temperature, adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve, the process comprising: determining the normal operation value of the exhaust gas temperature according to the turbine pressure ratio, and based on the preset temperature boundary value, the temperature action coefficient, the temperature bias and the temperature correction coefficient, determining the final exhaust gas temperature according to the normal operation value of the temperature and the actual exhaust gas temperature, and based on the final exhaust gas temperature, determining the adjustment value of the fuel distribution ratio; wherein the value range of the temperature boundary value is greater than or equal to 0 and less than or equal to 300; the value range of the temperature action coefficient is greater than or equal to 0 and less than or equal to 30; the value range of the temperature bias is greater than or equal to -15 and less than or equal to 15; and the value range of the temperature correction coefficient is greater than or equal to 0 and less than or equal to 1.

3. The method of claim 1, wherein, according to the generator load and the NOx emission value, adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve, the process comprising: determining the normal operation value of NOx emission according to the generator load, and based on the preset NOx boundary value, the NOx action coefficient, the NOx bias and the NOx correction coefficient, determining the final NOx emission value according to the normal operation value of NOx emission and the actual NOx emission value, and based on the final NOx emission value, determining the adjustment value of the fuel distribution ratio; wherein the value range of the NOx boundary value is greater than or equal to 0 and less than or equal to 25; the value range of the NOx action coefficient is greater than or equal to 0 and less than or equal to 35; the value range of the NOx bias is greater than or equal to -15 and less than or equal to 15; and the value range of the NOx correction coefficient is greater than or equal to 0 and less than or equal to 1.

4. The method of claim 1, wherein, according to the CO emission amount, adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve, the process comprising: adjust the CO emission based on a preset emission boundary value, an emission percentage action coefficient and an emission bias, determine a final CO emission according to the adjusted CO emission and a preset emission correction coefficient, and determine an adjustment value of the fuel distribution ratio based on the final CO emission; wherein the emission boundary value ranges from greater than or equal to 0 to less than or equal to 45, the emission percentage action coefficient ranges from greater than 0 to less than or equal to 55, the emission bias ranges from greater than or equal to -15 to less than or equal to 15, and the emission correction coefficient ranges from greater than or equal to -1 to less than or equal to 1.

5. A system for automatic combustion adjustment of a class E heavy duty gas turbine, characterized by The system comprises: an acquisition module configured to acquire actual flame intensity, actual turbine pressure ratio and flue gas temperature, actual generator load and NOx emission value, and actual CO emission of each flame in the secondary combustion chamber of the combustor, respectively; an adjustment module configured to adjust fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity, the turbine pressure ratio and the flue gas temperature, the generator load and the NOx emission value, and the CO emission, respectively, to maintain premixed stable combustion conditions, wherein adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the flame intensity comprises: adjusting the flame intensity value based on a preset intensity boundary value, an intensity percentage action coefficient and an intensity bias, determining a final flame intensity value according to the adjusted flame intensity value and a preset intensity correction coefficient, and determining an adjustment value of the fuel distribution ratio based on the final flame intensity value, wherein the adjustment value satisfies the following formula: wherein, is the adjustment value for the fuel distribution ratio, FL is the 4 flame detection intensity; K FAT0 , FAT1 is the flame intensity self-adaptive intensity correction coefficient, K FAT0 , FAT1 ∈[-1,1]; K M , N is the flame intensity percentage action coefficient, K M , N ∈(0,20]; K0,K1 are biases, K0,K1∈[-15,15]; N,M are flame intensity self-adaptive boundaries, M,N∈[0,100].

6. The system of claim 5, wherein, In the adjustment module, adjusting the fuel distribution ratio of the primary gas valve and the secondary gas valve according to the turbine pressure ratio and the flue gas temperature comprises: determining a flue gas temperature normal operation value according to the turbine pressure ratio, determining a final flue gas temperature based on a preset temperature boundary value, a temperature action coefficient, a temperature bias and a temperature correction coefficient according to the temperature normal operation value and the actual flue gas temperature, and determining an adjustment value of the fuel distribution ratio based on the final flue gas temperature; wherein the temperature boundary value ranges from greater than or equal to 0 to less than or equal to 300, the temperature action coefficient ranges from greater than or equal to 0 to less than or equal to 30, the temperature bias ranges from greater than or equal to -15 to less than or equal to 15, and the temperature correction coefficient ranges from greater than or equal to 0 to less than or equal to 1. 7.An electronic device comprising a memory and a processor, the electronic device characterized by, The memory stores a computer program, and the processor is configured to run the computer program to execute the method for automatically adjusting the combustion of the E-class heavy gas turbine according to any one of claims 1 to 4.

8. A storage medium, characterized by The storage medium stores a computer program, wherein the computer program is configured to execute the method for automatically adjusting the combustion of the E-class heavy gas turbine according to any one of claims 1 to 4 when running.

Images