Combustion state evaluation method, device, equipment and medium for gas turbine

Abstract

The present application relates to a method, device, equipment and medium for evaluating the combustion state of a gas turbine. The method comprises obtaining various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration, integrating the various combustion state parameters into a comprehensive parameter, calculating the value of the comprehensive parameter each time after a combustion adjustment test is completed, and evaluating the combustion state of the gas turbine according to the value of the comprehensive parameter. The method is not only simple to operate, but also shortens the time of the entire experiment. At the same time, the selection of the optimal value during the combustion adjustment test is not only objective but also unified, thereby solving the problems in the combustion state evaluation method of the gas turbine in the related art that the evaluation time is too long as the number of test point parameters continues to increase, and the selection of the optimal value (i.e., the optimal ratio) during the combustion adjustment test is highly subjective and lacks uniformity.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to a method, device, equipment and medium for evaluating the combustion state of a gas turbine. Background Art

[0002] In order to reduce the NOx emission of gas turbines, modern advanced gas turbines all use premixed combustion technology. Before combustion, the fuel and oxygen (or air) are premixed into a uniform mixture. This combustible mixture is called premixed gas. The process of ignition and combustion of the premixed gas in the burner is called premixed combustion. The combustion stability window of premixed combustion is narrow, and the combustion dynamic pressure needs to be monitored in real time for adjustment, so that all indicators related to combustion in the gas turbine are at a healthy level.

[0003] At present, the combustion state evaluation method of gas turbines has the following disadvantages. On the one hand, during the combustion adjustment process, each test point needs to record each parameter (for example, exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration, CO emission concentration and other parameters) separately. After the test is completed, each parameter of each test point is evaluated separately to find the optimal test point. The process is complicated, and with the increasing number of test point parameters, the evaluation time is also increasing. On the other hand, at each adjustment point, the combustion stability, emission index, and unit safety index will have different values, and there is a mutual constraint relationship between the indicators, so that the combustion state of each test point cannot be given the same standard. Therefore, finding a fuel ratio that can take into account all indicators depends entirely on the experience of the adjustment test personnel. However, different test personnel perform combustion adjustment tests and finally give different adjustment results, which makes the selection of the optimal value (i.e., the optimal ratio) in the combustion adjustment test process highly subjective and not uniform.

[0004] At present, for the combustion state evaluation method of gas turbines in related technologies, as the number of test point parameters continues to increase, the evaluation time is too long, and the selection of the optimal value (i.e. the optimal ratio) during the combustion adjustment test is highly subjective and lacks uniformity. No effective solution has been proposed yet. Summary of the invention

[0005] The embodiments of the present application provide a method, device, equipment and medium for evaluating the combustion state of a gas turbine, so as to at least solve the problems in the combustion state evaluation method of a gas turbine in the related art, that the evaluation time is too long as the number of test point parameters continues to increase, and that the selection of the optimal value (i.e., the optimal ratio) during the combustion adjustment test is highly subjective and lacks uniformity.

[0006] In a first aspect, an embodiment of the present application provides a method for evaluating a combustion state of a gas turbine, the method comprising:

[0007] Acquiring various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust gas dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration;

[0008] Integrate each combustion state parameter into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1;

[0009] Each time after the combustion adjustment test is completed, the value of the comprehensive parameter is calculated, and the combustion state of the gas turbine is evaluated based on the value of the comprehensive parameter.

[0010] In some embodiments, when the total number of the combustion state parameters is N, integrating the combustion state parameters into a comprehensive parameter includes:

[0011] Mapping the limit values ​​of the combustion state parameters into corresponding first line segments according to a preset ratio, wherein the length of each first line segment is the same as the limit value of each combustion state parameter;

[0012] Mapping the measured values ​​of each combustion state parameter into a corresponding second line segment according to a preset ratio; wherein the length of each second line segment is the same as the measured value of each combustion state parameter;

[0013] When each second line segment is respectively disposed on each first line segment and each second line segment and each first line segment have the same first endpoint, a common endpoint formed by aggregating the first endpoints of each first line segment is taken as the origin O, where N is a positive integer greater than or equal to 4;

[0014] When the lengths of the first line segments are the same, a regular N-gon is formed according to the origin O and the second endpoints of the first line segments, and the area of ​​the regular N-gon is calculated to obtain a first area;

[0015] The origin O and the second endpoints of each second line segment form an N-gon, and the area of ​​the N-gon is calculated to obtain a second area;

[0016] The first area and the second area are used to integrate various combustion state parameters into a comprehensive parameter.

[0017] In some embodiments, calculating the value of the comprehensive parameter includes:

[0018] calculating a ratio of the second area to the first area;

[0019] Subtracting the ratio from 1 yields the value of the comprehensive parameter.

[0020] In some embodiments, when N is 5, the calculation formula of the comprehensive parameter is:

[0021]

[0022] in, is the comprehensive parameter, is the second area, is the first area.

[0023] In some embodiments, the calculation formula for integrating various combustion state parameters into a comprehensive parameter using the first area and the second area is as follows:

[0024]

[0025] in, is the ratio of exhaust dispersion to allowable dispersion, is the measured value of the dynamic pressure level in the combustion chamber, is the measured value of nitrogen oxide emission level, is the measured value of CO emission level.

[0026] In some embodiments, the combustion state parameter also includes flame intensity.

[0027] In some embodiments, after calculating the value of the comprehensive parameter each time after the combustion adjustment test is completed, the method further includes:

[0028] The value of the comprehensive parameter closest to 1 in each combustion adjustment test is selected as the optimal fuel ratio value during the combustion adjustment test.

[0029] In a second aspect, an embodiment of the present application provides a combustion state evaluation device for a gas turbine, the device comprising:

[0030] An acquisition module, used for acquiring various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration;

[0031] An integration module, used to integrate various combustion state parameters into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1;

[0032] The evaluation module is used to calculate the value of the comprehensive parameter each time after the combustion adjustment test is completed, and evaluate the combustion state of the gas turbine according to the value of the comprehensive parameter.

[0033] In a third aspect, an embodiment of the present application provides an electronic device, comprising a processor and a storage medium storing a computer program, wherein the computer program, when executed by the processor, implements any of the methods described above.

[0034] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements any of the methods described above.

[0035] Compared with the related art, the combustion state evaluation method of the gas turbine provided in the embodiment of the present application needs to record each parameter separately, and evaluate each parameter of each test point separately after the test is completed, which makes the whole adjustment step too complicated, and as the number of test point parameters increases, the evaluation time also increases. In this embodiment, on the one hand, several combustion state parameters are integrated into one comprehensive parameter, that is, no matter how many combustion state parameters there are, the combustion state of the gas turbine can be comprehensively reflected by one comprehensive parameter, which is not only simple to operate, but also shortens the time of the whole experiment. On the other hand, compared with the previous method that all depends on the experience of the adjustment test personnel, different test personnel When the personnel conduct the combustion adjustment test, the final adjustment results are also different, which makes the selection of the optimal value (that is, the optimal ratio) in the combustion adjustment test process subjective and inconsistent. In this embodiment, the combustion state of the gas turbine can be comprehensively reflected through a comprehensive parameter. Each test condition only needs to compare the comprehensive parameter and select the operating point where the value of the comprehensive parameter is close to 1, so that the selection of the optimal value in the combustion adjustment test process is not only objective but also consistent, which solves the problem that the evaluation method of the combustion state of the gas turbine in the related art leads to a long evaluation time as the number of test point parameters continues to increase, and the selection of the optimal value (that is, the optimal ratio) in the combustion adjustment test process is subjective and inconsistent. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0037] Figure 1 is a schematic flow chart of a combustion state evaluation method for a gas turbine according to an embodiment of the present application;

[0038] Figure 2 is a first schematic diagram that can comprehensively reflect the degree of proximity between various parameters of the gas turbine and the limit value according to an embodiment of the present application;

[0039] Figure 3 is a structural block diagram of a combustion state evaluation device for a gas turbine according to an embodiment of the present application;

[0040] Figure 4 It is a schematic diagram of the internal structure of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solutions and advantages of the present application clearer, the present application is described and illustrated below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments provided in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the contents disclosed in the present application, some changes such as design, manufacturing or production based on the technical contents disclosed in the present application are only conventional technical means, and should not be understood as insufficient contents disclosed in the present application.

[0042] Reference to "embodiments" in this application means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those of ordinary skill in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0043] Unless otherwise defined, the technical terms or scientific terms involved in this application should be understood by people with ordinary skills in the technical field to which this application belongs. The words "one", "a", "a", "the" and the like involved in this application do not indicate a quantity limitation, and may indicate the singular or plural. The terms "include", "comprise", "have" and any of their variations involved in this application are intended to cover non-exclusive inclusions; 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 that are not listed, or may also include other steps or units inherent to these processes, methods, products or devices. The words "connect", "connected", "coupled" and the like involved in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The "multiple" involved in this application means greater than or equal to two. "And / or" describes the association relationship of associated objects, indicating that there can be three relationships. For example, "A and / or B" can mean: A exists alone, A and B exist at the same time, and B exists alone. The terms "first", "second", "third" and the like involved in the present application are merely used to distinguish similar objects and do not represent a specific ordering of the objects.

[0044] The invention provides a method for evaluating the combustion state of a gas turbine.

[0045] Figure 1 is a flow chart of a method for evaluating the combustion state of a gas turbine according to an embodiment of the present application, with reference to Figure 1 In one embodiment of the present invention, a method for evaluating the combustion state of a gas turbine is provided by the present invention, and the method comprises the following steps:

[0046] Step S101, obtaining various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration; of course, in other embodiments, the combustion state parameters may also include others. It is easy to understand that the various combustion state parameters are parameters indicating the non-uniformity of the exhaust temperature of the gas turbine.

[0047] Step S102, integrating various combustion state parameters into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1; it should be noted that the closer the comprehensive parameter is to 1, the more stable the combustion state of the gas turbine is.

[0048] Step S103, each time after the combustion adjustment test is completed, the value of the comprehensive parameter is calculated, and the combustion state of the gas turbine is evaluated according to the value of the comprehensive parameter.

[0049] Compared with the related art, the above steps S101 to S103 need to record each parameter separately, and evaluate each parameter of each test point separately after the test is completed, which makes the whole adjustment step too complicated, and as the number of test point parameters increases, the evaluation time also increases. In this embodiment, on the one hand, a plurality of combustion state parameters are integrated into a comprehensive parameter, that is, no matter how many combustion state parameters there are, the combustion state of the gas turbine can be comprehensively reflected by a comprehensive parameter, which not only reduces the operation steps, but also shortens the time of the whole test. On the other hand, compared with the previous method of relying entirely on the experience of the adjustment test personnel, different test personnel make combustion adjustment tests. The test results finally given are also different, which makes the selection of the optimal value (i.e., the optimal ratio) in the combustion adjustment test process more subjective and lacks uniformity. In this embodiment, a comprehensive parameter can comprehensively reflect the combustion state of the gas turbine. Each test condition only needs to compare the comprehensive parameter and select the operating point where the value of the comprehensive parameter is close to 1, so that the selection of the optimal value in the combustion adjustment test process is not only objective but also unified, which solves the problem that the combustion state evaluation method of the gas turbine in the related art leads to a long evaluation time as the number of test point parameters continues to increase, and the selection of the optimal value (i.e., the optimal ratio) in the combustion adjustment test process is more subjective and lacks uniformity.

[0050] Considering that there are several parameters reflecting the combustion state of the gas turbine, each parameter has both a measured value and a limit value. The dimensionless parameter can be used to represent the closeness of the parameter to the limit value. Back to this case, if each parameter is also represented by a dimensionless parameter, the closeness of each parameter of the gas turbine to the limit value can be comprehensively reflected. The larger the value, the closer the combustion state is to the limit value, and the combustion tends to be unstable. In addition, those skilled in the art know that dimensionless parameters refer to several basic units and many derived units specified in metrology. Derived units can be expressed in basic units. Using basic units to express physical quantities is a dimensional expression. There are many constants in physics (also called constants, such as the gravitational constant, Avogadro's constant, etc.), some of which have no units, which are dimensionless coefficients. Some common dimensionless quantities include pi, Euler's constant and golden ratio. In addition, for the convenience of explanation, the parameters of the combustion state are referred to as parameters below, which are the measured values ​​of each test, and will not be explained one by one in the future.

[0051] Specifically, assuming that there are N parameters that can reflect the combustion state of the gas turbine, these N parameters are f1, f2...fn, and the limit value of each parameter is f1-lim, f2-lim...fn-lim, then the calculation formula of the dimensionless parameter is:

[0052]

[0053] in, dimensionless parameter representing parameter and limit value, represents the nth combustion state parameter, Indicates the maximum value of the nth combustion state parameter.

[0054] It is easy to understand that the dimensionless parameter can indicate how close the parameter is to the limit value. In other words, the dimensionless parameter can comprehensively reflect how close the parameters of the gas turbine are to the limit value. The larger the value of the dimensionless parameter is, the closer the combustion state is to the limit value, and the combustion tends to be unstable.

[0055] Figure 2 is a first schematic diagram that can comprehensively reflect the proximity of various parameters of the gas turbine to the limit value according to the embodiment of the present application. In order to make the combustion state of the gas turbine at each test point have a unified evaluation standard, refer to Figure 2 In some embodiments, when the total number of combustion state parameters is N, integrating the combustion state parameters into a comprehensive parameter comprises the following steps:

[0056] According to a preset ratio, the limit value of each combustion state parameter is mapped into a first line segment corresponding to each of them, wherein the length of each first line segment is the same as the limit value of each combustion state parameter;

[0057] According to the preset ratio, the measured value of each combustion state parameter is mapped into a corresponding second line segment; wherein the length value of each second line segment is the same as the measured value of each combustion state parameter; in this embodiment, for the convenience of understanding, the length value of the preset ratio is adjusted so that the length value of each first line segment and the limit value of each combustion state parameter are both set to 1. Of course, in other embodiments, the preset ratio can be set according to user needs and is not specifically limited here;

[0058] Specifically, refer to Figure 2 In this embodiment, when the number of combustion state parameters is 5, the limit value of each combustion state parameter is mapped into a corresponding first line segment according to a preset ratio, which are line segment OA, line segment OB, line segment OC, line segment OD and line segment OE in the figure respectively; the measured value of each combustion state parameter is mapped into a corresponding second line segment according to a preset ratio, which are line segment OA`, line segment OB`, line segment OC`, line segment OD` and line segment OE` in the figure respectively.

[0059] When each second line segment is respectively arranged on each first line segment, and each second line segment and each first line segment have the same first endpoint, a common endpoint formed by aggregating the first endpoints of each first line segment is taken as the origin O, wherein N is a positive integer greater than or equal to 4; for example, in this embodiment, N is 5, and of course in other embodiments, N can also be 4, 6, 7, etc. or other, which is not specifically limited here;

[0060] When the lengths of the first line segments are the same (i.e., all are 1), a regular N-gon is formed according to the origin O and the second endpoints of the first line segments, and the area of ​​the regular N-gon is calculated to obtain the first area. For example, in this embodiment, a regular pentagon is formed according to the origin O and the second endpoints of the first line segments. , calculate the regular pentagon The area of ​​​​the first area ;

[0061] The origin O and the second endpoints of each second line segment form an N-gon, and the area of ​​the N-gon is calculated to obtain the second area. For example, in this embodiment, the origin O and the second endpoints of each second line segment form a pentagon. , calculate the N-gon The area of ​​​​the second area Of course, in other embodiments, when N is different, the first area and the second area are also different. Those skilled in the art can calculate the first area and the second area according to existing mathematical methods. In other words, as long as the first area and the second area can be calculated, the specific mathematical method is not specifically limited here.

[0062] The first area and the second area are used to integrate the various combustion state parameters into a comprehensive parameter, so that the combustion state of the gas turbine at each test point has a unified evaluation standard, thereby facilitating the subsequent evaluation of the combustion state of the gas turbine.

[0063] It should be noted that each side of the polygon (i.e., N-gon) corresponds to a parameter, which is not fixed. For example, the measured value of exhaust dispersion can be a pentagon. Any edge in the line segment OA`, OB`, OC`, OD` and OE` can be any one of the line segments, and the above situations are within the protection scope of this patent.

[0064] In order to more intuitively evaluate the combustion state of the gas turbine through the value of the comprehensive parameter, in some embodiments, calculating the value of the comprehensive parameter includes the following steps:

[0065] The ratio of the second area to the first area is calculated; thus, the ratio can comprehensively reflect the degree of proximity of various parameters of the gas turbine to the limit values. The larger the value, the closer the combustion state is to the limit value, and the combustion tends to be unstable.

[0066] The value of the comprehensive parameter is obtained by subtracting the ratio from 1. The physical meaning of the value of the comprehensive parameter is the combustion stability of the gas turbine. The larger the value (or the closer it is to 1), the more stable the combustion of the gas turbine.

[0067] In one embodiment, referring to Figure 2 , when N is 5, the calculation formula of the comprehensive parameters is:

[0068]

[0069] in, is a comprehensive parameter, is the second area, It is worth noting that, in other embodiments, as N changes, the calculation formula of the comprehensive parameter will also change accordingly, and the calculation formula of the comprehensive parameter obtained according to the above concept is also within the protection scope of this application.

[0070] In one embodiment, the comprehensive parameter may also be expressed by the following function:

[0071]

[0072] Among them, C0 represents the comprehensive parameter, Indicates various combustion state parameters. If a parameter F (i.e. a combustion state parameter) that constitutes C0 is also composed of several parameters P, then the calculation method of C0 parameters is also applicable to F. Parameter F can be expressed by the following function:

[0073]

[0074] Where, F represents the combustion state parameter, represents the function of the parameters that make up the parameter F, It should be noted that as the number of combustion state parameters changes, the expression of the function of the comprehensive parameters will also change, and the functions obtained according to the above conception are all within the protection scope of this application.

[0075] In one embodiment, the calculation formula for integrating various combustion state parameters into a comprehensive parameter using the first area and the second area is as follows:

[0076]

[0077] in, is the ratio of exhaust dispersion S1 to allowable dispersion TXSPL, is the measured value of the dynamic pressure level in the combustion chamber, is the measured value of nitrogen oxide emission level, is the measured value of CO emission level.

[0078] in addition, The calculation formula is S0=S1 / TXSPL, and S0 can reflect the health of the unit in terms of dispersion.

[0079] In some embodiments, the calculation formula of the ratio of the allowable dispersion is as follows:

[0080]

[0081] in, To allow for dispersion, is the average temperature of the exhaust gas during the combustion engine, is the gas turbine exhaust temperature gain coefficient, is the combustion engine exhaust temperature bias constant, is the compressor exhaust temperature,

[0082] is the compressor exhaust temperature gain coefficient, is the dispersion bias constant, KSLP8 is the first-order inertia link bias constant, is the time constant of the first-order inertia link;

[0083] In addition, those skilled in the art know that a combustion engine (i.e. a heavy-duty gas turbine) generally has several exhaust thermocouples evenly distributed along the circumferential direction in the rear passage of the turbine exhaust diffuser to measure the exhaust temperature, where the difference between the highest temperature and the lowest temperature is called the exhaust dispersion (S1). When the exhaust dispersion exceeds or approaches the allowable dispersion (TXSPL), it means that there is a problem with the combustion system.

[0084] The calculation formula for the measured value of the combustion chamber dynamic pressure level is as follows:

[0085]

[0086] in, is the measured value of the dynamic pressure level in the combustion chamber, is the number of frequency bands, is the maximum measured amplitude of the ith frequency band, is the dynamic pressure alarm value of the ith frequency band, is the maximum value of the measured amplitude of the nth frequency band, is the dynamic pressure alarm value of the nth frequency band, is the maximum value of the measured amplitude of the first frequency band, is the dynamic pressure alarm value of the first frequency band;

[0087] In addition, those skilled in the art know that a combustion dynamic pressure monitoring sensor is installed in each combustion cylinder of a gas turbine. The sensor signal is converted into a frequency domain signal after fast Fourier transformation. The frequency domain signal is divided into n frequency bands, such as the first frequency band of 10Hz~70Hz, the second frequency band of 70 Hz~110 Hz, the third frequency band of 110 Hz~250 Hz, and the fourth frequency band of 250 Hz~600Hz. The frequency band division method is related to the dynamic frequency response of the gas turbine. The measurement data per second will count the maximum amplitude corresponding to each frequency band. This amplitude is the maximum value of the amplitudes of different frequencies in the frequency band. For example, the maximum amplitude of the first frequency band is 5kPa, which means that there is a certain frequency in the frequency range of 10Hz~70Hz. The amplitude is 5kPa, and 5kPa is the maximum value of all amplitudes in this frequency band. This frequency may be 15Hz or 60Hz. The number of frequency bands divided by different units is also different. For example, GE's F-class gas turbine generally has 4 or 5 frequency bands, and Mitsubishi has 10 frequency bands. Each engine can be divided into n frequency bands. The maximum measurement amplitude of each frequency band is , subscript n is the frequency band number, for example, p1=5kPa means the maximum value measured in the first frequency band is 5kPa. Each frequency band corresponds to a dynamic pressure amplitude alarm value, and the dynamic pressure alarm value of the nth frequency band is

[0088] .

[0089] The calculation formula for the measured value of nitrogen oxide emission level is as follows:

[0090]

[0091] in, To measure the actual value of NOx concentration in the flue gas of the combustion engine, is the national limit value for NOx concentration, It is the measured percentage of O2 content in the flue gas of the combustion engine;

[0092] The calculation formula for the measured value of CO emission level is as follows:

[0093]

[0094] in To measure the actual value of CO concentration in the flue gas of the gas turbine, is the national limit value for CO concentration, is the measured percentage of O2 content in the flue gas of the combustion engine. In addition, , , and The unit is mg / m3.

[0095] Considering that there may be more parameters that can reflect the combustion state in the future, in some embodiments, the combustion state parameter also includes flame intensity. In this way, the combustion state can be reflected more accurately. Of course, in other embodiments, the combustion state parameter may also include other parameters, which are not specifically limited here.

[0096] In addition, it is worth noting that, in the present technical solution, although only one calculation formula for exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration is mentioned, in other scenarios, the calculation formulas of each parameter may change. However, no matter what calculation method or formula of each parameter changes, as long as the parameter can represent the non-uniformity of the exhaust temperature of the gas turbine, it is within the protection scope of this patent.

[0097] In some embodiments, each time after the combustion adjustment test is completed and the value of the comprehensive parameter is calculated, the method further includes:

[0098] The value of the comprehensive parameter closest to 1 in each combustion adjustment test is selected as the optimal fuel ratio value during the combustion adjustment test. Compared with before the combustion state parameter C0 is defined, in the combustion adjustment process, each test point needs to record the exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration separately, and each parameter of each test point is evaluated separately after the test is completed to find the optimal test point. This embodiment introduces a comprehensive parameter, combining four parameters (i.e., exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration) into one. Each test condition only needs to compare the comprehensive parameter and select the operating point where the value of the comprehensive parameter is close to 1. This makes the selection of the optimal value in the combustion adjustment test more objective and unified, and also provides an intuitive basis for the final fuel setting.

[0099] It should be noted that the steps shown in the above process or the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0100] This embodiment also provides a combustion state evaluation device for a gas turbine, which is used to implement the above-mentioned embodiments and preferred implementation modes, and will not be repeated hereafter. As used below, the terms "module", "unit", "subunit", etc. can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceivable.

[0101] Figure 3 is a structural block diagram of a combustion state evaluation device for a gas turbine according to an embodiment of the present application, such as Figure 3 As shown, the system includes:

[0102] An acquisition module, used for acquiring various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration;

[0103] An integration module is used to integrate various combustion state parameters into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1;

[0104] The evaluation module is used to calculate the value of the comprehensive parameter each time after the combustion adjustment test is completed, and evaluate the combustion state of the gas turbine according to the value of the comprehensive parameter. Compared with the related art, it is necessary to record each parameter separately, and evaluate each parameter of each test point separately after the test is completed, which makes the whole operation steps complicated, and as the number of test point parameters increases, the evaluation time also increases. In this embodiment, on the one hand, several combustion state parameters are integrated into one comprehensive parameter, that is, no matter how many combustion state parameters there are, the combustion state of the gas turbine can be comprehensively reflected by one comprehensive parameter, which is not only simple to operate, but also shortens the time of the whole experiment. On the other hand, compared with the previous reliance on the experience of the adjustment test personnel, different test personnel perform combustion adjustment tests, and the final adjustment results are different. The results are also different, which makes the selection of the optimal value (i.e., the optimal ratio) in the combustion adjustment test process highly subjective and lacks uniformity. In this embodiment, a comprehensive parameter can comprehensively reflect the combustion state of the gas turbine. Each test condition only needs to compare the comprehensive parameter and select the operating point where the value of the comprehensive parameter is close to 1, so that the selection of the optimal value in the combustion adjustment test process is not only objective but also unified, which solves the problem that the combustion state evaluation method of the gas turbine in the related art leads to a long evaluation time as the number of test point parameters continues to increase, and the selection of the optimal value (i.e., the optimal ratio) in the combustion adjustment test process is highly subjective and lacks uniformity.

[0105] It should be noted that the above modules can be functional modules or program modules, and can be implemented by software or hardware. For modules implemented by hardware, the above modules can be located in the same processor; or the above modules can be located in different processors in any combination.

[0106] This embodiment further provides an electronic device, including a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0107] Optionally, the electronic device may further include a transmission device and an input / output device, wherein the transmission device is connected to the processor, and the input / output device is connected to the processor.

[0108] Optionally, in this embodiment, the processor may be configured to perform the following steps through a computer program:

[0109] Step S101, obtaining various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust gas dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration;

[0110] Step S102, integrating the combustion state parameters into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1;

[0111] Step S103, each time after the combustion adjustment test is completed, the value of the comprehensive parameter is calculated, and the combustion state of the gas turbine is evaluated according to the value of the comprehensive parameter.

[0112] It should be noted that the specific examples in this embodiment can refer to the examples described in the above embodiments and optional implementation modes, and this embodiment will not be described in detail here.

[0113] In addition, in combination with the combustion state evaluation method of the gas turbine in the above embodiment, the embodiment of the present application can provide a storage medium for implementation. The storage medium stores a computer program; when the computer program is executed by the processor, any one of the combustion state evaluation methods of the gas turbine in the above embodiment is implemented.

[0114] In one embodiment, a computer device is provided, which may be a terminal. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected via a system bus. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal via a network connection. When the computer program is executed by the processor, a method for evaluating the combustion state of a gas turbine is implemented. The display screen of the computer device may be a liquid crystal display screen or an electronic ink display screen, and the input device of the computer device may be a touch layer covered on the display screen, or a key, trackball, or touchpad provided on the housing of the computer device, or an external keyboard, touchpad, or mouse, etc.

[0115] In one embodiment, Figure 4 is a schematic diagram of the internal structure of an electronic device according to an embodiment of the present application, such as Figure 4 As shown, an electronic device is provided, which may be a server, and its internal structure diagram may be as shown in Figure 4 As shown. The electronic device includes a processor, a network interface, an internal memory and a non-volatile memory connected through an internal bus, wherein the non-volatile memory stores an operating system, a computer program and a database. The processor is used to provide computing and control capabilities, the network interface is used to communicate with an external terminal through a network connection, the internal memory is used to provide an environment for the operation of the operating system and the computer program, the computer program is executed by the processor to implement a method for evaluating the combustion state of a gas turbine, and the database is used to store data.

[0116] Those skilled in the art will understand that Figure 4 The structure shown in the figure is merely a block diagram of a partial structure related to the scheme of the present application, and does not constitute a limitation on the electronic device to which the scheme of 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 a different arrangement of components.

[0117] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be implemented by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application may 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 many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0118] Those skilled in the art should understand that the various technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the various technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0119] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the attached claims.

Claims

1. A method for evaluating the combustion state of a gas turbine, characterized in that: The method comprises: Acquiring various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust gas dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration; The combustion state parameters are integrated into a comprehensive parameter, wherein the value of the comprehensive parameter ranges from 0 to 1, wherein the calculation formula for integrating the combustion state parameters into a comprehensive parameter is as follows: in, is the ratio of exhaust dispersion to allowable dispersion, is the measured value of the dynamic pressure level in the combustion chamber, is the measured value of nitrogen oxide emission level, is the measured value of CO emission level; The calculation formula of the ratio of the exhaust dispersion to the allowable dispersion is S0=S1 / TXSPL, which can reflect the health of the unit from the dispersion aspect, where S1 is the exhaust dispersion and the calculation formula of the allowable dispersion is as follows: in, To allow for dispersion, is the average temperature of the exhaust gas during the combustion engine, is the gas turbine exhaust temperature gain coefficient, is the combustion engine exhaust temperature bias constant, is the compressor exhaust temperature, is the compressor exhaust temperature gain coefficient, is the dispersion bias constant, is the first-order inertial link bias constant, is the time constant of the first-order inertia link; The calculation formula of the measured value of the combustion chamber dynamic pressure level is as follows: in, is the measured value of the dynamic pressure level in the combustion chamber, is the number of frequency bands, is the maximum measured amplitude of the ith frequency band, is the dynamic pressure alarm value of the ith frequency band, is the maximum value of the measured amplitude of the nth frequency band, is the dynamic pressure alarm value of the nth frequency band, is the maximum value of the measured amplitude of the first frequency band, is the dynamic pressure alarm value of the first frequency band; The calculation formula for the measured value of the nitrogen oxide emission level is as follows: in, To measure the actual value of NOx concentration in the flue gas of the combustion engine, is the national limit value for NOx concentration, It is the measured percentage of O2 content in the flue gas of the combustion engine; The calculation formula for the measured value of the CO emission level is as follows: in To measure the actual value of CO concentration in the flue gas of the gas turbine, is the national limit value for CO concentration, To measure the percentage of O2 content in the flue gas of the combustion engine, in addition, , , and The unit is mg / m3; Each time after the combustion adjustment test is completed, the value of the comprehensive parameter is calculated, and the combustion state of the gas turbine is evaluated based on the value of the comprehensive parameter.

2. The method according to claim 1, characterized in that: When the total number of the combustion state parameters is N, integrating the combustion state parameters into a comprehensive parameter includes: Mapping the limit values ​​of the combustion state parameters into corresponding first line segments according to a preset ratio, wherein the length of each first line segment is the same as the limit value of each combustion state parameter; Mapping the measured values ​​of each combustion state parameter into a corresponding second line segment according to a preset ratio; wherein the length of each second line segment is the same as the measured value of each combustion state parameter; When each second line segment is respectively disposed on each first line segment and each second line segment and each first line segment have the same first endpoint, a common endpoint formed by aggregating the first endpoints of each first line segment is taken as the origin O, where N is a positive integer greater than or equal to 4; When the lengths of the first line segments are the same, a regular N-gon is formed according to the origin O and the second endpoints of the first line segments, and the area of ​​the regular N-gon is calculated to obtain a first area; The origin O and the second endpoints of each second line segment form an N-gon, and the area of ​​the N-gon is calculated to obtain a second area; The first area and the second area are used to integrate various combustion state parameters into a comprehensive parameter.

3. The method according to claim 2, characterized in that: The values ​​of the calculated comprehensive parameters include: calculating a ratio of the second area to the first area; Subtracting the ratio from 1 yields the value of the comprehensive parameter.

4. The method according to claim 3, characterized in that: When N is 5, the calculation formula of the comprehensive parameter is: in, is the comprehensive parameter, is the second area, is the first area.

5. The method according to claim 1, characterized in that: The combustion state parameters also include flame intensity.

6. The method according to claim 1, characterized in that: After each combustion adjustment test is completed and the value of the comprehensive parameter is calculated, the method further includes: The value of the comprehensive parameter closest to 1 in each combustion adjustment test is selected as the optimal fuel ratio value during the combustion adjustment test.

7. A combustion state evaluation device for a gas turbine, characterized in that: The device comprises: An acquisition module, used for acquiring various combustion state parameters in the gas turbine, wherein the various combustion state parameters at least include exhaust dispersion, combustion chamber dynamic pressure level, NOx emission concentration and CO emission concentration; The integration module is used to integrate various combustion state parameters into a comprehensive parameter, wherein the value range of the comprehensive parameter is between 0 and 1, wherein the calculation formula for integrating various combustion state parameters into a comprehensive parameter is as follows: in, is the ratio of exhaust dispersion to allowable dispersion, is the measured value of the dynamic pressure level in the combustion chamber, is the measured value of nitrogen oxide emission level, is the measured value of CO emission level; The calculation formula of the ratio of the exhaust dispersion to the allowable dispersion is S0=S1 / TXSPL, which can reflect the health of the unit from the dispersion aspect, where S1 is the exhaust dispersion and the calculation formula of the allowable dispersion is as follows: in, To allow for dispersion, is the average temperature of the exhaust gas during the combustion engine, is the gas turbine exhaust temperature gain coefficient, is the combustion engine exhaust temperature bias constant, is the compressor exhaust temperature, is the compressor exhaust temperature gain coefficient, is the dispersion bias constant, is the first-order inertial link bias constant, is the time constant of the first-order inertia link; The calculation formula of the measured value of the combustion chamber dynamic pressure level is as follows: in, is the measured value of the dynamic pressure level in the combustion chamber, is the number of frequency bands, is the maximum measured amplitude of the ith frequency band, is the dynamic pressure alarm value of the ith frequency band, is the maximum value of the measured amplitude of the nth frequency band, is the dynamic pressure alarm value of the nth frequency band, is the maximum value of the measured amplitude of the first frequency band, is the dynamic pressure alarm value of the first frequency band; The calculation formula for the measured value of the nitrogen oxide emission level is as follows: in, To measure the actual value of NOx concentration in the flue gas of the combustion engine, is the national limit value for NOx concentration, It is the measured percentage of O2 content in the flue gas of the combustion engine; The calculation formula for the measured value of the CO emission level is as follows: in To measure the actual value of CO concentration in the flue gas of the gas turbine, is the national limit value for CO concentration, To measure the percentage of O2 content in the flue gas of the combustion engine, in addition, , , and The unit is mg / m3; The evaluation module is used to calculate the value of the comprehensive parameter each time after the combustion adjustment test is completed, and evaluate the combustion state of the gas turbine according to the value of the comprehensive parameter.

8. An electronic device, comprising a memory and a processor, characterized in that: A computer program is stored in the memory, and the processor is configured to run the computer program to perform the method according to any one of claims 1 to 7.

9. A storage medium, characterized in that: The storage medium stores a computer program, wherein the computer program is configured to execute the method according to any one of claims 1 to 7 when executed.

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