Method and system for determining performance of gas turbine combined cycle unit under supplementary combustion conditions

Abstract

The present application relates to a method, system and medium for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, wherein the method obtains the equivalent total heat transfer coefficient under standard conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance; obtains the equivalent total heat transfer coefficient under supplementary combustion conditions according to the preset supplementary combustion exhaust temperature; compares the equivalent total heat transfer coefficient under standard conditions with the equivalent total heat transfer coefficient under supplementary combustion conditions; when the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under supplementary combustion conditions is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition. The problem of low accuracy in determining the supplementary combustion performance of the gas turbine combined cycle unit under non-design conditions in the related art is solved.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbine combined cycle unit power generation, and in particular to a method, system and medium for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions. Background Art

[0002] As the positioning of thermal power in my country shifts from base load power to regulating power, gas turbines have become the norm for deep participation in power grid peak and frequency regulation. Waste heat generator (HRSG) is an important part of the gas-steam combined cycle. Its main working principle is to absorb the waste heat of the gas turbine exhaust by arranging a large number of heat exchange tubes to generate steam for steam turbine power generation or heating and other process steam.

[0003] Gas turbine combined cycle units are generally operated based on design conditions. In order to better achieve both heating and power generation peak load regulation, the flue gas temperature and flue gas flow are increased through supplementary combustion technology in the waste heat boiler, and the gas turbine combined cycle unit is operated under non-design conditions to improve energy efficiency. However, the existing gas turbine combined cycle unit has a low accuracy problem in determining the supplementary combustion performance under non-design conditions, which affects the operation of the gas turbine combined cycle unit. Summary of the invention

[0004] The embodiments of the present application provide a method, system and medium for determining the performance of a gas turbine combined cycle unit under supplemental combustion conditions, so as to at least solve the problem of low accuracy in determining the supplemental combustion performance of a gas turbine combined cycle unit under non-design conditions in the related art.

[0005] In a first aspect, an embodiment of the present application provides a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, the method comprising:

[0006] According to the standard performance parameters of the gas turbine combined cycle unit obtained in advance, the equivalent total heat transfer coefficient under the standard working condition is obtained;

[0007] According to the preset supplementary combustion exhaust temperature, the equivalent total heat transfer coefficient under the supplementary combustion condition is obtained;

[0008] comparing the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition;

[0009] When the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under the supplementary combustion condition is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition.

[0010] In one embodiment, the method of adjusting the approach point temperature difference and the exhaust temperature after the supplementary combustion until the comparison result meets the preset threshold value to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition includes:

[0011] Setting the temperature difference at the approach point of the reburning, obtaining the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, obtaining the initial reburning equivalent total heat transfer coefficient of the evaporator based on the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, repeatedly setting the approach point temperature difference until the comparison result meets the preset threshold value, and obtaining the equivalent total heat transfer coefficient of the evaporator under the target reburning working condition;

[0012] Set the exhaust temperature after reburning, obtain the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, obtain the equivalent total heat transfer coefficient of the economizer initial reburning based on the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, repeatedly set the exhaust temperature after reburning until the comparison result meets the preset threshold, and obtain the equivalent total heat transfer coefficient of the economizer under the target reburning condition.

[0013] In one embodiment, obtaining the equivalent total heat transfer coefficient under the supplementary combustion condition according to the preset supplementary combustion exhaust temperature includes:

[0014] Obtain the supplementary fuel flow rate according to the preset supplementary combustion exhaust temperature, combustion gas heat capacity, power turbine exhaust temperature and methane low calorific value;

[0015] When the exhaust temperature of supplementary combustion is the same as the exhaust temperature of standard working condition, the supplementary combustion steam mass flow rate is obtained according to the supplementary combustion flue gas flow rate, the heat capacity of combustion gas, the supplementary combustion exhaust temperature, the supplementary combustion exhaust temperature, the steam saturation enthalpy value and the waste heat boiler water supply enthalpy value; wherein the supplementary combustion flue gas flow rate is obtained according to the supplementary fuel flow rate and the initial flue gas flow rate;

[0016] When the temperature difference of the supplementary combustion approach point is the same as the temperature difference of the standard working condition approach point, the supplementary combustion node temperature is obtained according to the supplementary combustion steam mass flow rate, the steam saturation enthalpy value, the supplementary combustion approach point enthalpy value, the supplementary combustion flue gas flow rate, the heat capacity of the combustion gas and the supplementary combustion exhaust temperature;

[0017] When the refueling node temperature is the same as the standard operating condition node temperature and the refueling approach point temperature difference is the same as the standard operating condition approach point temperature difference, the refueling logarithmic mean temperature difference is obtained according to the refueling node temperature, and the refueling equivalent total heat transfer coefficient is obtained based on the refueling logarithmic mean temperature difference.

[0018] In one embodiment, the supplementary combustion logarithmic mean temperature difference includes the supplementary combustion logarithmic mean temperature difference of the economizer and the supplementary combustion logarithmic mean temperature difference of the evaporator, and the supplementary combustion equivalent total heat transfer coefficient includes the supplementary combustion equivalent total heat transfer coefficient of the economizer and the evaporator equivalent total heat transfer coefficient;

[0019] The step of obtaining the logarithmic mean temperature difference of supplementary combustion according to the supplementary combustion node temperature, and obtaining the supplementary combustion equivalent total heat transfer coefficient based on the logarithmic mean temperature difference of supplementary combustion includes:

[0020] Obtaining the logarithmic mean temperature difference of the evaporator according to the post-combustion node temperature, the post-combustion exhaust temperature, the steam saturation temperature and the post-combustion approach point temperature;

[0021] Obtaining the logarithmic mean temperature difference of the economizer supplementary combustion according to the supplementary combustion node temperature, the supplementary combustion exhaust temperature, the water supply temperature and the supplementary combustion approach point temperature;

[0022] Obtaining an equivalent total heat transfer coefficient of the evaporator according to the logarithmic mean temperature difference of the evaporator supplementary combustion and the total energy of the evaporator supplementary combustion side;

[0023] The equivalent total heat transfer coefficient of the economizer is obtained according to the logarithmic mean temperature difference of the supplementary combustion of the economizer and the total energy of the supplementary combustion side of the economizer.

[0024] In one embodiment, comparing the equivalent total heat transfer coefficient under the standard working condition with the equivalent total heat transfer coefficient under the supplemental combustion working condition comprises:

[0025] Comparing the equivalent total heat transfer coefficient under the standard working condition with the equivalent total heat transfer coefficient under the supplementary combustion working condition, and obtaining the difference between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition;

[0026] Compare whether the difference meets the preset threshold, and obtain the comparison result that meets the preset threshold and the comparison result that does not meet the preset threshold.

[0027] In one embodiment, after obtaining the equivalent total heat transfer coefficient under the target supplementary combustion condition, the method further includes:

[0028] An objective function is established to minimize the deviation between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplemental combustion working condition by adjusting the approach point temperature difference and the exhaust temperature after supplemental combustion.

[0029] In one embodiment, the standard performance parameters include exhaust thermal conductivity, exhaust viscosity and flue gas volume; the equivalent total heat transfer coefficient under standard operating conditions is obtained based on the pre-acquired standard performance parameters of the gas turbine combined cycle unit, including:

[0030] Obtaining an equivalent total heat transfer coefficient of the evaporator under standard working conditions according to the exhaust gas thermal conductivity, the exhaust gas viscosity and the flue gas volume;

[0031] The equivalent total heat transfer coefficient of the economizer under standard operating conditions is obtained according to the exhaust gas thermal conductivity, the exhaust gas viscosity and the flue gas volume.

[0032] In one embodiment, before obtaining the equivalent total heat transfer coefficient under standard operating conditions according to the pre-acquired standard performance parameters of the gas turbine combined cycle unit, the method further includes:

[0033] Obtaining initial operating parameters of the gas turbine combined cycle unit;

[0034] Based on the initial operating condition parameters, standard performance parameters of the gas turbine combined cycle unit are obtained.

[0035] In a second aspect, an embodiment of the present application provides a system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, the system comprising a standard equivalent total heat transfer coefficient module, a supplementary combustion equivalent total heat transfer coefficient module, a comparison module and a performance determination module, wherein:

[0036] The standard equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under standard working conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance;

[0037] The supplementary combustion equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under the supplementary combustion working condition according to the preset supplementary combustion exhaust temperature;

[0038] The comparison module is used to compare the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition;

[0039] The performance determination module is used to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold when the comparison result does not meet the preset threshold, and determine the performance of the gas turbine combined cycle unit under the supplementary combustion condition based on the equivalent total heat transfer coefficient under the target supplementary combustion condition.

[0040] In a third aspect, an embodiment of the present application provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions as described in the first aspect above is implemented.

[0041] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions as described in the first aspect above.

[0042] The performance determination method, system and medium of a gas turbine combined cycle unit under supplementary combustion conditions provided in the embodiments of the present application have at least the following technical effects.

[0043] By obtaining the standard performance parameters of the gas turbine combined cycle unit in advance, the equivalent total heat transfer coefficient under the standard working condition is obtained; according to the preset supplementary combustion exhaust temperature, the equivalent total heat transfer coefficient under the supplementary combustion condition is obtained; the equivalent total heat transfer coefficient under the standard working condition is compared with the equivalent total heat transfer coefficient under the supplementary combustion condition; when the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under the supplementary combustion condition is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition. In the present application, the approach point temperature difference and the exhaust temperature after supplementary combustion are adjusted so that the difference between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion condition meets the preset threshold, and then the performance of the gas turbine combined cycle unit is determined by the supplementary combustion equivalent total heat transfer coefficient. The method achieves both heating and power generation peak regulation of the gas turbine combined cycle unit under supplementary combustion conditions, improves energy utilization efficiency, and solves the problem of low accuracy in determining the supplementary combustion performance of the gas turbine combined cycle unit under non-design conditions in related technologies.

[0044] Details of one or more embodiments of the present application are set forth in the following drawings and description to make other features, objects, and advantages of the present application more readily apparent. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] 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:

[0046] Figure 1 It is a flow chart for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions;

[0047] Figure 2 is a flowchart of step S102 according to an exemplary embodiment;

[0048] Figure 3 is a flowchart of step S104 according to an exemplary embodiment;

[0049] Figure 4 is a structural block diagram of a system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions according to an exemplary embodiment;

[0050] Figure 5 It is a structural block diagram of an electronic device according to an exemplary embodiment. DETAILED DESCRIPTION

[0051] 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 the field without making creative work are within the scope of protection of the present application.

[0052] Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. In addition, it can also be understood that although the efforts made in this development process may be complicated and lengthy, for ordinary technicians in this field related to the content disclosed in this application, some changes in design, manufacturing or production based on the technical content disclosed in this application are just conventional technical means, and should not be understood as insufficient content disclosed in this application.

[0053] 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.

[0054] 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 refers to two or more. "And / or" describes the association relationship of associated objects, indicating that there may 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 character " / " generally indicates that the objects before and after are in an "or" relationship. The terms "first", "second", "third", etc. involved in this application are only used to distinguish similar objects and do not represent a specific ordering of the objects.

[0055] In a first aspect, an embodiment of the present application provides a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions. Figure 1 It is a flow chart for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions. Figure 1 As shown, a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions includes:

[0056] Step S101: Obtain an equivalent total heat transfer coefficient under standard operating conditions based on pre-acquired standard performance parameters of a gas turbine combined cycle unit.

[0057] Step S102: Obtain the equivalent total heat transfer coefficient under the supplementary combustion condition according to the preset supplementary combustion exhaust temperature.

[0058] Step S103, comparing the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition.

[0059] Step S104: When the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under the supplementary combustion condition is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition.

[0060] In summary, the embodiment of the present application provides a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, by obtaining the equivalent total heat transfer coefficient under standard conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance; obtaining the equivalent total heat transfer coefficient under supplementary combustion conditions according to the preset supplementary combustion exhaust temperature; comparing the equivalent total heat transfer coefficient under standard conditions with the equivalent total heat transfer coefficient under supplementary combustion conditions; when the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion conditions is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under supplementary combustion conditions is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion conditions. In the present application, the approach point temperature difference and the exhaust temperature after supplementary combustion are adjusted so that the difference between the equivalent total heat transfer coefficient under the standard conditions and the equivalent total heat transfer coefficient under the supplementary combustion conditions meets the preset threshold, and then the performance of the gas turbine combined cycle unit is determined by the supplementary combustion equivalent total heat transfer coefficient. The method achieves both heating and power generation peak regulation of the gas turbine combined cycle unit under supplementary combustion conditions, improves energy utilization efficiency, and solves the problem of low accuracy in determining the supplementary combustion performance of the gas turbine combined cycle unit under non-design conditions in related technologies.

[0061] In one embodiment, before obtaining the equivalent total heat transfer coefficient under standard conditions in step S101 based on the standard performance parameters of the gas turbine combined cycle unit obtained in advance, the method for determining the performance of the gas turbine combined cycle unit under supplementary combustion conditions further includes:

[0062] Obtain the initial operating parameters of the gas turbine combined cycle unit.

[0063] Based on the initial operating parameters, the standard performance parameters of the gas turbine combined cycle unit are obtained.

[0064] Optionally, according to the operating condition of the gas turbine combined cycle unit, the initial operating condition parameters of the gas turbine combined cycle unit are collected. The initial operating condition parameters of the gas turbine combined cycle unit are shown in Table 1.

[0065] Table 1. Initial operating parameters of gas turbine combined cycle unit

[0066]

[0067] According to the initial operating parameters in Table 1, the standard performance parameters of the gas turbine combined cycle unit are obtained based on the thermodynamic equation, mass balance and energy balance. Table 2 is a table of standard performance parameters of the gas turbine combined cycle unit. It should be noted that the calculation formulas for each performance parameter are conventional formulas and are not described here.

[0068] Table 2. Calculation variables for design performance calculation of gas turbine combined cycle unit

[0069]

[0070] In this embodiment, the main initial operating parameters of the gas turbine combined cycle unit (such as turbine inlet temperature, pressure ratio, combustion chamber pressure, cycle efficiency, etc.) are obtained to clarify and initialize, providing necessary input data for subsequent analysis. Based on the obtained initial operating parameters, the theoretical performance indicators of the gas turbine combined cycle unit, such as electric power output, thermal efficiency, fuel consumption rate, etc., are calculated through thermodynamic equations, mass balance and energy balance. This provides a basis for the subsequent establishment of the equivalent total heat transfer coefficient under standard conditions.

[0071] In one embodiment, step S101, based on the standard performance parameters of the gas turbine combined cycle unit acquired in advance, obtain the equivalent total heat transfer coefficient under standard working conditions. Specifically includes:

[0072] According to the exhaust gas thermal conductivity, exhaust gas viscosity and flue gas volume, the equivalent total heat transfer coefficient of the evaporator under standard working conditions is obtained;

[0073] According to the exhaust gas thermal conductivity, exhaust gas viscosity and flue gas volume, the equivalent total heat transfer coefficient of the economizer under standard operating conditions is obtained.

[0074] Optionally, based on an estimate of the air-side thermal conductivity,

[0075] By formula Solve the equivalent total heat transfer coefficient of the evaporator under standard conditions;

[0076] By formula To solve the equivalent total heat transfer coefficient of the economizer under standard operating conditions, it should be noted that the standard operating conditions are also the design conditions, and the standard operating conditions will be used in the following text.

[0077] in, is the exhaust thermal conductivity, is the exhaust viscosity, For the amount of supplementary combustion flue gas, is the heat capacity of the combustion gas, is the standard flue gas volume. Based on a given exhaust gas temperature, The value can be obtained based on the gas property calculator, The value can be obtained based on the gas viscosity calculator. It is worth noting that in the total heat transfer coefficient of this embodiment, an exponent of 0.6 is applied to the gas flow rate. and In software development or actual calculations, an exponent of 0.8 can also be used. and .

[0078] By analyzing the operating parameters (such as temperature, pressure, flow rate, etc.) of the gas turbine combined cycle unit under standard conditions, the equivalent total heat transfer coefficient under standard conditions is calculated. The equivalent total heat transfer coefficient is the core indicator for measuring heat exchange efficiency, which is related to energy conversion efficiency and overall system performance. The equivalent total heat transfer coefficient under standard conditions provides a clear reference standard for subsequent performance comparisons, making it easier to identify performance parameters that deviate from standard conditions.

[0079] Optionally, Figure 2 is a flowchart of step S102 according to an exemplary embodiment. Figure 2 As shown, in one embodiment, step S102, according to the preset supplementary combustion exhaust temperature, obtains the equivalent total heat transfer coefficient under the supplementary combustion condition. Specifically, it includes the following steps:

[0080] Step S1021, obtaining the supplementary fuel flow rate according to the preset supplementary combustion exhaust temperature, the heat capacity of the combustion gas, the power turbine exhaust temperature and the low calorific value of methane.

[0081] Optionally, supplementary firing can increase the exhaust temperature of the waste heat boiler from (Power turbine exhaust temperature) increases to (Preset afterburning exhaust gas temperature). For the variable initial quantity, solve for the supplementary fuel flow rate

[0082] In the formula, is the heat capacity of the combustion gas, is the heat capacity of the combustion gas, To preset the afterburning exhaust gas temperature, is the power turbine exhaust temperature, Low calorific value of natural gas (methane) (preferably 77 o F, 1atm), is the temperature of the fuel at LHV (preferably 77°F).

[0083] Step S1022, when the supplementary combustion exhaust temperature is the same as the standard operating exhaust temperature, the supplementary combustion steam mass flow rate is obtained according to the supplementary combustion flue gas flow rate, the heat capacity of the combustion gas, the supplementary combustion exhaust temperature, the supplementary combustion exhaust temperature, the steam saturation enthalpy value and the waste heat boiler water supply enthalpy value; wherein the supplementary combustion flue gas flow rate is obtained according to the supplementary fuel flow rate and the initial flue gas flow rate.

[0084] Optionally, at the exhaust temperature When the exhaust gas temperature is the same as the standard working condition , solve for the steam mass flow rate in the supplementary combustion

[0085] In the formula, is the supplementary combustion flue gas flow rate, is the heat capacity of the combustion gas, To preset the afterburning exhaust gas temperature, is the exhaust temperature of supplementary combustion, is the steam saturation enthalpy, is the enthalpy of water supply to the waste heat boiler. It is worth noting that , is the heat capacity of the combustion gas, To supplement fuel flow.

[0086] Step S1023, when the temperature difference of the supplementary combustion approach point is the same as the temperature difference of the standard operating condition approach point, the supplementary combustion node temperature is obtained according to the supplementary combustion steam mass flow rate, the steam saturation enthalpy value, the supplementary combustion approach point enthalpy value, the supplementary combustion flue gas flow rate, the combustion gas heat capacity and the supplementary combustion exhaust temperature.

[0087] Alternatively, it is assumed that the approach point temperature difference under supplementary combustion conditions is the same as the design value ( ), and then the approach point enthalpy value under the supplementary combustion condition is the same as the design value ( ), determine the new gas side node temperature after supplementary combustion The node temperature formula is as follows:

[0088]

[0089] In the formula, Supplementary combustion steam mass flow rate, is the steam saturation enthalpy, Enthalpy of approach point of post-combustion, is the supplementary combustion flue gas flow rate, is the heat capacity of the combustion gas, It is the preset post-combustion exhaust gas temperature.

[0090] Step S1024, when the supplementary combustion node temperature is the same as the standard operating condition node temperature and the supplementary combustion approach point temperature difference is the same as the standard operating condition approach point temperature difference, obtain the supplementary combustion logarithmic mean temperature difference according to the supplementary combustion node temperature, and obtain the supplementary combustion equivalent total heat transfer coefficient based on the supplementary combustion logarithmic mean temperature difference.

[0091] Optionally, at present, when a gas turbine combined cycle unit needs to perform deep peak regulation, its operating conditions (supplementary combustion conditions) are far away from the standard conditions on which the performance curve provided by the manufacturer is based. At this time, the efficiency, power output, etc. estimated according to the manufacturer's performance curve may no longer be accurate because the actual operating conditions (such as intake temperature, pressure, load, etc.) are significantly different from the design conditions. Inapplicability may lead to low operating efficiency, reduced economy, and even affect the safe and stable operation of the unit. By calculating the equivalent total heat transfer coefficient of supplementary combustion for the gas turbine combined cycle unit under supplementary combustion conditions in step S102, the adaptability problem of the manufacturer's performance curve under deep peak regulation is solved.

[0092] In one embodiment, the supplementary combustion logarithmic mean temperature difference includes the supplementary combustion logarithmic mean temperature difference of the economizer and the supplementary combustion logarithmic mean temperature difference of the evaporator, and the supplementary combustion equivalent total heat transfer coefficient includes the supplementary combustion equivalent total heat transfer coefficient of the economizer and the evaporator equivalent total heat transfer coefficient;

[0093] According to the supplementary combustion node temperature, the supplementary combustion logarithmic mean temperature difference is obtained. Based on the supplementary combustion logarithmic mean temperature difference, the supplementary combustion equivalent total heat transfer coefficient is obtained, including:

[0094] The logarithmic mean temperature difference of the evaporator after-burning is obtained according to the after-burning node temperature, after-burning exhaust temperature, steam saturation temperature and after-burning approach point temperature.

[0095] Optionally, the evaporator supplementary combustion logarithmic mean temperature difference formula is as follows:

[0096]

[0097] In the formula, is the afterburning exhaust gas temperature, is the steam saturation temperature, Afterburning node temperature, It is the temperature approaching the point of afterburning.

[0098] The logarithmic average temperature difference of the economizer supplementary combustion is obtained according to the supplementary combustion node temperature, supplementary combustion exhaust temperature, water supply temperature and supplementary combustion approach point temperature.

[0099] Optionally, the logarithmic mean temperature difference formula for economizer supplementary combustion is as follows:

[0100]

[0101] In the formula, Afterburning node temperature, is the temperature approaching the point of afterburning, is the exhaust temperature of supplementary combustion, is the supply water (condensation return water) temperature.

[0102] The equivalent total heat transfer coefficient of the evaporator is obtained based on the logarithmic mean temperature difference of the evaporator supplementary combustion and the total energy of the evaporator supplementary combustion side.

[0103] Alternatively, the formula for the equivalent overall heat transfer coefficient of the evaporator is as follows:

[0104]

[0105] In the formula, is the logarithmic mean temperature difference of the evaporator after combustion, is the logarithmic mean temperature difference of the evaporator after combustion.

[0106] The equivalent total heat transfer coefficient of the economizer is obtained based on the logarithmic mean temperature difference of the economizer supplementary combustion and the total energy of the economizer supplementary combustion side.

[0107] Alternatively, the formula for the equivalent overall heat transfer coefficient of the economizer is as follows:

[0108]

[0109] In the formula, is the logarithmic mean temperature difference of economizer supplementary combustion, is the logarithmic mean temperature difference of economizer supplementary combustion.

[0110] At present, when the total energy balance method is used to predict the performance of non-design conditions (such as supplementary combustion conditions), in order to simplify the calculation, it is often necessary to make assumptions about some parameters that are difficult to directly measure or calculate (such as the heat transfer coefficient of the heat exchanger, flow resistance loss, etc.). Although these assumptions are convenient for calculation, if there are too many or inaccurate assumptions, they may cause a large deviation between the calculation results and the actual situation, affecting the accurate evaluation and optimization of system performance. By refining the calculation and analysis of the logarithmic mean temperature difference and the equivalent total heat transfer coefficient under supplementary combustion conditions, the accuracy of the calculation performance is improved, and the problem of too many assumed values ​​in the total energy balance method is solved.

[0111] In one embodiment, step S103, comparing the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition, specifically includes the following steps:

[0112] Compare the equivalent total heat transfer coefficient under the standard working condition with the equivalent total heat transfer coefficient under the supplementary combustion working condition to obtain the difference between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition;

[0113] Compare whether the difference meets the preset threshold, and obtain the comparison result that meets the preset threshold and the comparison result that does not meet the preset threshold.

[0114] Optionally, the equivalent total heat transfer coefficient of the economizer under the standard working condition is compared with the equivalent total heat transfer coefficient of the economizer under the supplementary combustion working condition to obtain the difference between the equivalent total heat transfer coefficient of the economizer under the standard working condition and the equivalent total heat transfer coefficient of the economizer under the supplementary combustion working condition. Compare whether the difference meets the preset threshold, where the preset threshold is 0~1. If the difference is within the range between 0~1, a comparison result that meets the preset threshold is obtained. If the difference is not within the range between 0~1, a comparison result that does not meet the preset threshold is obtained.

[0115] Compare the equivalent total heat transfer coefficient of the evaporator under the standard working condition with the equivalent total heat transfer coefficient of the evaporator under the supplementary combustion working condition, and obtain the difference between the equivalent total heat transfer coefficient of the evaporator under the standard working condition and the equivalent total heat transfer coefficient of the evaporator under the supplementary combustion working condition. Compare whether the difference meets the preset threshold, where the preset threshold is 0~1. If the difference is within the range of 0~1, a comparison result that meets the preset threshold is obtained. If the difference is not within the range of 0~1, a comparison result that does not meet the preset threshold is obtained.

[0116] By comparing the equivalent total heat transfer coefficient under standard conditions and supplementary combustion conditions, the impact of supplementary combustion operation on the heat exchange efficiency of the system can be intuitively evaluated. This is conducive to adjusting the parameters of the gas turbine combined cycle unit under supplementary combustion conditions, and then determining the performance of the gas turbine combined cycle unit under supplementary combustion conditions.

[0117] Figure 3 is a flowchart of step S104 according to an exemplary embodiment. Figure 3 As shown, in one embodiment, step S104, when the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under the supplementary combustion condition is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition. Specifically, the following steps are included:

[0118] Step S1041, set the temperature difference of the re-combustion approach point, obtain the logarithmic mean temperature difference of the evaporator re-combustion and the total energy measured by the evaporator re-combustion gas, obtain the initial re-combustion equivalent total heat transfer coefficient of the evaporator based on the logarithmic mean temperature difference of the evaporator re-combustion and the total energy measured by the evaporator re-combustion gas, repeatedly set the temperature difference of the approach point until the comparison result meets the preset threshold value, and obtain the equivalent total heat transfer coefficient of the evaporator under the target re-combustion working condition.

[0119] Optionally, when the comparison result does not meet the preset threshold, the re-combustion approach point temperature difference is set, wherein the re-combustion approach point temperature difference = steam saturation temperature - re-combustion approach point temperature. According to the logarithmic mean temperature difference of the evaporator re-combustion and the total energy measured by the evaporator re-combustion, the evaporator initial re-combustion equivalent total heat transfer coefficient is obtained. (It is worth noting that the evaporator re-combustion equivalent total heat transfer coefficient is obtained according to the logarithmic mean temperature difference of the evaporator re-combustion and the total energy measured by the evaporator re-combustion, which has been recorded in the above embodiment and will not be repeated here). After obtaining the evaporator initial re-combustion equivalent total heat transfer coefficient, the evaporator initial re-combustion equivalent total heat transfer coefficient is used as the economizer equivalent total heat transfer coefficient under the re-combustion condition in step S103, and a comparison operation is performed to obtain a comparison result. According to the comparison result, the approach point temperature difference is repeatedly set until the comparison result meets the preset threshold, and the evaporator equivalent total heat transfer coefficient under the target re-combustion condition is obtained.

[0120] Step S1042, set the exhaust temperature after re-combustion, obtain the logarithmic mean temperature difference of the economizer re-combustion and the total energy measured by the economizer re-combustion gas, obtain the equivalent total heat transfer coefficient of the economizer initial re-combustion based on the logarithmic mean temperature difference of the economizer re-combustion and the total energy measured by the economizer re-combustion gas, repeatedly set the exhaust temperature after re-combustion until the comparison result meets the preset threshold, and obtain the equivalent total heat transfer coefficient of the economizer under the target re-combustion working condition.

[0121] Optionally, when the comparison result does not meet the preset threshold, the exhaust temperature after the supplementary combustion is set, and the initial supplementary combustion equivalent total heat transfer coefficient of the economizer is obtained according to the logarithmic mean temperature difference of the economizer supplementary combustion and the total energy measured by the economizer supplementary combustion. (It is worth noting that the equivalent total heat transfer coefficient of the economizer supplementary combustion is obtained according to the logarithmic mean temperature difference of the economizer supplementary combustion and the total energy measured by the economizer supplementary combustion, which has been recorded in the above embodiment and will not be repeated here). After obtaining the equivalent total heat transfer coefficient of the initial supplementary combustion of the economizer, the equivalent total heat transfer coefficient of the initial supplementary combustion of the economizer is used as the equivalent total heat transfer coefficient of the economizer under the supplementary combustion condition in step S103, and a comparison operation is performed to obtain a comparison result. According to the comparison result, the approach point temperature difference is repeatedly set until the comparison result meets the preset threshold, and the equivalent total heat transfer coefficient of the economizer under the target supplementary combustion condition is obtained.

[0122] By continuously adjusting the temperature difference of the supplementary combustion approach point (for the evaporator) and the exhaust temperature after supplementary combustion (for the economizer), the equivalent total heat transfer coefficient of the evaporator and economizer under the target supplementary combustion working condition can be accurately determined. The heat exchange process can be more accurately controlled and optimized, especially under dynamic and complex working conditions such as supplementary combustion, which helps to improve energy utilization efficiency, reduce energy consumption, and ensure stable operation of the system.

[0123] In one embodiment, after obtaining the equivalent total heat transfer coefficient under the target supplementary combustion condition, the method for determining the performance of the gas turbine combined cycle unit further includes:

[0124] The objective function is established to minimize the deviation between the equivalent total heat transfer coefficient under standard conditions and the equivalent total heat transfer coefficient under supplementary combustion conditions by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion.

[0125] Optionally, after obtaining the equivalent total heat transfer coefficient under the target post-combustion condition, the objective function is solved by reselecting a new post-combustion approach point temperature difference and post-combustion exhaust temperature. , where the objective function is used to correct the deviation caused by the amount of supplementary combustion steam due to the change in the supplementary combustion exhaust temperature.

[0126] By minimizing the difference in the equivalent total heat transfer coefficient between standard and supplementary combustion conditions, the unit is ensured to maintain high heat exchange efficiency and stability in different operating modes. This helps to eliminate performance fluctuations caused by operating condition conversion, achieve smooth transition of unit operation and balance of overall performance. Adjusting the approach point temperature difference and supplementary combustion exhaust temperature as independent variables can more precisely match the actual operating conditions, especially in complex and changeable actual operating conditions, and can more flexibly respond to and optimize system performance.

[0127] In one embodiment, based on the calculated waste heat boiler flue gas temperature (supplementary combustion exhaust gas temperature , afterburning node temperature and exhaust temperature ) to obtain gas physical properties (heat capacity , Viscosity and thermal conductivity ) Calculate the physical properties of the average evaporator for post-combustion ( and The arithmetic mean of the parameters) and the physical properties of the supplementary combustion average economizer ( and The arithmetic mean of the parameters), recalculated and , iterate step S104 until the waste heat boiler temperature converges.

[0128] Optionally, by and The average value of the parameters, and and The physical properties of the evaporator and economizer are calculated based on the average value of the parameters, and the impact on the performance of the equipment is evaluated, which not only takes into account the diversity of actual operating conditions, but also simplifies the calculation process. and , ensuring that as the physical properties are updated, the relevant performance parameters (such as the equivalent total heat transfer coefficient) can be adjusted in time and tend to more accurate values. Iterate step S104 until the waste heat boiler temperature converges. This means that the optimal performance under the current operating conditions has been found.

[0129] In summary, the embodiment of the present application provides a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, by obtaining the equivalent total heat transfer coefficient under standard conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance; obtaining the equivalent total heat transfer coefficient under supplementary combustion conditions according to the preset supplementary combustion exhaust temperature; comparing the equivalent total heat transfer coefficient under standard conditions with the equivalent total heat transfer coefficient under supplementary combustion conditions; when the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion conditions is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under supplementary combustion conditions is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion conditions. In the present application, the approach point temperature difference and the exhaust temperature after supplementary combustion are adjusted so that the difference between the equivalent total heat transfer coefficient under the standard conditions and the equivalent total heat transfer coefficient under the supplementary combustion conditions meets the preset threshold, and then the performance of the gas turbine combined cycle unit is determined by the supplementary combustion equivalent total heat transfer coefficient. The method achieves both heating and power generation peak regulation of the gas turbine combined cycle unit under supplementary combustion conditions, improves energy utilization efficiency, and solves the problem of low accuracy in determining the supplementary combustion performance of the gas turbine combined cycle unit under non-design conditions in related technologies.

[0130] Practical application examples:

[0131] Step 1: Obtain the initial operating parameters of the gas turbine combined cycle unit.

[0132] The initial operating parameters of the gas turbine combined cycle unit are obtained. The design and benchmark of the performance are based on the standard operating conditions specified by the International Standard (ISO), that is, the steam supply temperature is 59℉ (15℃), the pressure is 14.7 psia (1.013 bar), and the relative humidity is 60%. Table 3 is an example table of initial operating parameters of the gas turbine combined cycle unit, as shown in Table 3:

[0133] Table 3 Example of initial operating parameters of gas turbine combined cycle unit

[0134]

[0135] Step 2: Based on the initial operating parameters, obtain the standard performance parameters of the gas turbine combined cycle unit.

[0136] Table 4 is an example table of initial operating parameters of a gas turbine combined cycle unit, as shown in Table 4:

[0137] Table 4 Example of standard performance parameters of gas turbine combined cycle units

[0138]

[0139] Among them, the parameters of items No. 29-31 can be obtained by calling a third-party water vapor thermodynamic property calculation table, which will not be described in detail here.

[0140] Step 3: According to the preset supplementary combustion exhaust temperature, obtain the performance parameters under the supplementary combustion condition.

[0141] Under supplementary combustion conditions, the exhaust temperature of the waste heat boiler is reduced from Increase to (Preset afterburning exhaust temperature), set , calculate and determine the supplementary combustion flue gas flow rate Table 5 is an example table of performance parameters under standard working conditions and performance parameters under supplementary combustion working conditions, as shown in Table 5:

[0142] Table 5 Example of performance parameters under standard working conditions and performance parameters under supplementary combustion conditions

[0143]

[0144] Step 4: Based on the standard performance parameters of the gas turbine combined cycle unit obtained in advance, obtain the equivalent total heat transfer coefficient under standard operating conditions.

[0145] Solving the equivalent total heat transfer coefficient of the standard working condition, we get: Btu / (s·R), Btu / (s·R).

[0146] Step 5: Obtain the equivalent total heat transfer coefficient of the evaporator under supplementary combustion conditions.

[0147] Adjust the approach point temperature difference until the comparison result of the equivalent total heat transfer coefficient of the supplementary-fired evaporator and the equivalent total heat transfer coefficient of the standard-condition evaporator meets the preset threshold. Table 6 is an example table of calculation of the supplementary-fired evaporator. It can be implemented using conventional nonlinear GRG or single linear programming methods. Define the approach point temperature difference is the independent variable, and the absolute deviation between the equivalent total heat transfer coefficient of the supplementary-fired evaporator and the equivalent total heat transfer coefficient of the evaporator under standard conditions is the target value.

[0148] Table 6 Calculation example of supplementary combustion evaporator

[0149]

[0150] Step 6: Obtain the equivalent total heat transfer coefficient of the economizer under supplementary combustion conditions.

[0151] Adjust the supplementary combustion exhaust temperature until the comparison result of the equivalent total heat transfer coefficient of the supplementary combustion economizer and the equivalent total heat transfer coefficient of the standard operating economizer meets the preset threshold. Table 7 is a calculation example table of the supplementary combustion economizer, and the detailed calculation results are shown in Table 7. Since the comparison result of the equivalent total heat transfer coefficient of the supplementary combustion economizer and the equivalent total heat transfer coefficient of the standard operating economizer meets the preset threshold, it can be implemented using conventional nonlinear GRG or single linear programming methods, defining the adjustment of the supplementary combustion exhaust temperature as the independent variable, and the absolute deviation of the equivalent total heat transfer coefficient of the supplementary combustion economizer and the equivalent total heat transfer coefficient of the standard operating economizer as the target value.

[0152] Table 7 Calculation example of supplementary combustion economizer

[0153]

[0154] Step 7: Establish an objective function to minimize the deviation between the equivalent total heat transfer coefficient under standard conditions and the equivalent total heat transfer coefficient under supplementary combustion conditions.

[0155] By reselecting the new post-combustion approach point temperature difference) and the post-combustion exhaust temperature, the objective function is solved. , where the objective function is used to correct the deviation caused by the supplementary combustion steam quantity due to the change in the supplementary combustion exhaust temperature. Table 8 is an example table of objective function calculation, and the detailed calculation results are shown in Table 8.

[0156] Table 8 Example of optimization calculation for waste heat boiler

[0157]

[0158] Through the above practical application examples, it can be explained that by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion, the difference between the equivalent total heat transfer coefficient under standard conditions and the equivalent total heat transfer coefficient under supplementary combustion conditions meets the preset threshold, and then the performance of the gas turbine combined cycle unit is determined by the supplementary combustion equivalent total heat transfer coefficient. The gas turbine combined cycle unit under supplementary combustion conditions achieves both heating and power generation peak regulation, improves energy utilization efficiency, and solves the problem of low accuracy in determining the supplementary combustion performance of the gas turbine combined cycle unit under non-design conditions in related technologies.

[0159] In a second aspect, an embodiment of the present application provides a system for determining the performance of a gas turbine combined cycle unit under supplemental combustion conditions. Figure 4 FIG. 1 is a block diagram of a system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions according to an exemplary embodiment. Figure 4 As shown, the system includes a standard equivalent total heat transfer coefficient module, a supplementary combustion equivalent total heat transfer coefficient module, a comparison module and a performance determination module, wherein:

[0160] A standard equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under standard working conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance;

[0161] The supplementary combustion equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under the supplementary combustion working condition according to the preset supplementary combustion exhaust temperature;

[0162] A comparison module is used to compare the equivalent total heat transfer coefficient under standard conditions and the equivalent total heat transfer coefficient under supplementary combustion conditions;

[0163] The performance determination module is used to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold when the comparison result does not meet the preset threshold, and determine the performance of the gas turbine combined cycle unit under the supplementary combustion condition based on the equivalent total heat transfer coefficient under the target supplementary combustion condition.

[0164] In summary, the embodiment of the present application provides a system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, which realizes both heating and peak load regulation of a gas turbine combined cycle unit under supplementary combustion conditions, improves energy utilization efficiency, and solves the problem of low accuracy in determining the supplementary combustion performance of a gas turbine combined cycle unit under non-design conditions in the related art through the mutual cooperation of a standard equivalent total heat transfer coefficient module, a supplementary combustion equivalent total heat transfer coefficient module, a comparison module, and a performance determination module.

[0165] It should be noted that the system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions provided in this embodiment is used to implement the above-mentioned implementation mode, and the descriptions that have been made will not be repeated. As used above, the terms "module", "unit", "subunit" and the like can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the above embodiments is preferably implemented in software, the implementation in hardware, or a combination of software and hardware, is also possible and conceivable.

[0166] In a third aspect, an embodiment of the present application provides an electronic device, Figure 5 FIG. 1 is a block diagram of an electronic device according to an exemplary embodiment. Figure 5 As shown, the electronic device may include a processor 51 and a memory 52 storing computer program instructions.

[0167] Specifically, the processor 51 may include a central processing unit (CPU), or an application specific integrated circuit (ASIC), or may be configured to implement one or more integrated circuits of the embodiments of the present application.

[0168] Among them, the memory 52 may include a large-capacity memory for data or instructions. By way of example and not limitation, the memory 52 may include a hard disk drive (HDD), a floppy disk drive, a solid-state drive (SSD), a flash memory, an optical disk, a magneto-optical disk, a magnetic tape, or a universal serial bus (USB) drive, or a combination of two or more of these. Where appropriate, the memory 52 may include a removable or non-removable (or fixed) medium. Where appropriate, the memory 52 may be inside or outside the data processing device. In a specific embodiment, the memory 52 is a non-volatile memory. In a specific embodiment, the memory 52 includes a read-only memory (ROM) and a random access memory (RAM). Where appropriate, the ROM may be a mask-programmed ROM, a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), an electrically alterable ROM (EAROM) or a flash memory (FLASH), or a combination of two or more of these. Under appropriate circumstances, the RAM can be a static random access memory (SRAM) or a dynamic random access memory (DRAM), wherein the DRAM can be a fast page mode dynamic random access memory (FPMDRAM), an extended data output dynamic random access memory (EDODRAM), a synchronous dynamic random access memory (SDRAM), etc.

[0169] The memory 52 may be used to store or cache various data files required for processing and / or communication, as well as possible computer program instructions executed by the processor 51 .

[0170] The processor 51 reads and executes the computer program instructions stored in the memory 52 to implement the performance determination method of the gas turbine combined cycle unit under any one of the supplementary combustion conditions in the above embodiments.

[0171] In one embodiment, a device for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions may further include a communication interface 53 and a bus 50. Figure 5 As shown, the processor 51, the memory 52, and the communication interface 53 are connected via a bus 50 and communicate with each other.

[0172] The communication interface 53 is used to implement communication between the modules, devices, units and / or equipment in the embodiment of the present application. The communication port 53 can also implement data communication with other components such as: external devices, image / data acquisition equipment, databases, external storage, and image / data processing workstations.

[0173] The bus 50 includes hardware, software or both, and couples the components of a device for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions to each other. The bus 50 includes but is not limited to at least one of the following: a data bus (DataBus), an address bus (Address Bus), a control bus (Control Bus), an expansion bus (Expansion Bus), and a local bus (Local Bus). By way of example and not limitation, bus 50 may include Accelerated Graphics Port (AGP) or other graphics bus, Extended Industry Standard Architecture (EISA) bus, Front Side Bus (FSB), Hyper Transport (HT) interconnect, Industry Standard Architecture (ISA) bus, InfiniBand interconnect, Low Pin Count (LPC) bus, memory bus, Micro Channel Architecture (MCA) bus, Peripheral Component Interconnect (PCI) bus, PCI-Express (PCI-X) bus, Serial Advanced Technology Attachment (SATA) bus, Video Electronics Standards Association Local Bus (VLB) bus, or other suitable bus or a combination of two or more of the above. Where appropriate, bus 50 may include one or more buses. Although embodiments of the present application describe and illustrate a particular bus, the present application contemplates any suitable bus or interconnect.

[0174] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a program stored thereon, which, when executed by a processor, implements a method for determining the performance of a gas turbine combined cycle unit under supplemental combustion conditions provided in the first aspect.

[0175] The readable storage medium may include but is not limited to: a portable disk, a hard disk, a random access memory, a read-only memory, an erasable programmable read-only memory, an optical storage device, a magnetic storage device or any suitable combination of the above.

[0176] In a possible implementation, the present invention can also be implemented in the form of a program product, which includes a program code. When the program product is run on a terminal device, the program code is used to enable the terminal device to execute the steps of a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions provided in the first aspect.

[0177] Among them, the program code for executing the present invention can be written in any combination of one or more programming languages, and the program code can be executed completely on the user device, partially on the user device, as an independent software package, partially on the user device and partially on a remote device, or completely on the remote device.

[0178] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above 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.

[0179] The above 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 determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, characterized in that: The method comprises: According to the standard performance parameters of the gas turbine combined cycle unit obtained in advance, the equivalent total heat transfer coefficient under the standard working condition is obtained; According to the preset supplementary combustion exhaust temperature, the equivalent total heat transfer coefficient under the supplementary combustion condition is obtained; comparing the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition; When the comparison result does not meet the preset threshold, the equivalent total heat transfer coefficient under the target supplementary combustion condition is obtained by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold, and the performance of the gas turbine combined cycle unit under the supplementary combustion condition is determined based on the equivalent total heat transfer coefficient under the target supplementary combustion condition; The method of adjusting the approach point temperature difference and the exhaust temperature after the supplementary combustion until the comparison result meets the preset threshold value to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition includes: Setting the temperature difference at the approach point of the reburning, obtaining the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, obtaining the initial reburning equivalent total heat transfer coefficient of the evaporator based on the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, repeatedly setting the approach point temperature difference until the comparison result meets the preset threshold value, and obtaining the equivalent total heat transfer coefficient of the evaporator under the target reburning working condition; Set the exhaust temperature after reburning, obtain the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, obtain the equivalent total heat transfer coefficient of the economizer initial reburning based on the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, repeatedly set the exhaust temperature after reburning until the comparison result meets the preset threshold, and obtain the equivalent total heat transfer coefficient of the economizer under the target reburning condition.

2. The method according to claim 1, characterized in that The obtaining of the equivalent total heat transfer coefficient under the supplementary combustion condition according to the preset supplementary combustion exhaust temperature includes: Obtain the supplementary fuel flow rate according to the preset supplementary combustion exhaust temperature, combustion gas heat capacity, power turbine exhaust temperature and methane low calorific value; When the exhaust temperature of supplementary combustion is the same as the exhaust temperature of standard working condition, the supplementary combustion steam mass flow rate is obtained according to the supplementary combustion flue gas flow rate, the heat capacity of combustion gas, the supplementary combustion exhaust temperature, the supplementary combustion exhaust temperature, the steam saturation enthalpy value and the waste heat boiler water supply enthalpy value; wherein the supplementary combustion flue gas flow rate is obtained according to the supplementary fuel flow rate and the initial flue gas flow rate; When the temperature difference of the supplementary combustion approach point is the same as the temperature difference of the standard working condition approach point, the supplementary combustion node temperature is obtained according to the supplementary combustion steam mass flow rate, the steam saturation enthalpy value, the supplementary combustion approach point enthalpy value, the supplementary combustion flue gas flow rate, the heat capacity of the combustion gas and the supplementary combustion exhaust temperature; When the refueling node temperature is the same as the standard operating condition node temperature and the refueling approach point temperature difference is the same as the standard operating condition approach point temperature difference, the refueling logarithmic mean temperature difference is obtained according to the refueling node temperature, and the refueling equivalent total heat transfer coefficient is obtained based on the refueling logarithmic mean temperature difference.

3. The method according to claim 2, characterized in that The supplementary combustion logarithmic mean temperature difference includes the supplementary combustion logarithmic mean temperature difference of the economizer and the supplementary combustion logarithmic mean temperature difference of the evaporator, and the supplementary combustion equivalent total heat transfer coefficient includes the supplementary combustion equivalent total heat transfer coefficient of the economizer and the evaporator equivalent total heat transfer coefficient; The step of obtaining the logarithmic mean temperature difference of supplementary combustion according to the supplementary combustion node temperature, and obtaining the supplementary combustion equivalent total heat transfer coefficient based on the logarithmic mean temperature difference of supplementary combustion includes: Obtaining the logarithmic mean temperature difference of the evaporator according to the post-combustion node temperature, the post-combustion exhaust temperature, the steam saturation temperature and the post-combustion approach point temperature; Obtaining the logarithmic mean temperature difference of the economizer supplementary combustion according to the supplementary combustion node temperature, the supplementary combustion exhaust temperature, the water supply temperature and the supplementary combustion approach point temperature; Obtaining an equivalent total heat transfer coefficient of the evaporator according to the logarithmic mean temperature difference of the evaporator supplementary combustion and the total energy of the evaporator supplementary combustion side; The equivalent total heat transfer coefficient of the economizer is obtained according to the logarithmic mean temperature difference of the supplementary combustion of the economizer and the total energy of the supplementary combustion side of the economizer.

4. The method according to claim 1, characterized in that: Comparing the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition, including: Comparing the equivalent total heat transfer coefficient under the standard working condition with the equivalent total heat transfer coefficient under the supplementary combustion working condition, and obtaining the difference between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition; Compare whether the difference meets the preset threshold, and obtain the comparison result that meets the preset threshold and the comparison result that does not meet the preset threshold.

5. The method according to claim 1, characterized in that After obtaining the equivalent total heat transfer coefficient under the target supplementary combustion condition, the method further includes: An objective function is established to minimize the deviation between the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplemental combustion working condition by adjusting the approach point temperature difference and the exhaust temperature after supplemental combustion.

6. The method according to claim 1, characterized in that The standard performance parameters include exhaust thermal conductivity, exhaust viscosity and flue gas volume; the equivalent total heat transfer coefficient under standard operating conditions is obtained based on the standard performance parameters of the gas turbine combined cycle unit obtained in advance, including: Obtaining an equivalent total heat transfer coefficient of the evaporator under standard working conditions according to the exhaust gas thermal conductivity, the exhaust gas viscosity and the flue gas volume; The equivalent total heat transfer coefficient of the economizer under standard operating conditions is obtained according to the exhaust gas thermal conductivity, the exhaust gas viscosity and the flue gas volume.

7. The method according to claim 1, characterized in that Before obtaining the equivalent total heat transfer coefficient under standard operating conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance, the method further includes: Obtaining initial operating parameters of the gas turbine combined cycle unit; Based on the initial operating condition parameters, standard performance parameters of the gas turbine combined cycle unit are obtained.

8. A system for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions, characterized in that: The system comprises a standard equivalent total heat transfer coefficient module, a supplementary combustion equivalent total heat transfer coefficient module, a comparison module and a performance determination module, wherein: The standard equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under standard working conditions according to the standard performance parameters of the gas turbine combined cycle unit obtained in advance; The supplementary combustion equivalent total heat transfer coefficient module is used to obtain the equivalent total heat transfer coefficient under the supplementary combustion working condition according to the preset supplementary combustion exhaust temperature; The comparison module is used to compare the equivalent total heat transfer coefficient under the standard working condition and the equivalent total heat transfer coefficient under the supplementary combustion working condition; The performance determination module is used to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition by adjusting the approach point temperature difference and the exhaust temperature after supplementary combustion until the comparison result meets the preset threshold value when the comparison result does not meet the preset threshold value, and determine the performance of the gas turbine combined cycle unit under the supplementary combustion condition based on the equivalent total heat transfer coefficient under the target supplementary combustion condition; The method of adjusting the approach point temperature difference and the exhaust temperature after the supplementary combustion until the comparison result meets the preset threshold value to obtain the equivalent total heat transfer coefficient under the target supplementary combustion condition includes: Setting the temperature difference at the approach point of the reburning, obtaining the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, obtaining the initial reburning equivalent total heat transfer coefficient of the evaporator based on the logarithmic mean temperature difference of the reburning of the evaporator and the total energy measured by the reburning of the evaporator, repeatedly setting the approach point temperature difference until the comparison result meets the preset threshold value, and obtaining the equivalent total heat transfer coefficient of the evaporator under the target reburning working condition; Set the exhaust temperature after reburning, obtain the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, obtain the equivalent total heat transfer coefficient of the economizer initial reburning based on the logarithmic mean temperature difference of the economizer reburning and the total energy measured by the economizer reburning gas, repeatedly set the exhaust temperature after reburning until the comparison result meets the preset threshold, and obtain the equivalent total heat transfer coefficient of the economizer under the target reburning condition.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, a method for determining the performance of a gas turbine combined cycle unit under supplementary combustion conditions is implemented as described in any one of claims 1 to 7.

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