Gas turbine air-cooled turbine performance calculation method and device, and electronic equipment

Abstract

This disclosure proposes a method, apparatus, and electronic equipment for calculating the performance of an air-cooled gas turbine, relating to the field of gas turbine performance evaluation technology. The method includes: acquiring work data of cooling air at multiple preset cross-sections of the target gas turbine, and acquiring the operating parameters of the target gas turbine; calculating the turbine efficiency of the target gas turbine based on the work data and operating parameters. Thus, by dividing the turbine into multiple preset cross-sections and collecting work data from each corresponding cross-section, the complex influence of cooling air on the gas turbine is transformed into data collection and analysis at simpler preset cross-sections. This reduces complexity while incorporating the influence of cooling air on the gas turbine, facilitating subsequent performance evaluation. Compared to current turbine efficiency evaluation methods, this reduces the number of iterations in the design process, shortens the development cycle, and thus lowers R&D costs.

Description

Technical Field

[0001] This disclosure relates to the field of gas turbine performance evaluation technology, and in particular to a method, apparatus, and electronic equipment for calculating the performance of a gas-cooled gas turbine. Background Technology

[0002] Heavy-duty gas turbines are efficient, clean, and high-power power generation devices. Gas turbines and their combined cycle systems are widely used in natural gas power generation or combined heat and power (CHP) systems. A gas turbine mainly consists of three major components: a compressor, a combustion chamber, and a turbine. The compressor draws in air from the environment, compresses it to form high-pressure air, and sends the high-pressure air into the combustion chamber, where it reacts with fuel to generate high-temperature, high-pressure gas. The high-temperature, high-pressure gas expands and does work in the turbine, and is discharged after its temperature and pressure decrease.

[0003] In the operation and control of heavy-duty gas turbines, maintaining high efficiency requires ensuring the combustion chamber outlet temperature doesn't decrease while simultaneously preventing it from exceeding design values ​​for safe operation, as this would significantly shorten the lifespan of hot-end components. However, in actual gas turbine operation, the combustion chamber outlet temperature cannot be measured online. The usual strategy involves calculating the outlet temperature using a specific model based on the turbine exhaust temperature and the gas turbine pressure ratio—indirectly controlling the outlet temperature through monitoring these parameters. Changes in turbine efficiency can alter the relationship between the combustion chamber outlet temperature, exhaust temperature, and pressure ratio, making it difficult to maintain the required temperature using the original built-in control strategy. Therefore, timely detection of turbine blade problems is crucial for the safe operation and optimized maintenance of gas turbine units. Summary of the Invention

[0004] This disclosure aims to at least partially address one of the technical problems in the related art.

[0005] Therefore, one objective of this disclosure is to propose a method for calculating the performance of a gas turbine.

[0006] The second objective of this disclosure is to provide a device for calculating the performance of a gas turbine.

[0007] The third objective of this disclosure is to propose an electronic device.

[0008] The fourth objective of this disclosure is to provide a non-transitory computer-readable storage medium.

[0009] The fifth objective of this disclosure is to provide a computer program product.

[0010] To achieve the above objectives, the first aspect of this disclosure proposes a method for calculating the performance of a gas turbine with air cooling, comprising: acquiring work data of cooling air at multiple preset sections of a target gas turbine, and acquiring operating parameters of the target gas turbine; and calculating the turbine efficiency of the target gas turbine based on the work data and the operating parameters.

[0011] According to one embodiment of this disclosure, the operating parameters include the turbine shaft work, physical speed, first gas flow rate through four cross sections, second specific enthalpy increase of the flow rate through the first stage rotor, gas flow rate of each stage rotor, and turbine rotor diameter of the target gas turbine. The work data of the cooling air includes the second gas flow rate of the cooling air obtained from multiple preset cross sections and the first specific enthalpy increase of the cooling air obtained from the multiple preset cross sections. The calculation of the turbine efficiency of the target gas turbine based on the work data and the operating parameters includes: calculating the turbine efficiency of the target gas turbine based on the turbine shaft work, the physical speed, the first gas flow rate, the second gas flow rate, the first specific enthalpy increase, the second specific enthalpy increase, and the gas flow rate and turbine rotor diameter of the rotor.

[0012] According to one embodiment of this disclosure, the calculation of the turbine efficiency of the target gas turbine based on the turbine shaft work, the physical rotational speed, the first gas flow rate, the second gas flow rate, the first specific enthalpy increase, the second specific enthalpy increase, and the rotor gas flow rate and turbine rotor diameter includes: calculating a first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter; calculating a second factor based on the corresponding second gas flow rate and the first specific enthalpy increase obtained from the plurality of preset cross-sections; multiplying the first specific enthalpy increase and the first gas flow rate to calculate a third factor; adding the first factor and the turbine shaft work, and using the sum as a fourth factor; adding the first factor, the second factor, and the third factor to calculate a fifth factor; and dividing the fourth factor and the fifth factor to calculate the turbine efficiency of the target gas turbine.

[0013] According to one embodiment of this disclosure, the formula for calculating the first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter is as follows: Wherein, P is the first factor, N is the physical rotational speed, and W... k Let D be the gas flow rate of the k-th stage rotor. k Let n be the turbine rotor diameter of the k-th stage rotor, and n be the total number of turbine stages of the target gas turbine.

[0014] According to one embodiment of this disclosure, the formula for calculating the second factor based on the corresponding second gas flow rate and first specific enthalpy increase obtained from the plurality of preset cross-sections is as follows: Wherein, Q is the second factor, and W i The second gas flow rate obtained for the i-th preset cross-section, ΔH i,is This is the increase in the first specific enthalpy.

[0015] According to one embodiment of this disclosure, obtaining the turbine rotor diameter of each stage rotor includes: obtaining the inlet diameter and outlet diameter of the target gas turbine; and for the k-th stage rotor, calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages of the target gas turbine, the inlet diameter, and the outlet diameter.

[0016] According to one embodiment of this disclosure, the formula for calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages of the target gas turbine, the inlet diameter, and the outlet diameter is as follows: Wherein, the D k Let D be the turbine rotor diameter of the k-th stage rotor. f Where D is the inlet diameter. l The outlet diameter is [value].

[0017] To achieve the above objectives, a second aspect of this disclosure provides a gas turbine air-cooled turbine performance calculation device, comprising: an acquisition module for acquiring work data of cooling air at multiple preset sections of a target gas turbine and acquiring operating parameters of the target gas turbine; and a calculation module for calculating the turbine efficiency of the target gas turbine based on the work data and the operating parameters.

[0018] To achieve the above objectives, a third aspect of this disclosure provides an electronic device, comprising: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, the instructions being executed by the at least one processor to implement the gas turbine performance calculation method as described in the first aspect of this disclosure.

[0019] To achieve the above objectives, a fourth aspect of this disclosure provides a non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are used to implement the gas turbine performance calculation method as described in the first aspect of this disclosure.

[0020] To achieve the above objectives, a fifth aspect of this disclosure provides a computer program product, including a computer program that, when executed by a processor, is used to implement the gas turbine performance calculation method as described in the first aspect of this disclosure.

[0021] Therefore, by dividing the turbine into multiple preset sections and obtaining the work data of each corresponding section, the complex influence of cooling gas on the gas turbine can be transformed into a simple preset section for acquisition and analysis. This reduces the complexity while incorporating the influence of cooling gas on the gas turbine, facilitating subsequent performance evaluation. Compared with current turbine efficiency evaluation methods, this reduces the number of iterations in the design process, shortens the development cycle, and thus lowers R&D costs. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of a gas turbine performance calculation method according to one embodiment of the present disclosure;

[0023] Figure 2 This is a schematic diagram of the cross-sectional division of a target gas turbine according to one embodiment of the present disclosure;

[0024] Figure 3 This is a schematic diagram of another method for calculating the performance of a gas turbine air-cooled turbine according to one embodiment of this disclosure;

[0025] Figure 4 This is a schematic diagram of another method for calculating the performance of a gas turbine air-cooled turbine according to one embodiment of this disclosure;

[0026] Figure 5 This is a schematic diagram of a gas turbine performance calculation device according to one embodiment of the present disclosure;

[0027] Figure 6 This is a schematic diagram of an electronic device according to one embodiment of the present disclosure. Detailed Implementation

[0028] Embodiments of this disclosure are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this disclosure, and should not be construed as limiting this disclosure.

[0029] The acquisition, storage, use, and processing of data in this disclosed technical solution all comply with the relevant provisions of relevant laws and regulations.

[0030] It should be noted that in the embodiments of this application, certain software, components, models and other existing solutions in the industry may be mentioned. These should be regarded as exemplary and are only intended to illustrate the feasibility of implementing the technical solution of this application. However, it does not mean that the applicant has used or necessarily used the solution.

[0031] Figure 1This is a schematic diagram of a method for calculating the performance of a gas turbine air-cooled turbine according to one embodiment of this disclosure, as shown below. Figure 1 As shown, the method for calculating the performance of a gas turbine includes the following steps:

[0032] S101, acquire the work data of cooling air at multiple preset sections of the target gas turbine, and acquire the operating parameters of the target gas turbine.

[0033] The gas turbine gas-cooled turbine performance calculation method of this application embodiment can be applied to the scenario of gas turbine control. The execution subject of the gas turbine gas-cooled turbine performance calculation of this application embodiment can be the gas turbine gas-cooled turbine performance calculation device of this application embodiment, which can be installed on an electronic device.

[0034] Currently, there are two different methods for calculating the efficiency of a gas turbine: one is to study its expansion process in detail and solve for each stage step by step, which is called the detailed solution method; the other treats the turbine as a "black box", which is called the black box solution method.

[0035] For detailed solution methods, if the equivalent single-stage turbine method is used, a certain amount of work capacity is allocated proportionally to the location of each cooling air mixing stage. However, the calculation process does not analyze the detailed influence of the cooling air, and the work capacity is only based on the location of cooling air mixing, without considering the pressure difference between the cooling air and the mainstream gas, resulting in insufficient accuracy. While the stage-by-stage calculation method directly studies the influence of cooling air compared to the equivalent single-stage turbine method, it requires knowledge of the efficiency of each turbine stage and the work distribution between the two rotor stages. Furthermore, when simulating outside the design point, the characteristic curves of each single-stage turbine must be known. These turbine characteristic curves cannot be obtained from turbine tests because such testing methods do not yet exist. Characteristic curves obtained from turbine test benches cannot fully reflect the actual turbine conditions because the temperature ratio between the cooling air and the main combustion gas flow in such tests is completely different from that in an actual engine, making it impossible to accurately simulate the influence of the cooling air flow on the main combustion gas flow. The characteristic curve of the second-stage turbine is affected by the constantly changing swirl angle at the outlet of the first-stage turbine. Therefore, theoretically, several turbine characteristic curves are needed for different inlet swirl angles.

[0036] For the black-box solution method, the advantage of this turbine efficiency definition is that it completely eliminates the need to assume the work capacity of each secondary gas stream. The work capacity of these gas streams is defined by their respective pressures and temperatures, which are at least theoretically measurable. Therefore, this aerodynamic thermodynamic turbine efficiency is better than the detailed solution method. Furthermore, the aerodynamic thermodynamic efficiency considers the pressure of the secondary gas stream, while all other efficiency definitions do not. The main problem with this calculation method is the significant difficulty in calculating at non-design points and the lack of consideration for losses.

[0037] In practice, underestimating the work capacity of the cooling air can lead to an underestimation of the calculated power, necessitating the use of other adjustment schemes to increase the power. This can result in an overestimation of the gas turbine power during later testing, potentially causing a mismatch between the compressor and turbine, leading to a disruptive design. Conversely, overestimating the work capacity of the cooling air can result in an overestimation of the turbine power and turbine efficiency, leading to problems such as the gas turbine power failing to meet design requirements or a mismatch between the compressor and turbine during later testing.

[0038] To better reflect the impact of cooling air on gas turbine performance, this disclosed method incorporates the work done by cooling air at multiple preset cross-sections of the target gas turbine into subsequent turbine efficiency calculations. By dividing the turbine into multiple preset cross-sections and acquiring the work done by each corresponding cross-section, the complex impact of cooling air on the gas turbine is transformed into data acquisition and analysis using simpler preset cross-sections. This reduces complexity while incorporating the impact of cooling air on the gas turbine, facilitating subsequent performance evaluation. It should be noted that the preset cross-sections are those of gas turbines used for specific data analysis or research purposes. The setting of these preset cross-sections is related to the gas turbine model, the data to be acquired, and / or the research objective; therefore, the preset cross-sections can be limited and modified according to actual design needs. For example, the cross-section division of the target gas turbine can be as follows: Figure 2 As shown, it may include sections 2, 3, 31, 4, 41, 5, 6, and 8, wherein section 2 is the compressor inlet, section 3 is the compressor outlet, section 31 is the combustion chamber inlet, section 4 is the turbine inlet (combustion chamber outlet), section 41 is the turbine first-stage rotor inlet, section 5 is the turbine outlet, section 6 is the gas turbine outlet, and section 8 is the gas turbine exhaust device outlet.

[0039] In the embodiments of this disclosure, the work data of the cooling air may include various parameters, which are not limited here, and can be specifically defined according to actual design needs. For example, the work data of the cooling air may include the flow rate, temperature, pressure, specific enthalpy change, etc.

[0040] Operating parameters of a gas turbine are important indicators for evaluating its performance, efficiency, and reliability. Operating parameters may include one or more of the following: inlet parameters, compressor parameters, combustion chamber parameters, turbine parameters, etc.

[0041] In this embodiment of the disclosure, the operating parameters of the gas turbine can be manually set parameters or parameters that can be adjusted according to actual production needs.

[0042] There are several methods for obtaining work data on cooling air. One possible approach is to establish a simulation model of the target gas turbine and then obtain the work data on cooling air through simulation.

[0043] In another possible implementation, the work done by the cooling air can be obtained through a work calculation algorithm. This algorithm is pre-designed and can be modified according to actual design needs or requirements. For example, the work done by the cooling air at a preset cross-section can be calculated using the work calculation algorithm.

[0044] In actual operation, as the rotor cooling air accelerates to the blade tangential velocity, the enthalpy value in the cooling air also increases. However, this enthalpy increase is difficult to calculate. It is generally believed that the shaft power required for the rotor cooling air to accelerate to the blade tangential velocity is close to the change in enthalpy in the cooling air caused by it. Therefore, the work done by the cooling air can be calculated based on the rotor shaft power.

[0045] S102 calculates the turbine efficiency of the target gas turbine based on work data and operating parameters.

[0046] In this embodiment, the work done by the cooling air at multiple preset cross-sections of the target gas turbine is first acquired, along with the operating parameters of the target gas turbine. Then, the turbine efficiency of the target gas turbine is calculated based on the work done data and operating parameters. Thus, by dividing the turbine into multiple preset cross-sections and collecting work done data for each corresponding cross-section, the complex influence of cooling air on the gas turbine is transformed into data collection and analysis for simpler preset cross-sections. This reduces complexity while incorporating the influence of cooling air on the gas turbine, facilitating subsequent performance evaluation. Compared to current turbine efficiency evaluation methods, this reduces the number of iterations in the design process, shortens the development cycle, and thereby lowers R&D costs.

[0047] It should be noted that the operating parameters include the turbine shaft work, physical speed, first gas flow rate through four sections, second specific enthalpy increase through the first-stage rotor flow rate, gas flow rate of each stage rotor, and turbine rotor diameter of the target gas turbine. The cooling air work data includes the second gas flow rate of the cooling air obtained from multiple preset sections and the first specific enthalpy increase of the cooling air obtained from multiple preset sections. The turbine efficiency of the target gas turbine is calculated based on the work data and operating parameters. The turbine efficiency of the target gas turbine can be calculated based on the turbine shaft work, physical speed, first gas flow rate, second gas flow rate, first specific enthalpy increase, second specific enthalpy increase, as well as the rotor gas flow rate and turbine rotor diameter.

[0048] In the above embodiments, the turbine efficiency of the target gas turbine is calculated based on turbine shaft work, physical rotational speed, first gas flow rate, second gas flow rate, first specific enthalpy increase, second specific enthalpy increase, and the rotor gas flow rate and turbine rotor diameter. Furthermore, it can be calculated by... Figure 3 To further explain, the method includes:

[0049] S301, calculate the first factor based on the physical rotational speed, the gas flow rate of each stage rotor and the turbine rotor diameter, calculate the second factor based on the corresponding second gas flow rate and the first specific enthalpy increase obtained at multiple preset cross sections, and multiply the first specific enthalpy increase and the first gas flow rate to calculate and obtain the third factor.

[0050] In this embodiment of the disclosure, the formula for calculating the first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter is as follows:

[0051]

[0052] Where P is the first factor, N is the physical rotational speed, and W k Let D be the gas flow rate of the k-th stage rotor. k Let be the turbine rotor diameter of the k-th stage, n be the total number of turbine stages of the target gas turbine, and 1 / 2 and 60 be constant coefficients that can be obtained experimentally.

[0053] As can be seen from the above formula, the first factor comprehensively considers factors such as the gas flow rate of each rotor stage, the turbine rotor diameter, and the physical rotational speed. Specifically, the contribution of each rotor stage to the first factor is related to its gas flow rate W. k It is related to the rotational speed and diameter.

[0054] The formula for calculating the second factor based on the corresponding second gas flow rate and first specific enthalpy increase obtained from multiple preset cross-sections is as follows:

[0055]

[0056] Where Q is the second factor, W i The second gas flow rate collected at the i-th preset cross-section represents the second gas flow rate collected at different preset cross-sections (from 1 to (m)). The gas flow rate at each cross-section may be different, therefore it needs to be measured or calculated separately. ΔH i,is The first specific enthalpy increase is the i-th preset cross section. Specific enthalpy increase is usually related to thermodynamic processes. For example, in a gas turbine, it may represent the change in enthalpy of the gas passing through the turbine.

[0057] As can be seen from the above formula, the second factor represents the sum of the changes in gas energy at each stage or section in the gas turbine.

[0058] The formula for calculating the third factor by multiplying the first specific enthalpy increase and the first gas flow rate is as follows:

[0059] O=W4*ΔH is

[0060] Where O is the third factor, ΔH isW4 represents the first specific enthalpy increase for the i-th preset cross-section, and W4 represents the first gas flow rate. The third factor represents the change in energy carried by the gas passing through this cross-section per unit time, i.e., the energy transfer rate or power.

[0061] S302, add the first factor and the turbine shaft work together, and use the sum as the fourth factor, and add the first factor, the second factor and the third factor together to calculate the fifth factor.

[0062] It's important to note that turbine work refers to the mechanical energy generated in a gas turbine through the expansion of gas within the turbine section. This energy is typically used to drive equipment such as compressors or generators. Specifically, turbine work is achieved through the expansion of high-temperature, high-pressure gas within the turbine. During this process, the gas's pressure and temperature decrease, while its kinetic energy increases, thus driving the turbine blades to rotate and generating mechanical work. Turbine work reflects the efficiency of energy conversion from thermal energy to mechanical energy. In this process, the high-temperature, high-pressure gas expands upon entering the turbine, resulting in a decrease in its internal energy, which is then converted into mechanical energy output.

[0063] The sum of the first factor and the turbine shaft work represents different forms of energy (kinetic and mechanical energy), and their combination can be seen as a more comprehensive assessment of the energy of the entire system. Therefore, the fourth factor can help engineers better understand the energy distribution within the system, especially in the design phase for optimizing the matching between different components.

[0064] In actual operation, as the rotor cooling air accelerates to the blade tangential velocity, the enthalpy in the cooling air also increases. However, this enthalpy increase is difficult to calculate. It is generally believed that the shaft power required to accelerate the rotor cooling air to the blade tangential velocity is close to the resulting change in enthalpy in the cooling air, and here we consider them to be equal. Therefore, the first factor can be regarded as the shaft power required to accelerate the rotor cooling air to the blade tangential velocity.

[0065] Adding the first, second, and third factors together provides a comprehensive assessment of the different energy conversion processes within the gas turbine system. Calculating the sum of these three factors helps engineers perform energy balance analysis of the system, understand the energy input and output of each component, and thus optimize the design and improve overall efficiency.

[0066] S303, divide the fourth factor and the fifth factor to calculate the turbine efficiency of the target gas turbine.

[0067] In this embodiment of the disclosure, the formula for calculating the turbine efficiency of the target gas turbine is:

[0068]

[0069] In one possible scenario, the diameter of each rotor stage cannot be determined before the turbine flow path calculation is completed. In this embodiment of the disclosure, when the diameter of each rotor stage cannot be directly obtained, the diameter of each rotor stage can be calculated using the following method: Figure 4 As shown:

[0070] S401, obtain the inlet diameter and outlet diameter of the target gas turbine.

[0071] S402, for the k-th stage rotor, calculate the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages, inlet diameter, and outlet diameter of the target gas turbine.

[0072] It should be noted that the turbine inlet and outlet diameters can be calculated based on the inlet and outlet Mach numbers and temperatures. The design of each stage turbine rotor diameter is also related to the inlet and outlet diameters. Therefore, after obtaining the inlet and outlet diameters of the target gas turbine, the turbine rotor diameter for each stage can be derived from these diameters. The variation in the gas turbine rotor diameter depends on the actual design of the gas turbine.

[0073] Taking a linear change in diameter from inlet to outlet as an example, the formula for calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages, inlet diameter, and outlet diameter of the target gas turbine is as follows:

[0074]

[0075] Among them, D k Let D be the diameter of the turbine rotor of the k-th stage. f D is the inlet diameter. l This refers to the outlet diameter.

[0076] Substituting the formula for turbine rotor diameter into the formula for calculating the turbine efficiency of the target gas turbine, we can obtain the following formula:

[0077]

[0078] Corresponding to the gas turbine performance calculation methods provided in the above embodiments, one embodiment of this disclosure also provides a gas turbine performance calculation device. Since the gas turbine performance calculation device provided in this disclosure corresponds to the gas turbine performance calculation methods provided in the above embodiments, the implementation methods of the above gas turbine performance calculation methods are also applicable to the gas turbine performance calculation device provided in this disclosure, and will not be described in detail in the following embodiments.

[0079] Figure 5This is a schematic diagram of a gas turbine performance calculation device according to one embodiment of the present disclosure, as shown below. Figure 5 As shown, the gas turbine performance calculation device 500 includes: an acquisition module 510 and a calculation module 520.

[0080] The acquisition module 510 is used to acquire the work data of the cooling air at multiple preset sections of the target gas turbine, and to acquire the operating parameters of the target gas turbine.

[0081] The calculation module 520 is used to calculate the turbine efficiency of the target gas turbine based on the work data and operating parameters.

[0082] According to one embodiment of this disclosure, the operating parameters include the turbine shaft work, physical speed, first gas flow rate through four cross sections, second specific enthalpy increase of the flow rate through the first stage rotor, gas flow rate of each stage rotor, and turbine rotor diameter of the target gas turbine. The work data of the cooling air includes the second gas flow rate of the cooling air obtained from multiple preset cross sections and the first specific enthalpy increase of the cooling air obtained from multiple preset cross sections. The turbine efficiency of the target gas turbine is calculated based on the work data and operating parameters, including: calculating the turbine efficiency of the target gas turbine based on the turbine shaft work, physical speed, first gas flow rate, second gas flow rate, first specific enthalpy increase, second specific enthalpy increase, and the gas flow rate and turbine rotor diameter of the rotor.

[0083] According to one embodiment of this disclosure, the turbine efficiency of a target gas turbine is calculated based on turbine shaft work, physical rotational speed, first gas flow rate, second gas flow rate, first specific enthalpy increase, second specific enthalpy increase, and the rotor gas flow rate and turbine rotor diameter. The calculation includes: calculating a first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter; calculating a second factor based on the corresponding second gas flow rate and first specific enthalpy increase obtained from multiple preset cross-sections; multiplying the first specific enthalpy increase and the first gas flow rate to calculate a third factor; adding the first factor and the turbine shaft work, and using the sum as a fourth factor; adding the first factor, the second factor, and the third factor to calculate a fifth factor; and dividing the fourth factor and the fifth factor to calculate the turbine efficiency of the target gas turbine.

[0084] According to one embodiment of this disclosure, the formula for calculating the first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter is as follows: Where P is the first factor, N is the physical rotational speed, and W k Let D be the gas flow rate of the k-th stage rotor. k Let n be the turbine rotor diameter of the k-th stage rotor, and n be the total number of turbine stages of the target gas turbine.

[0085] According to one embodiment of this disclosure, the formula for calculating the second factor based on the corresponding second gas flow rate and first specific enthalpy increase obtained from multiple preset cross-sections is as follows: Where Q is the second factor, W i ΔH represents the second gas flow rate collected at the i-th preset cross-section. i,is This is the first specific enthalpy increase.

[0086] According to one embodiment of this disclosure, obtaining the turbine rotor diameter of each stage rotor includes: obtaining the inlet diameter and outlet diameter of the target gas turbine; and for the k-th stage rotor, calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages, inlet diameter, and outlet diameter of the target gas turbine.

[0087] According to one embodiment of this disclosure, the formula for calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages, inlet diameter, and outlet diameter of the target gas turbine is as follows: Among them, D k Let D be the diameter of the turbine rotor of the k-th stage. f D is the inlet diameter. l This refers to the outlet diameter.

[0088] Therefore, by dividing the turbine into multiple preset sections and collecting the work data of each section, the complex influence of cooling gas on the gas turbine can be transformed into a simple preset section for data collection and analysis. This reduces the complexity while incorporating the influence of cooling gas on the gas turbine, facilitating subsequent performance evaluation. Compared with current turbine efficiency evaluation methods, this reduces the number of iterations in the design process, shortens the development cycle, and thus lowers R&D costs.

[0089] To implement the above embodiments, this disclosure also proposes an electronic device 600. Figure 6 This is a schematic diagram of an electronic device according to one embodiment of the present disclosure, such as... Figure 6 As shown, the electronic device 600 includes: a processor 601 and a memory 602 communicatively connected to the processor. The memory 602 stores instructions executable by at least one processor. The instructions are executed by at least one processor 601 to implement the functions described in this disclosure. Figures 1-4 The method for calculating the performance of a gas turbine with air cooling in the embodiment.

[0090] To implement the above embodiments, this disclosure also proposes a non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are used to cause a computer to implement the present disclosure. Figures 1-4 The method for calculating the performance of a gas turbine with air cooling in the embodiment.

[0091] To implement the above embodiments, this disclosure also proposes a computer program product, including a computer program, which, when executed by a processor, implements the features of this disclosure. Figures 1-4 The method for calculating the performance of a gas turbine with air cooling in the embodiment.

[0092] It should be noted that personal information collected from users should be used for legitimate and reasonable purposes and should not be shared or sold outside of these legitimate uses. Furthermore, such collection / sharing should only be conducted after receiving the user's informed consent, including but not limited to notifying the user to read the user agreement / user notice and sign an agreement / authorization that includes authorization of relevant user information before the user uses the function. In addition, any necessary steps must be taken to protect and safeguard access to such personal information data and ensure that others with access to personal information data comply with their privacy policies and procedures.

[0093] This application is intended to provide an implementation scheme for users to selectively prevent the use or access to their personal information data. Specifically, this disclosure is intended to provide hardware and / or software to prevent or block access to such personal information data. Once personal information data is no longer needed, risks can be minimized by restricting data collection and deleting data. Furthermore, where applicable, such personal information is de-identified to protect user privacy.

[0094] In the foregoing descriptions of the embodiments, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0095] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0096] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0097] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a ordered list of executable instructions for implementing logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (such as a computer-based system, a processor-included system, or other system that can fetch and execute instructions from, an instruction execution system, apparatus, or device). For the purposes of this specification, "computer-readable medium" can be any means that contains, stores, communicates, propagates, or transmits programs for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include: an electrical connection having one or more wires (electronic device), a portable computer disk drive (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and editable read-only memory (EPROM or flash memory), fiber optic devices, and portable optical disc read-only memory (CDROM). Alternatively, the computer-readable medium may be paper or other suitable media on which the program can be printed, since the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, interpreting, or otherwise processing as necessary, and then stored in a computer memory.

[0098] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0099] Those skilled in the art will understand that all or part of the steps of the methods described in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it includes one or a combination of the steps of the method embodiments.

[0100] Furthermore, the functional units in the various embodiments of this application can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0101] The storage medium mentioned above can be a read-only memory, a disk, or an optical disk, etc. Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of this application.

Claims

1. A method for calculating the performance of a gas turbine with air cooling, characterized in that, include: Acquire the work data of cooling air at multiple preset sections of the target gas turbine, and acquire the operating parameters of the target gas turbine; The turbine efficiency of the target gas turbine is calculated based on the work done and the operating parameters. The operating parameters include the turbine shaft work, physical speed, first gas flow rate through the turbine inlet, second specific enthalpy increase of the flow rate through the first-stage rotor, gas flow rate of each stage rotor, and turbine rotor diameter of the target gas turbine. The work data of the cooling air includes the second gas flow rate of the cooling air obtained from multiple preset cross-sections and the first specific enthalpy increase of the cooling air obtained from the multiple preset cross-sections. The calculation of the turbine efficiency of the target gas turbine based on the work data and the operating parameters includes: The first factor is calculated based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter; the second factor is calculated based on the corresponding second gas flow rate and the first specific enthalpy increase obtained from the plurality of preset cross sections; and the first specific enthalpy increase and the first gas flow rate are multiplied to calculate and obtain the third factor. The first factor and the turbine shaft work are added together, and the sum is used as the fourth factor. The first factor, the second factor and the third factor are added together to calculate the fifth factor. The turbine efficiency of the target gas turbine is calculated by dividing the fourth factor and the fifth factor.

2. The method according to claim 1, characterized in that, The formula for calculating the first factor based on the physical rotational speed, the gas flow rate of each stage rotor, and the turbine rotor diameter is as follows: Wherein, P is the first factor, N is the physical rotational speed, and the... The gas flow rate of the k-th stage rotor is... Let n be the turbine rotor diameter of the k-th stage rotor, and n be the total number of turbine stages of the target gas turbine.

3. The method according to claim 1, characterized in that, The formula for calculating the second factor based on the corresponding second gas flow rate and first specific enthalpy increase obtained from the multiple preset cross-sections is as follows: Wherein, Q is the second factor, and the The second gas flow rate obtained for the i-th preset cross-section, the The first specific enthalpy increase for the i-th preset cross section.

4. The method according to claim 1, characterized in that, Obtain the turbine rotor diameter for each stage of the rotor, including: Obtain the inlet diameter and outlet diameter of the target gas turbine; For the k-th stage rotor, the turbine rotor diameter of the k-th stage rotor is calculated based on the total number of turbine stages of the target gas turbine, the inlet diameter, and the outlet diameter.

5. The method according to claim 4, characterized in that, The formula for calculating the turbine rotor diameter of the k-th stage rotor based on the total number of turbine stages of the target gas turbine, the inlet diameter, and the outlet diameter is as follows: Among them, the The diameter of the turbine rotor of the k-th stage rotor is... The inlet diameter is the specified diameter. The outlet diameter is n, and the total number of turbine stages is n.

6. A device for calculating the performance of a gas turbine, characterized in that, include: The acquisition module is used to acquire the work data of cooling air at multiple preset sections of the target gas turbine, and to acquire the operating parameters of the target gas turbine. The operating parameters include the turbine shaft work, physical speed, first gas flow rate through the turbine inlet, second specific enthalpy increase of the flow rate through the first stage rotor, gas flow rate of each stage rotor, and turbine rotor diameter. The work data of cooling air includes the second gas flow rate of cooling air acquired at the multiple preset sections and the first specific enthalpy increase of cooling air acquired at the multiple preset sections. The calculation module is used to calculate the turbine efficiency of the target gas turbine based on the work data and the operating parameters, including: calculating a first factor based on the physical speed, the gas flow rate of each stage rotor and the turbine rotor diameter, calculating a second factor based on the corresponding second gas flow rate and the first specific enthalpy increase obtained from the plurality of preset cross sections, and multiplying the first specific enthalpy increase and the first gas flow rate to calculate and obtain a third factor. The first factor and the turbine shaft work are added together, and the sum is used as the fourth factor. The first factor, the second factor and the third factor are added together to calculate the fifth factor. The turbine efficiency of the target gas turbine is calculated by dividing the fourth factor and the fifth factor.

7. An electronic device, characterized in that, Including memory and processor; The processor reads executable program code stored in the memory to run a program corresponding to the executable program code, so as to implement the method as described in any one of claims 1-5.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions, which, when executed by a processor, are used to implement the method as described in any one of claims 1-5.

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