One-dimensional aerodynamic optimization design method and system for real gas centrifugal compressor

Abstract

The application discloses a kind of real gas centrifugal compressor one-dimensional aerodynamic optimization design method and system, mainly for the one-dimensional optimization design of real gas centrifugal or mixed flow compressor, based on aerodynamic analysis database, extract real gas compressor optimal loss model;Based on the fluid thermophysical property database, the thermophysical property data of compressor working medium are generated;According to single-region average line method, one-dimensional aerodynamic analysis is carried out, and the design parameters of centrifugal compressor are obtained;With the feasible solution of compressor design parameters to initialize population, according to the one-dimensional aerodynamic analysis process and evolution algorithm, the design parameters are optimized, and the optimal design scheme of centrifugal compressor is obtained;According to the geometric parameters of centrifugal compressor, CAD modeling is carried out, and variable condition CFD calculation is carried out for compressor geometric model, to verify the performance index of centrifugal compressor under different design parameters.The application can quickly and accurately obtain the optimal design scheme of real gas centrifugal compressor, and help to improve the performance index of compressor.

Description

Technical Field

[0001] This invention relates to fluid machinery design methods, specifically a one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor, used for the aerodynamic design of real gas centrifugal compressors or mixed-flow compressors. Background Technology

[0002] Turbine compressors are divided into two types: centrifugal and axial-flow. In a centrifugal compressor, a high-speed rotating impeller applies centrifugal force to the gas, while the diffuser channel provides diffusion, thus increasing the gas pressure. Centrifugal compressors are characterized by their small size and high single-stage pressure ratio, and are widely used in key fields such as aerospace and marine propulsion, holding an extremely important position in the field of fluid machinery.

[0003] Since the 1950s, the design methodology for centrifugal compressors has evolved from zero-dimensional models based on criterion numbers and empirical relationships to a three-dimensional unsteady, refined design system based on flow field analysis and dynamic mode decomposition. Among these, aerodynamic analysis and scheme design within a one-dimensional framework, as the foundational step for impeller / blade topology shaping and parameter optimization, is one of the most crucial aspects of the aerodynamic development process.

[0004] The widespread use of real gases such as supercritical carbon dioxide and carbon tetrafluoride in process industries has significantly increased the difficulty of aerodynamic analysis and preliminary design of centrifugal compressors. The increased computational load in the design process challenges the accuracy and stability of the solution program, and recent advancements in gas dynamics are difficult to effectively transfer and apply to existing analysis systems. Therefore, this invention addresses the need and necessity for aerodynamic analysis and preliminary design of real gas centrifugal compressors by proposing a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors. Summary of the Invention

[0005] The purpose of this invention is to provide a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors, such as supercritical carbon dioxide centrifugal compressors and carbon dioxide-based mixed working fluid compressors in low-power supercritical fluid dynamic cycles, aerospace / underwater weapon power platforms, mobile high-load compact turbine expanders, etc.

[0006] This invention is achieved through the following technical solution:

[0007] A one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor includes the following steps:

[0008] Step 1: Obtain the optimal loss model for a real gas compressor;

[0009] Step 2: Obtain the thermophysical property data of the compressor working fluid;

[0010] Step 3: Perform one-dimensional aerodynamic analysis based on the optimal loss model and thermophysical data to obtain the performance indicators and working curves of the centrifugal compressor. Determine the design parameters of the moving and stationary components based on the performance indicators and working curves.

[0011] Step 4: Optimize the design parameters of moving and stationary components using a multi-objective optimization method, and design the centrifugal compressor based on the optimal design parameters of the moving and stationary components.

[0012] Preferably, the optimal loss model in step 1 includes incident angle of attack loss, blade load loss, surface friction loss, top clearance undercurrent loss, wake mixing loss, circulating undercurrent loss, disk friction loss, top leakage loss, and diffusion loss.

[0013] Preferably, the incident angle of attack loss (Δh) IN ):

[0014] Δh IN =f inc W1 2 sin 2 (β f1 -β b1 )

[0015] The blade load loss (△h) BL ):

[0016]

[0017]

[0018] The surface friction loss (Δh) SF ):

[0019]

[0020]

[0021] The top gap undercurrent loss (△h) TC ):

[0022]

[0023] The wake mixing loss (△h) WM ):

[0024]

[0025] The circulating undercurrent loss (△h) RC ):

[0026]

[0027] The disc friction loss (△h) DF ):

[0028]

[0029]

[0030] The top leakage loss (△h) LK ):

[0031]

[0032]

[0033] In the formula, Re is the Reynolds number, and d h1 d is the impeller inlet hub diameter. t1 d1 is the impeller inlet blade tip diameter, d2 is the impeller outlet diameter, b2 is the impeller outlet blade height, Z is the equivalent number of blades of the centrifugal impeller, and β is the impeller outlet blade height. h1 β is the blade mounting angle at the impeller inlet hub position. t1 β1 is the blade installation angle at the impeller inlet blade tip, and β2 is the blade installation angle at the impeller outlet. f1 α1 is the average relative airflow angle at the impeller inlet, α2 is the absolute airflow angle at the impeller outlet, and W is the mean relative airflow angle at the impeller inlet. h1 W represents the relative velocity at the impeller inlet hub position. t1 W1 is the relative velocity at the impeller inlet blade tip position, W2 is the relative airflow velocity at the impeller outlet, C1 is the average absolute velocity at the impeller inlet, and C... u2 U1 is the absolute circumferential velocity at the impeller outlet, U2 is the circumferential velocity at the impeller inlet blade tip, and U3 is the circumferential velocity at the impeller outlet.

[0034] Preferably, in step 2, thermal property data of the compressor working fluid are generated based on a fluid thermal property database;

[0035] The fluid thermophysical property database includes real gas equations of state and experimental databases of real gas thermophysical properties.

[0036] Preferably, in step 3, a one-dimensional aerodynamic analysis is performed using the single-region moving average method, and the design parameters of the moving and stationary components are calculated through inverse problem calculation.

[0037] Preferably, the method for one-dimensional aerodynamic analysis using the single-region moving average method is as follows:

[0038] S31. Determine the inlet velocity triangle of the centrifugal impeller based on the set geometric parameters of the centrifugal impeller inlet;

[0039] S32. Assuming the prior efficiency or entropy production of the centrifugal impeller, determine the actual compression power of the centrifugal impeller.

[0040] S33. Establish a set of nonlinear equations for the conserved quantities at the centrifugal impeller outlet, and solve them to obtain the design parameters and outlet velocity triangle of the centrifugal impeller.

[0041] S34. Based on the thermodynamic parameters, geometric parameters, inlet velocity triangle, and outlet velocity triangle of the centrifugal impeller, calculate the local energy loss caused by various irreversible processes during the actual compression process of the centrifugal compressor using the optimal loss model, and calculate the posterior efficiency of the centrifugal impeller based on the energy conservation relationship.

[0042] S35. Determine the difference between the prior efficiency of step S32 and the posterior efficiency of step S34. If the difference is greater than the allowable value, execute step S32 and iterate repeatedly until convergence to obtain the final actual compression power.

[0043] S36. Based on the principle of conservation of angular momentum and friction loss, calculate the flow loss and isentropic efficiency in the stationary component.

[0044] S37. Based on the isentropic efficiency of the centrifugal impeller, the final actual compression power, and the flow loss in the stationary components, calculate the performance indicators and operating curves of the centrifugal compressor, and determine the design parameters of the moving and stationary components based on the performance indicators and operating curves.

[0045] Preferably, the posterior efficiency is calculated as follows:

[0046]

[0047] In the formula, For internal losses, For parasitic loss.

[0048] Preferably, in step 4, a genetic algorithm is used to optimize the design parameters.

[0049] Preferably, the method for optimizing the design parameters of the moving and stationary components is as follows:

[0050] S41. Conduct sensitivity analysis on the design parameters to obtain the key design parameters of the centrifugal compressor;

[0051] S32. Sampling of key design parameters of centrifugal compressor to obtain initial population;

[0052] S33. Based on the initial population, use an evolutionary algorithm to perform multi-objective collaborative optimization of the geometric parameters of the centrifugal compressor, and obtain the optimized design parameters of the moving and stationary components of the centrifugal compressor.

[0053] A system for a one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor includes,

[0054] The loss model module is used to obtain the optimal loss model for a real gas compressor.

[0055] Thermophysical property data module is used to acquire the thermophysical property data of the compressor working fluid;

[0056] The dynamic and static parameter module is used to perform one-dimensional aerodynamic analysis based on the optimal loss model and thermophysical property data to obtain the performance indicators and working curves of the centrifugal compressor, and to determine the design parameters of the dynamic and static components based on the performance indicators and working curves.

[0057] The optimization module is used to optimize the design parameters of moving and stationary components using a multi-objective optimization method, and to design a centrifugal compressor based on the optimal design parameters of moving and stationary components.

[0058] Compared with the prior art, the present invention has the following beneficial technical effects:

[0059] This invention provides a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors. Through comparative experiments with standard models such as CO2 compressors and CCl4 compressors, the optimal correlations for various local loss models in the single-region average method are determined, improving the accuracy of isentropic efficiency calculations in the one-dimensional aerodynamic analysis process. Secondly, by coupling high-precision equations of state such as the Span-Wagner equation with experimental data on fluid thermophysical properties, the calculation errors of fluid working fluid state parameters and transport properties in the near-critical region are successfully reduced. In special cases such as transcritical and supercritical compressors, the calculated values ​​of key performance indicators such as compression ratio and efficiency better match the actual values, significantly improving the reliability of the one-dimensional aerodynamic design results.

[0060] This invention proposes a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors based on the single-region moving average method. On one hand, it can automatically generate aerodynamic design schemes and performance evaluation charts for the proposed design points of the centrifugal compressor based on rated design parameters and empirical preferences, completing the aerodynamic design of the centrifugal compressor (inverse problem calculation). On the other hand, it can also generate key indicators such as surge limit and variable operating condition boundary, operating curve, and machine Mach number of the centrifugal compressor based on the centrifugal compressor's geometric parameters, completing the aerodynamic analysis of the centrifugal compressor (forward problem calculation). The principle is simple and clear, the functions are comprehensive and powerful, and it takes into account all aspects of compressor product development. Furthermore, this method involves relatively small computational loads and is easily parallelized, resulting in fast and efficient execution. Attached Figure Description

[0061] Figure 1 This is a flowchart of a one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to the present invention.

[0062] Figure 2This is a flowchart of the one-dimensional aerodynamic analysis using the single-region moving average method of the present invention. Detailed Implementation

[0063] The present invention will now be described in further detail with reference to the accompanying drawings. These descriptions are intended to explain the invention and not to limit it.

[0064] See Figure 1 A one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor includes the following steps:

[0065] Step 1: Based on the aerodynamic analysis database, obtain the optimal loss model for a real gas compressor;

[0066] The optimal loss model includes incident angle of attack loss, blade load loss, surface friction loss, top clearance undercurrent loss, wake mixing loss, circulating undercurrent loss, disk friction loss, top leakage loss, and diffusion loss.

[0067] Incident angle of attack loss (△h) IN ):

[0068] Δh IN =f inc W1 2 sin 2 (β f1 -β b1 )

[0069] Blade load loss (Δh) BL ):

[0070]

[0071]

[0072] Surface friction loss (Δh) SF ):

[0073]

[0074]

[0075] Top gap undercurrent loss (Δh) TC ):

[0076]

[0077] Wake mixing loss (Δh) WM ):

[0078]

[0079] Circulating undercurrent loss (△h) RC ):

[0080]

[0081] Wheel friction loss (△h) DF ):

[0082]

[0083]

[0084] Top leakage loss (△h) LK ):

[0085]

[0086]

[0087] In the formula, Re is the Reynolds number, and d h1 d is the impeller inlet hub diameter. t1 d1 is the impeller inlet blade tip diameter, d2 is the impeller outlet diameter, b2 is the impeller outlet blade height, Z is the equivalent number of blades of the centrifugal impeller, and β is the impeller outlet blade height. h1 β is the blade mounting angle at the impeller inlet hub position. t1 β1 is the blade installation angle at the impeller inlet blade tip, and β2 is the blade installation angle at the impeller outlet. f1 α1 is the average relative airflow angle at the impeller inlet, α2 is the absolute airflow angle at the impeller outlet, and W is the mean relative airflow angle at the impeller inlet. h1 W represents the relative velocity at the impeller inlet hub position. t1 W1 is the relative velocity at the impeller inlet blade tip position, W2 is the relative airflow velocity at the impeller outlet, C1 is the average absolute velocity at the impeller inlet, and C... u2 U1 is the absolute circumferential velocity at the impeller outlet, U2 is the circumferential velocity at the impeller inlet blade tip, and ε is the circumferential velocity at the impeller outlet. b =0.1~0.5, b * =0 to 0.5.

[0088] Step 2: Generate the thermal property data of the compressor working fluid based on the fluid thermal property database;

[0089] The fluid thermophysical property database includes real gas equations of state and experimental databases of real gas thermophysical properties.

[0090] The equations of state for real gases include the RK equation, the BWR equation, the Martin-Hou equation, and the Span-Wagner equation.

[0091] Step 3: Perform one-dimensional aerodynamic analysis based on the optimal loss model and thermophysical property data to obtain the performance indicators and working curves of the centrifugal compressor. Determine the design parameters of the moving and stationary components based on the performance indicators and working curves.

[0092] See Figure 2 One-dimensional aerodynamic analysis was performed using the single-region moving average method. The design parameters of the moving and stationary components were calculated through inverse problem calculations. Specific design parameters included the impeller inlet hub diameter d. h1 Impeller inlet blade tip diameter d t1 Impeller outlet diameter d2, impeller outlet blade height b2, impeller inlet hub airflow angle β h1 The airflow angle β at the impeller inlet blade tip is perpendicular to the airflow. t1 The airflow angle β2 at the impeller outlet, specifically the one-dimensional aerodynamic analysis includes the following steps:

[0093] S31. Set the geometric parameters of the centrifugal impeller inlet, and calculate the inlet velocity triangle of the centrifugal impeller based on the velocity triangle relationship and the mass conservation equation of the centrifugal impeller.

[0094] S32. Assume the prior efficiency of the centrifugal impeller. Alternatively, based on entropy production, the actual compression power of the centrifugal impeller is calculated according to the thermodynamic parameters and design requirements of the centrifugal compressor.

[0095] S33. By combining the relative velocity at the outlet of the centrifugal impeller, the slip factor, the relative airflow angle, and the mass flow rate, a set of nonlinear equations about the outlet momentum of the centrifugal impeller is obtained. Solving the above set of nonlinear equations yields the design parameters of the centrifugal impeller and the outlet velocity triangle.

[0096] S34. Based on the thermodynamic parameters, geometric parameters, inlet velocity triangle, and outlet velocity triangle of the centrifugal impeller, calculate the local energy loss caused by various irreversible processes during the actual compression process of the centrifugal compressor using the optimal loss model, and calculate the posterior efficiency of the centrifugal impeller based on the energy conservation relationship. The calculation method is as follows:

[0097]

[0098] In the formula, For internal losses, The parasitic loss is calculated as follows:

[0099]

[0100] S35. Calculate the relative error δ between the prior efficiency in step S32 and the posterior efficiency in step S34. If the relative error is greater than the allowable value, execute step S32 and iterate repeatedly until convergence, i.e., the difference between the prior efficiency and the posterior efficiency is less than the allowable value, thus obtaining the final actual compression power. The method for calculating the relative error δ is as follows:

[0101]

[0102] S36. Based on the principle of conservation of angular momentum and friction loss, calculate the flow loss and isentropic efficiency in the stationary component;

[0103] S37. Based on the isentropic efficiency of the centrifugal impeller, the final actual compression power, and the flow loss inside the diffuser, calculate the performance indicators and operating curves of the centrifugal compressor, and determine the design parameters of the moving and stationary components based on the performance indicators and operating curves.

[0104] Step 4: Use a multi-objective optimization method to optimize the design parameters of moving and stationary components, and design a centrifugal compressor based on the obtained optimal design parameters of moving and stationary components.

[0105] The design parameters are optimized using a genetic algorithm. The specific optimization method is as follows:

[0106] S41. Perform sensitivity analysis on the design parameters obtained in step 3 to obtain the key design parameters of the centrifugal compressor;

[0107] S32. Use the Latin Hypercube Sampling method to sample the key design parameters of the centrifugal compressor in the empirical design space to obtain an initial population;

[0108] S33. Based on the initial population, use an evolutionary algorithm to perform multi-objective collaborative optimization of the compressor geometric parameters to obtain the optimal design scheme of the centrifugal compressor geometric parameters.

[0109] Among them, the types of evolutionary algorithms can be selected from different intelligent algorithms such as genetic algorithms and reinforcement learning, based on the results of sensitivity analysis.

[0110] Step 5: Based on the design parameters of the optimal moving and stationary components, perform CAD modeling to obtain the centrifugal compressor model. Then, perform CFD calculations under varying operating conditions on the compressor geometric model to verify the performance indicators of the centrifugal compressor under different design parameters.

[0111] The CAD modeling process described above is based on d h1 d t1 d2, b2, β h1 β t1 The geometric parameters of the β2 centrifugal compressor were designed, and a 3D model of the impeller and diffuser flow channel was generated using 3D modeling software. The obtained 3D model was then imported into mesh generation software for fluid domain mesh generation, followed by CFD calculations under varying operating conditions.

[0112] The CFD simulation process mainly involves steady-state simulation of the rotating and static coupled regions; the turbulence models selected are the SA turbulence model and the SST k-ω turbulence model, and the boundary conditions adopt the compressor design conditions.

[0113] This invention discloses a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors, primarily used for the one-dimensional aerodynamic design of real gas centrifugal or mixed-flow compressors. First, based on an aerodynamic analysis database, the optimal loss model for the real gas compressor is extracted. Then, based on a fluid thermophysical property database, thermophysical property data of the compressor working fluid is generated. Next, one-dimensional aerodynamic analysis is performed using the single-region moving average method to obtain the centrifugal compressor design parameters. A population is initialized with the feasible solution of the compressor design parameters, and the design parameters are optimized according to the one-dimensional aerodynamic analysis process and evolutionary algorithm to obtain the optimal design scheme for the centrifugal compressor. Finally, CAD modeling is performed based on the centrifugal compressor's geometric parameters, and variable-condition CFD calculations are conducted on the compressor's geometric model to verify the performance indicators of the centrifugal compressor under different design parameters. This method provides rapid, accurate, and efficient optimization design for real gas centrifugal compressors, such as supercritical carbon dioxide centrifugal compressors and carbon dioxide-based mixed-working-fluid compressors, in applications such as low-power supercritical fluid dynamic cycles, aerospace / underwater weapon power platforms, and mobile high-load compact turbine expanders.

[0114] Example 1

[0115] The following description uses a supercritical carbon dioxide (CO2) centrifugal compressor as an example to illustrate one technical solution of the present invention. The design requirements for the supercritical carbon dioxide centrifugal compressor are as follows:

[0116] Rated speed: 40000 rpm

[0117] CO2 mass flow rate: 6.4 kg / s

[0118] Inlet static pressure: 7.8 MPa

[0119] Inlet static temperature: 47℃

[0120] Outlet static pressure: ≥14.4MPa

[0121] Protection temperature: 130±10℃

[0122] To ensure a scientifically sound and consistent selection of design parameters during the one-dimensional design process, this paper outlines some fundamental design principles for supercritical carbon dioxide centrifugal compressors. Based on design experience with centrifugal compressors, a brief explanation of these principles is provided to confirm their rationality:

[0123] ① First, ensure that the design scheme can achieve the pressure ratio or outlet pressure specified in the design requirements.

[0124] ② While ensuring the pressure ratio, make the centrifugal stage have the highest possible isentropic efficiency.

[0125] ③ Minimize the blade installation angle β1 at the impeller inlet.

[0126] ④ Minimize the absolute airflow angle α2 at the centrifugal impeller outlet.

[0127] ⑤ Maximize the blade height b2 at the centrifugal impeller outlet.

[0128] ⑥ The centrifugal impeller does not have separation blades.

[0129] ⑦ Select the appropriate number of centrifugal impeller blades based on the pressure ratio.

[0130] ⑧ The centrifugal compressor uses a bladeless diffuser.

[0131] ⑨ Select the process parameters of moving and stationary components reasonably according to design requirements and existing technology.

[0132] Based on the design requirements and the one-dimensional aerodynamic optimization design method for real gas centrifugal compressors proposed in this invention, a one-dimensional design of the supercritical carbon dioxide centrifugal compressor was carried out using the corresponding program package, and the basic design schemes of the centrifugal impeller and the bladeless diffuser were given.

[0133] Impeller inlet blade tip diameter: 42.00 mm

[0134] Impeller inlet hub diameter: 24.00mm

[0135] Impeller outlet diameter: 105mm

[0136] Impeller outlet blade height: 1.571mm

[0137] Impeller inlet blade installation angle: 64.25 degrees

[0138] Impeller outlet blade installation angle: 45.74 degrees

[0139] Number of blades (without splitter blades): 11

[0140] Blade thickness: 1.0mm

[0141] Blade tip clearance height: 0.3mm

[0142] Impeller axial length: 18.90mm

[0143] Diffuser inner diameter ratio: Vaneless

[0144] Diffuser outer diameter ratio: Vaneless

[0145] Number of diffuser blades: Vaneless

[0146] Diffuser outlet width: 3.60mm

[0147] This embodiment uses CFX computational fluid dynamics software to numerically simulate the compressor's operating characteristics at the design speed (40,000 rpm) under rated inlet parameters of 7.8 MPa inlet static pressure and 47°C static temperature. The supercritical carbon dioxide compressor design achieves a total pressure ratio of 1.89 and a corresponding outlet static pressure of 14.40 MPa at the design point, meeting the design requirements. As the mass flow rate of the centrifugal stage increases from the design point towards near-blocking conditions, the compressor's performance curve shows a significant shift. When the mass flow rate exceeds 8.5 kg / s, the rate of decrease in total pressure ratio and outlet pressure rise with decreasing mass flow rate slows considerably.

[0148] Compared to blockage phenomena, the unsteady flows (such as surge, stall, and rotating stall) generated by centrifugal compressors under low-flow conditions are accompanied by stronger unsteady effects, making them difficult to effectively simulate even in ideal gas compressors using steady-state models. Considering the variable thermodynamic properties of supercritical carbon dioxide as the working fluid, which may lead to more complex aerodynamic instabilities, the calculation is very difficult. Therefore, only a low-flow condition (6.0 kg / s) was selected upstream of the design flow rate for calculation. When the mass flow rate is 6.0 kg / s, the partial derivative of the pressure rise curve with respect to the mass flow rate, i.e., the flow coefficient, is negative. Referring to the Dunham estimation criterion for flow instability in centrifugal compressors, it can be concluded that the flow of the supercritical carbon dioxide centrifugal compressor designed in this embodiment is stable under the design point condition and has good aerodynamic stability.

[0149] Currently, due to complex conceptual design and a lack of practical tools, real gas compressors have not yet been widely and universally applied in aerospace, marine propulsion, and process industries, but still possess considerable market potential. This invention provides a one-dimensional aerodynamic optimization design method for real gas centrifugal compressors, which to some extent fills a gap in the field of real gas compressor technology and related engineering methods, and has positive significance for the promotion of real gas compressor technology.

[0150] The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made to the technical solution based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor, characterized in that, Includes the following steps: Step 1: Obtain the optimal loss model for a real gas compressor; The optimal loss model includes incident angle of attack loss, blade load loss, surface friction loss, top clearance undercurrent loss, wake mixing loss, circulating undercurrent loss, disk friction loss, top leakage loss, and diffusion loss; The incident angle of attack loss △ h IN : The blade load loss Δ h BL : The surface friction loss Δ h SF : The top gap undercurrent loss Δ h TC : The wake mixing loss Δ h WM : The circulating submerged flow loss △ h RC : The disc friction loss Δ h DF : The top leakage loss △ h LK : In the formula, Re is the Reynolds number. d h1 The impeller inlet hub diameter is... d t1 The diameter of the impeller inlet blade tip is 1. d 2 represents the impeller outlet diameter. b 2 represents the height of the impeller outlet blades. Z This represents the equivalent number of blades for a centrifugal impeller. β h1 The blade mounting angle at the impeller inlet hub position. β t1 The blade installation angle at the impeller inlet blade tip position. β 2 represents the blade installation angle at the impeller outlet. β f1 The average relative airflow angle at the impeller inlet. α 2 represents the absolute airflow angle at the impeller outlet. W h1 The relative velocity at the impeller inlet hub position is . W t1 The relative velocity at the impeller inlet blade tip position is denoted as . W 2 represents the relative airflow velocity at the impeller outlet. C 1 represents the average absolute velocity at the impeller inlet. C u2 The absolute circumferential velocity at the impeller outlet. U 1 represents the circumferential velocity at the impeller inlet blade tip position. U 2 represents the circumferential velocity at the impeller outlet; Step 2: Obtain the thermophysical property data of the compressor working fluid; Step 3: Perform one-dimensional aerodynamic analysis based on the optimal loss model and thermophysical property data to obtain the performance indicators and working curves of the centrifugal compressor. Determine the design parameters of the moving and stationary components based on the performance indicators and working curves. Step 4: Optimize the design parameters of moving and stationary components using a multi-objective optimization method, and design the centrifugal compressor based on the optimal design parameters of the moving and stationary components.

2. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 1, characterized in that, In step 2, thermal property data of the compressor working fluid are generated based on the fluid thermal property database; The fluid thermophysical property database includes real gas equations of state and experimental databases of real gas thermophysical properties.

3. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 1, characterized in that, In step 3, a one-dimensional aerodynamic analysis is performed using the single-region moving average method, and the design parameters of the moving and stationary components are calculated through inverse problem calculation.

4. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 3, characterized in that, The method for one-dimensional aerodynamic analysis using the single-region moving average method is as follows: S31. Determine the inlet velocity triangle of the centrifugal impeller based on the set geometric parameters of the centrifugal impeller inlet; S32. Assuming the prior efficiency or entropy production of the centrifugal impeller, determine the actual compression power of the centrifugal impeller. S33. Establish a set of nonlinear equations for the conserved quantities at the centrifugal impeller outlet, and solve them to obtain the design parameters and outlet velocity triangle of the centrifugal impeller. S34. Based on the thermodynamic parameters, geometric parameters, inlet velocity triangle, and outlet velocity triangle of the centrifugal impeller, calculate the local energy loss caused by various irreversible processes during the actual compression process of the centrifugal compressor using the optimal loss model, and calculate the posterior efficiency of the centrifugal impeller based on the energy conservation relationship. S35. Determine the difference between the prior efficiency of step S32 and the posterior efficiency of step S34. If the difference is greater than the allowable value, execute step S32 and iterate repeatedly until convergence to obtain the final actual compression power. S36. Based on the principle of conservation of angular momentum and friction loss, calculate the flow loss and isentropic efficiency in the stationary component; S37. Based on the isentropic efficiency of the centrifugal impeller, the final actual compression power, and the flow loss in the stationary components, calculate the performance indicators and operating curves of the centrifugal compressor, and determine the design parameters of the moving and stationary components based on the performance indicators and operating curves.

5. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 4, characterized in that, The method for calculating the posterior efficiency is as follows: In the formula, For internal losses, For parasitic loss.

6. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 1, characterized in that, In step 4, a genetic algorithm is used to optimize the design parameters.

7. The one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor according to claim 5, characterized in that, The optimization method for the design parameters of the moving and stationary components is as follows: S41. Conduct sensitivity analysis on the design parameters to obtain the key design parameters of the centrifugal compressor; S32. Sampling of key design parameters of centrifugal compressor to obtain initial population; S33. Based on the initial population, use an evolutionary algorithm to perform multi-objective collaborative optimization of the geometric parameters of the centrifugal compressor, and obtain the optimized design parameters of the moving and stationary components of the centrifugal compressor.

8. A system for a one-dimensional aerodynamic optimization design method for a real gas centrifugal compressor as described in any one of claims 1-7, characterized in that, include, The loss model module is used to obtain the optimal loss model for a real gas compressor. Thermophysical property data module is used to acquire the thermophysical property data of the compressor working fluid; The dynamic and static parameter module is used to perform one-dimensional aerodynamic analysis based on the optimal loss model and thermophysical property data to obtain the performance indicators and working curves of the centrifugal compressor, and to determine the design parameters of the dynamic and static components based on the performance indicators and working curves. The optimization module is used to optimize the design parameters of moving and stationary components using a multi-objective optimization method, and to design a centrifugal compressor based on the optimal design parameters of moving and stationary components.

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