Simple high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method

Abstract

The application discloses a simple high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method, relates to the field of wind tunnel operation characteristic digital modeling, and comprises the following steps: determining and obtaining a plurality of wind tunnel compressor constant speed total pressure ratio performance curves; increasing a virtual working point to obtain a plurality of virtual constant speed total pressure ratio performance curves; constructing a first parameterization model to obtain parameters in the first parameterization model; obtaining a mapping relationship; constructing a second parameterization model corresponding to a given speed; calculating and obtaining a constant speed total pressure ratio performance curve of a wind tunnel compressor corresponding to the given speed; and calculating and obtaining a total pressure ratio of the wind tunnel compressor corresponding to the equivalent mass flow of the given wind tunnel compressor based on the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed. The method solves the problem that conventional wind tunnel compressor parameterization modeling methods cannot realize simple high-precision wind tunnel compressor variable speed aerodynamic performance digital modeling and depend on massive real aerodynamic performance data.

Description

Technical Field

[0001] This invention relates to the field of digital modeling of wind tunnel operating characteristics, and more specifically, to a simplified, high-precision method for parameterizing the variable-speed aerodynamic performance of a wind tunnel compressor. Background Technology

[0002] Wind tunnels are indispensable ground-based testing facilities supporting the development of aerospace vehicles. Continuous wind tunnels, with their high testing efficiency and excellent flow field quality, better meet the development needs of aerospace vehicles. Ensuring the safe commissioning and operation of wind tunnels is a key technical issue that needs to be focused on and resolved during the commissioning and operation of continuous wind tunnels. On the other hand, shortening the development cycle and reducing development costs, as universal requirements for engineering construction, are also key issues that need to be addressed during the wind tunnel development process.

[0003] Digital modeling of wind tunnel operating characteristics is crucial for quickly and accurately predicting these characteristics, identifying potential safety issues, and developing targeted solutions to ensure safe commissioning and operation. The compressor is a core subsystem of a continuous wind tunnel. Wind tunnel compressors often employ variable speed control strategies to broaden their efficient and stable operating range, achieving full coverage of the wind tunnel's continuous, ultra-wide operating conditions. Therefore, simple, high-precision parametric modeling of the variable-speed total pressure ratio aerodynamic performance of the wind tunnel compressor is the core of digital modeling of wind tunnel operating characteristics.

[0004] Performance evaluation and testing of wind tunnel compressors are factors affecting the development cycle and cost of wind tunnels. Reducing the number of operating points requiring evaluation and testing is an effective way to shorten the development cycle and reduce development costs.

[0005] Limited by the development cost and cycle time of wind tunnel compressors, the total pressure ratio performance of wind tunnel compressors across the entire speed range is often characterized by discrete, finite iso-speed total pressure ratio performance lines. In actual wind tunnel operation, the total pressure ratio performance corresponding to any speed of the wind tunnel compressor is required. Constructing piecewise linear, higher-order (e.g., cubic spline interpolation) mappings between speed and flow rate, and between speed and total pressure ratio, and interpolating to obtain the iso-speed total pressure ratio performance at a given speed is a conventional method for parametric modeling of wind tunnel compressors. However, conventional methods cannot simultaneously meet the requirements of simplicity, high accuracy, and low cost (time and cycle time). On the one hand, if piecewise linear interpolation with low computational complexity is used, a massive number of iso-speed performance curves are needed to achieve high-accuracy interpolation, increasing the development cycle and cost of the wind tunnel compressor; on the other hand, if higher-order interpolation is used, the computational complexity of the interpolation method increases sharply, and the inability to accurately define the boundary conditions of higher-order interpolation methods reduces the interpolation accuracy near the boundary. Summary of the Invention

[0006] The purpose of this invention is to solve the problem that conventional parametric modeling methods for wind tunnel compressors rely on massive amounts of real aerodynamic performance data to achieve simple and high-precision digital modeling of the variable speed aerodynamic performance of wind tunnel compressors, and to shorten the compressor performance evaluation cycle and reduce the compressor development cost.

[0007] To achieve the above-mentioned objectives, this invention provides a simplified and high-precision method for parameterizing the variable-speed aerodynamic performance of a wind tunnel compressor, the method comprising:

[0008] Step 1: Measure and obtain the total pressure ratio performance curves at constant speeds of multiple wind tunnel compressors;

[0009] Step 2: Add a virtual operating point to each measured isostatic total pressure ratio performance curve to obtain multiple virtual isostatic total pressure ratio performance curves;

[0010] Step 3: Construct the first parameterized model, and use the first parameterized model to parametrically reconstruct multiple virtual isostatic total pressure ratio performance curves to obtain the parameters in the first parameterized model;

[0011] Step 4: Construct the mapping relationship between the parameters in the first parameterized model and the virtual operating point parameters corresponding to the measured rotational speed, and the rotational speed of the wind tunnel compressor based on the measured constant rotational speed total pressure ratio performance curve;

[0012] Step 5: Obtain the given speed of the wind tunnel compressor, construct a second parameterized model corresponding to the given speed, obtain the parameter values ​​in the second parameterized model and the virtual operating point parameters corresponding to the given speed based on the mapping relationship; calculate the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed based on the second parameterized model, its parameter values ​​and the virtual operating point parameters corresponding to the given speed.

[0013] Step 6: Obtain the equivalent mass flow rate of the given wind tunnel compressor, and calculate the total pressure ratio of the wind tunnel compressor corresponding to the equivalent mass flow rate of the given wind tunnel compressor based on the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed.

[0014] Steps 1 to 4 obtain similar characteristics of the total pressure ratio performance curves of the wind tunnel compressor at the same speed based on a small amount of real data (obtained through experiments or computational simulations) and transform these similar characteristics into a simple parametric mathematical model. Based on the obtained mathematical model, a relatively accurate mathematical description of the total pressure ratio performance curve at any speed is obtained through step 5. Finally, the total pressure ratio corresponding to a wind tunnel compressor with a given flow rate at any speed is obtained through step 6. This achieves the goal of obtaining the total pressure ratio performance characteristics of the entire speed range based on a small amount of real data, shortening the compressor performance evaluation cycle, and reducing the compressor development cost.

[0015] Preferably, in step 1, the a constant speed total pressure ratio performance curves obtained are: constant speed total pressure ratio performance curve S1, constant speed total pressure ratio performance curve S2, ... and constant speed total pressure ratio performance curve Sa; wherein, constant speed total pressure ratio performance curve S1 corresponds to the lowest operating speed of the wind tunnel compressor, constant speed total pressure ratio performance curve Sa corresponds to the highest operating speed of the wind tunnel compressor, constant speed total pressure ratio performance curves S2 to Sa-1 each correspond to the speeds between the lowest and highest operating speeds of the wind tunnel compressor, and a is an integer greater than 2.

[0016] Preferably, each constant speed total pressure ratio performance curve includes K performance points, among which the K performance points include surge points ( ) and blockage points ( ),in, For surge operation i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For surge operation i The total pressure ratio of the wind tunnel compressor corresponding to the measured rotational speed. For the first time in the blocked working state i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For the first time in the blocked working state i For each measured rotational speed, the total pressure ratio of the wind tunnel compressor is K≥5. i ≤ l , l =a-2.

[0017] Preferably, step 2 specifically includes: adding a virtual operating point to each measured isostatic total pressure ratio performance curve. Multiple virtual constant-speed total pressure ratio performance curves were obtained, and the equivalent mass flow rate of the wind tunnel compressor corresponding to the virtual operating point was... The total pressure ratio of the wind tunnel compressor corresponding to the virtual working point is 1.

[0018] Preferably, the expression for the first parameterized model is:

[0019] ;

[0020] in, This is the first parameter corresponding to the i-th measured rotational speed. This is the second parameter corresponding to the i-th measured rotational speed. For the first i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For the first i The total pressure ratio of the wind tunnel compressor corresponding to the measured rotational speed. The first virtual work point i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed.

[0021] Preferred, The calculation method is as follows:

[0022] ;

[0023] in, To conduct Exponentiation.

[0024] Preferably, the expression for the second parameterized model is:

[0025] ;

[0026] Where the subscript j represents the j-th given rotational speed, For the j-th given rotational speed, the first parameter is... The second parameter corresponds to the j-th given rotational speed. The virtual work point corresponding to the first j The reduced mass flow of the wind tunnel compressor corresponding to a given rotational speed. For the first j The reduced mass flow of the wind tunnel compressor corresponding to a given rotational speed. For the first j The total pressure ratio of the wind tunnel compressor corresponding to a given rotational speed.

[0027] One or more technical solutions provided by this invention have at least the following technical effects or advantages:

[0028] This paper proposes a low-cost, simple, and high-precision parametric modeling method for the variable-speed aerodynamic performance of wind tunnel compressors. This method addresses the problem that conventional wind tunnel compressor parametric modeling methods rely on massive amounts of real aerodynamic performance data to achieve simple, high-precision digital modeling of the variable-speed aerodynamic performance of wind tunnel compressors. It meets the requirements for simple, high-precision, and low-cost digital modeling of wind tunnel operating characteristics, thereby improving the safety of wind tunnel commissioning and operation.

[0029] This invention proposes a unified mathematical model for parameterizing the total pressure ratio performance of wind tunnel compressors at constant speeds. This parametric mathematical model accurately reflects the similar characteristics of the total pressure ratio performance curves of wind tunnel compressors at different constant speeds. Moreover, the parametric mathematical model is simple to calculate. Therefore, based on this parametric mathematical model, the total pressure ratio performance curves of wind tunnel compressors at constant speeds can be reconstructed quickly and with high accuracy.

[0030] This invention proposes to increase virtual working points ( A method for constructing a virtual constant-speed total pressure ratio performance curve is presented. Based on this method, the parameterized mathematical model of the constant-speed total pressure ratio performance curve of a wind tunnel compressor can be simplified to the mathematical model described above.

[0031] This invention proposes a complete, low-cost, simple, and high-precision parametric modeling method for the variable-speed aerodynamic performance of wind tunnel compressors, and provides detailed explanations and constraints on the parametric reconstruction steps, enabling complete parametric modeling of the variable-speed aerodynamic performance of wind tunnel compressors. Attached Figure Description

[0032] The accompanying drawings, which are provided to further illustrate embodiments of the invention and constitute a part of this invention, are not intended to limit the scope of the invention.

[0033] Figure 1 This is a schematic diagram of the total pressure ratio performance of a continuous wind tunnel compressor.

[0034] Figure 2 This is a schematic diagram showing the total pressure ratio error values ​​of the 85% and 95% speed lines reconstructed based on this method;

[0035] Figure 3 A flowchart illustrating a simplified, high-precision method for parameterizing the aerodynamic performance of a wind tunnel compressor at varying speeds. Detailed Implementation

[0036] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, where there is no conflict, the embodiments of the present invention and the features thereof can be combined with each other.

[0037] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and therefore the scope of protection of the invention is not limited to the specific embodiments disclosed below.

[0038] Those skilled in the art should understand that, in the disclosure of this invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limiting this invention.

[0039] It is understood that the term "a" should be understood as "at least one" or "one or more", that is, in one embodiment, the number of an element can be one, while in another embodiment, the number of the element can be multiple, and the term "a" should not be understood as a limitation on the number.

[0040] Example 1;

[0041] Please refer to Figure 3 This invention provides a low-cost, simple, and high-precision parametric modeling method for the variable-speed aerodynamic performance of a wind tunnel compressor. The parametric modeling method includes the following steps:

[0042] (1) Discrete, finite total pressure ratio performance curves at constant speeds across the entire speed range are actually determined using numerical calculation methods (CFD) and / or experimental measurement methods. These multiple total pressure ratio performance curves at constant speeds include the lowest operating speed. and maximum operating speed The corresponding constant speed total pressure ratio performance curve, and the speed corresponding to the minimum and maximum operating speeds. The total pressure ratio performance curve at constant speed is shown. The specific data is determined based on accuracy and cost requirements, generally selecting 1-2 lines. The actual measured constant-speed total pressure ratio performance curves show a uniform speed distribution. Each constant-speed line includes K performance points, including the surge point (…). ) and blockage points ( ), For surge operation i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For surge operation i The total pressure ratio of the wind tunnel compressor corresponding to the measured rotational speed. For the first time in the blocked working state i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For the first time in the blocked working state i For each measured rotational speed, the total pressure ratio of the wind tunnel compressor is K≥5. i ≤ l , l =a-2.

[0043] (2) Unsteady numerical simulation calculations of wind tunnel operating characteristics are performed using digital modeling. Each sub-time step of the unsteady simulation may contain non-physical components. Strictly following the parameterized isostatic total pressure ratio performance curve based on the actual measured operating points may lead to calculation divergence. Therefore, an equivalent mass flow rate is added to the i-th actual measured isostatic total pressure ratio performance curve. The virtual working point with a total pressure ratio of 1 ( The virtual operating point and other operating points on the i-th constant speed total pressure ratio performance curve obtained in step (1) are used to construct a virtual constant speed total pressure ratio performance curve, so as to broaden the constant speed total pressure ratio performance curve and prevent calculation divergence. The specific values ​​are determined using a linear interpolation method. The subscript "virtual" represents a virtual working point. Existing linear interpolation methods can be referenced for the linear interpolation method, and the embodiments of this invention will not elaborate on them.

[0044] (3) The first parameterized model is adopted ( For rotational speeds of The Parametric modeling of the virtual constant speed total pressure ratio performance curves can be performed, and the optimal value can be determined using least quadratic fitting or other optimization algorithms. , The rotational speed of the wind tunnel compressor for which the total pressure ratio performance curve at constant speed has been determined is the speed of the compressor. The calculation expression is as follows .

[0045] (4) Construct rotational speeds separately and , and The mapping relationship between the three parameters. , and If three rotational speed lines are actually measured, a mapping relationship can be constructed using a quadratic function.

[0046] (5) Given rotational speed , Based on the mapping relationship constructed in step (4), determine , and The second parameterized model is constructed by referring to the first parameterized model proposed in step (3): The total pressure ratio performance curve corresponding to a given rotational speed is determined using the second parameterized model.

[0047] (6) Based on the given equivalent mass flow rate, the equivalent mass flow rate is obtained through experimental measurement during actual wind tunnel operation. The given equivalent mass flow rate is calculated based on the total pressure ratio performance curve determined in step (5) for the given rotational speed. Corresponding total pressure ratio .

[0048] Example 2;

[0049] Based on Embodiment 1, Embodiment 2 of the present invention will be described in conjunction with specific data:

[0050] The continuous wind tunnel compressor is a multi-stage axial flow compressor unit with a variable speed operating range of 80%-100% of its maximum operating speed. Based on this invention, the aerodynamic performance of the wind tunnel compressor with variable speed and total pressure ratio is parametrically modeled. The specific implementation steps are as follows:

[0051] (1) The total pressure ratio performance characteristics of the wind tunnel compressor at 80%, 85%, 90%, 95% and 100% of its maximum speed were actually measured, see [reference]. Figure 1 Based on actual test conditions, the number of operating points measured on each constant speed line is ≥5, including clogging and surge operating points. The measured total pressure ratio performance curve of the wind tunnel compressor at varying speeds is shown below. Figure 1 .

[0052] (2) The aerodynamic characteristics of the total pressure ratio at constant speeds corresponding to 80%, 90%, and 100% of the highest operating speeds were selected as inputs for parametric modeling, see [reference]. Figure 1 To determine the three types of parameters that need to be determined during the parametric modeling process: , , and mapping relationships: , , The aerodynamic performance of the total pressure ratio at constant speeds of 85% and 95% was selected as test data to verify the accuracy of the parametric modeling method provided by this invention.

[0053] (3) Based on the clogging operating point and the parameters of the adjacent operating points on each constant speed line, the parameters corresponding to the virtual operating point are obtained by linear interpolation. The operating points corresponding to the 80%, 90%, and 100% constant speed lines are (0.0034, 1), (0.0040, 1), and (0.0043, 1), respectively. Based on the measured and virtual operating points of each constant speed line, a virtual constant speed total pressure ratio performance curve is constructed.

[0054] (4) Based on The virtual isostatic total pressure ratio performance curves are parametrically reconstructed to obtain the total pressure ratio performance curves corresponding to the 80%, 90%, and 100% isostatic speed lines. The values ​​are: 6.13, 5.38, and 4.47. The values ​​are 47.02, 143.10, and 245.85 respectively;

[0055] (5) Based on the parameters obtained in steps (3) and (4), construct the rotational speed respectively. and , and The mapping relationship between the three parameters. Since there are three actual measured isostatic total pressure ratio performance curves used for parameter reconstruction in this implementation case, a quadratic function is used to construct the mapping relationship. The obtained mapping relationship is shown in equations (1) to (3):

[0056] (1)

[0057] (2)

[0058] (3)

[0059] (6) Based on the mapping relationship obtained in step (5), calculate the total pressure ratio parameter model of the constant speed corresponding to 85% speed and 95% speed, as shown in equation (4) and equation (5) respectively.

[0060] (4)

[0061] (5)

[0062] A comparison of the total pressure ratio aerodynamic performance obtained according to the above specific implementation steps with the measured total pressure ratio aerodynamic performance at 85% and 95% speeds of a certain continuous wind tunnel compressor is shown below. Figure 1 As shown. Based on the specific steps described above, the predicted total pressure ratio on the 85% and 95% constant speed lines agrees well with the measured values, with a maximum error of 3.12%. (See attached image.) Figure 2 .

[0063] Example 3;

[0064] Based on Embodiment 1, Embodiment 3 of the present invention provides a system for obtaining aerodynamic performance parameters of a wind tunnel compressor, the system comprising:

[0065] The measurement unit is used to measure and obtain the total pressure ratio performance curves of multiple wind tunnel compressors at constant speeds.

[0066] The virtual operating point addition unit is used to add a virtual operating point to each measured isostatic total pressure ratio performance curve to obtain multiple virtual isostatic total pressure ratio performance curves.

[0067] The first parameterized model construction unit is used to construct the first parameterized model and to parametrically reconstruct multiple virtual isostatic total pressure ratio performance curves using the first parameterized model to obtain the parameters in the first parameterized model.

[0068] The mapping relationship acquisition unit is used to construct the mapping relationship between the parameters in the first parameterized model and the virtual operating point parameters corresponding to the measured rotational speed and the rotational speed of the wind tunnel compressor with the measured constant rotational speed total pressure ratio performance curve;

[0069] A given speed acquisition unit is used to obtain the given speed of the wind tunnel compressor, construct a second parameterized model corresponding to the given speed, obtain the parameter values ​​in the second parameterized model and the virtual operating point parameters corresponding to the given speed based on the mapping relationship, and calculate the iso-speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed based on the second parameterized model, its parameter values ​​and the virtual operating point parameters corresponding to the given speed.

[0070] The total pressure ratio acquisition unit is used to obtain the equivalent mass flow rate of a given wind tunnel compressor and calculate the total pressure ratio of the wind tunnel compressor corresponding to the equivalent mass flow rate of the given wind tunnel compressor based on the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed.

[0071] The system may also include an input unit for inputting data, such as a keyboard or other input devices, and a display unit for displaying data, such as a monitor.

[0072] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0073] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A simplified, high-precision parameterized modeling method for the variable-speed aerodynamic performance of a wind tunnel compressor, characterized in that... The method includes: Step 1: Measure and obtain the total pressure ratio performance curves at constant speeds of multiple wind tunnel compressors; Step 2: Add a virtual operating point to each measured isostatic total pressure ratio performance curve to obtain multiple virtual isostatic total pressure ratio performance curves; Step 3: Construct the first parameterized model, and use the first parameterized model to parametrically reconstruct multiple virtual isostatic total pressure ratio performance curves to obtain the parameters in the first parameterized model; Step 4: Construct the mapping relationship between the parameters in the first parameterized model and the virtual operating point parameters corresponding to the measured rotational speed, and the rotational speed of the wind tunnel compressor based on the measured constant rotational speed total pressure ratio performance curve; Step 5: Obtain the given speed of the wind tunnel compressor, construct a second parameterized model corresponding to the given speed, obtain the parameter values ​​in the second parameterized model and the virtual operating point parameters corresponding to the given speed based on the mapping relationship; calculate the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed based on the second parameterized model, its parameter values ​​and the virtual operating point parameters corresponding to the given speed. Step 6: Obtain the equivalent mass flow rate of the given wind tunnel compressor, and calculate the total pressure ratio of the wind tunnel compressor corresponding to the equivalent mass flow rate of the given wind tunnel compressor based on the constant speed total pressure ratio performance curve of the wind tunnel compressor corresponding to the given speed. Step 2 specifically includes: adding a virtual operating point to each measured isostatic total pressure ratio performance curve. Multiple virtual constant-speed total pressure ratio performance curves were obtained, and the equivalent mass flow rate of the wind tunnel compressor corresponding to the virtual operating point was... The total pressure ratio of the wind tunnel compressor corresponding to the virtual working point is 1; The expression for the first parameterized model is: ； in, This is the first parameter corresponding to the i-th measured rotational speed. This is the second parameter corresponding to the i-th measured rotational speed. For the first i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For the first i The total pressure ratio of the wind tunnel compressor corresponding to the measured rotational speed. The first virtual work point i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed.

2. The simplified high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method according to claim 1, characterized in that, Step 1 measures and obtains a total pressure ratio performance curves at constant speeds, namely: total pressure ratio performance curve S1, total pressure ratio performance curve S2, ... and total pressure ratio performance curve Sa; wherein, total pressure ratio performance curve S1 corresponds to the lowest operating speed of the wind tunnel compressor, total pressure ratio performance curve Sa corresponds to the highest operating speed of the wind tunnel compressor, and total pressure ratio performance curves S2 to Sa-1 correspond to the speeds between the lowest and highest operating speeds of the wind tunnel compressor, respectively, and a is an integer greater than 2.

3. The simplified high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method according to claim 2, characterized in that, Each constant speed total pressure ratio performance curve includes K performance points, among which the surge point is included. ) and blockage points ( ),in, For surge operation i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For surge operation i The total pressure ratio of the wind tunnel compressor corresponding to the measured rotational speed. For the first time in the blocked working state i The reduced mass flow of the wind tunnel compressor corresponding to a measured rotational speed. For the first time in the blocked working state i For each measured rotational speed, the total pressure ratio of the wind tunnel compressor is K≥5. i ≤ l , l =a-2.

4. The simplified high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method according to claim 1, characterized in that, The calculation method is as follows: ； in, To conduct Exponentiation.

5. The simplified high-precision wind tunnel compressor variable speed aerodynamic performance parameterization modeling method according to claim 1, characterized in that, The expression for the second parameterized model is: ； Where the subscript j represents the j-th given rotational speed, For the j-th given rotational speed, the first parameter is... The second parameter corresponds to the j-th given rotational speed. The virtual work point corresponding to the first j The reduced mass flow of the wind tunnel compressor corresponding to a given rotational speed. For the first j The reduced mass flow of the wind tunnel compressor corresponding to a given rotational speed. For the first j The total pressure ratio of the wind tunnel compressor corresponding to a given rotational speed.

Images