Plane cascade aerodynamic performance determination method, device, storage medium and equipment

Abstract

The present application provides a method, device, storage medium and equipment for determining the aerodynamic performance of a plane, which obtains a preset inlet Mach number of a plane blade cascade and sets an initial value of an outlet back pressure; inputs the preset inlet Mach number into a first function model, references the initial value of the outlet back pressure for iterative calculation, and obtains the outlet back pressure; obtains the actual inlet Mach number of the plane blade cascade according to the outlet back pressure; and obtains the aerodynamic performance of the plane blade cascade according to the actual inlet Mach number. The method automatically adjusts the outlet back pressure to obtain the inlet Mach number by constructing a functional relationship between the outlet back pressure and the preset inlet Mach number. The entire process fully automates the adjustment of the value of the outlet back pressure without human intervention, and can obtain a higher-precision inlet Mach number and a higher-precision total pressure loss of the plane blade cascade with a similar amount of calculation as the traditional method, thereby improving the calculation accuracy of the aerodynamic performance of the plane blade cascade.

Description

Technical Field

[0001] The present invention relates to the technical field of compressors, and in particular to a method, a device, a storage medium and equipment for determining the aerodynamic performance of a plane blade cascade. Background Art

[0002] A compressor is a type of mechanical component that increases air pressure by doing work on the air through high-speed rotating blades. A diffuser is provided at the outlet of the compressor to convert the kinetic energy obtained by the gas in the impeller into pressure to the greatest extent. The compressor is an important component of a gas turbine engine and is used in many industrial fields, especially in aerospace, defense and military fields. The performance of an aircraft engine has a decisive influence on the overall performance of the aircraft, and the compressor, as one of the core components of the engine, determines the performance of the entire aircraft.

[0003] Blades are the main components of compressors and have a vital impact on compressor performance. Plane cascade design method is a common method for compressor blade design. It is a method for designing flow structures based on comprehensive data from plane cascade wind tunnel tests. Therefore, plane cascade design is the basis for compressor blade performance. In recent years, with the rapid development of high-performance computers, computational fluid dynamics (CFD) has been widely used to evaluate and analyze the aerodynamic performance of plane cascades.

[0004] Normally, the aerodynamic performance of a planar cascade is evaluated using the total pressure loss-angle of attack characteristic curve at a specific Mach number. However, unlike the external flow calculation, where the incoming flow Mach number can be directly specified, the internal flow calculation requires adjusting the outlet back pressure to obtain a specific inlet Mach number. In existing CFD calculations, in order to make the inlet Mach number reach a specific value, it is necessary to adjust the input outlet back pressure value multiple times so that the corresponding inlet Mach number reaches the specified value. Generally, four to five back pressure states are selected near the estimated required outlet back pressure, and the back pressure corresponding to the specific inlet Mach number is obtained by reverse interpolation. The above method has low calculation accuracy and requires multiple selections of back pressure states. The calculation accuracy depends on the experience of selecting the back pressure state values, and the calculation accuracy is difficult to control.

[0005] Therefore, how to improve the calculation accuracy of the inlet Mach number and aerodynamic performance of the planar cascade is a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0006] The present invention provides a method for determining the aerodynamic performance of a plane blade cascade, which can automatically adjust the outlet back pressure, so that the inlet Mach number calculation is automated and a higher-precision inlet Mach number is obtained, thereby improving the calculation accuracy of the aerodynamic performance of the plane blade cascade.

[0007] In a first aspect, the present invention provides a method for determining aerodynamic performance of a planar cascade, comprising:

[0008] Get the preset inlet Mach number of the plane cascade and set the initial value of the outlet back pressure;

[0009] The preset inlet Mach number is input into the first function model, the initial value of the outlet back pressure is referenced for iterative calculation, and the outlet back pressure is obtained. The first function model is

[0010]

[0011] Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b ) is the actual inlet Mach number of the plane cascade;

[0012] The actual inlet Mach number of the plane cascade is obtained according to the outlet back pressure;

[0013] The aerodynamic performance of the planar blade cascade is obtained according to the actual inlet Mach number.

[0014] Preferably, the step of inputting the preset inlet Mach number into a first function model, referencing an initial value of the outlet back pressure for iterative calculation, and obtaining the outlet back pressure comprises:

[0015] S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the actual inlet Mach number , given the convergence condition ε, calculate the first function model

[0016] S2: Let n = n + 1, calculate calculate in The update method is as follows:

[0017]

[0018] S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2;

[0019] S4: Calculation convergence, let And output the outlet back pressure p b ;

[0020] Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

[0021] In a second aspect, the present invention provides a device for determining aerodynamic performance of a planar cascade, comprising:

[0022] An input module is used to obtain the preset inlet Mach number of the plane cascade and set the initial value of the outlet back pressure;

[0023] The outlet back pressure acquisition module is used to input the preset inlet Mach number into the first function model, reference the outlet back pressure initial value for iterative calculation, and obtain the outlet back pressure. The first function model is

[0024]

[0025] Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b ) is the actual inlet Mach number of the plane cascade;

[0026] An inlet Mach number acquisition module is used to obtain the actual inlet Mach number of the plane cascade according to the outlet back pressure;

[0027] The aerodynamic performance determination module is used to obtain the aerodynamic performance of the planar blade cascade according to the actual inlet Mach number.

[0028] Preferably, the outlet back pressure acquisition module includes:

[0029] S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the actual inlet Mach number Given the convergence condition ε, calculate the first function model

[0030] S2: Let n = n + 1, calculate calculate in The update method is as follows:

[0031]

[0032] S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2;

[0033] S4: Calculation convergence, let And output the outlet back pressure p b ;

[0034] Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

[0035] In a third aspect, the present invention provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the steps of the method for determining the aerodynamic performance of any planar blade cascade in the first aspect.

[0036] In a fourth aspect, the present invention provides a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method for determining the aerodynamic performance of any planar blade cascade in the first aspect is performed.

[0037] The beneficial effect of adopting the above technical solution is: a method for determining the aerodynamic performance of a plane blade cascade of the present application obtains an outlet back pressure that satisfies the preset inlet Mach number by inputting a preset inlet Mach number into a preset inlet Mach number-outlet back pressure model, inputs the outlet back pressure into the outlet back pressure-inlet Mach number model, obtains the actual inlet Mach number, and obtains the total pressure loss of the plane blade cascade according to the actual inlet Mach number, which is used to evaluate the aerodynamic performance of the plane blade cascade. Compared with the traditional calculation method, the entire process of this method fully automates the adjustment of the value of the outlet back pressure without human intervention, and can obtain a higher-precision inlet Mach number with a similar amount of calculation as the traditional method, thereby obtaining a higher-precision total pressure loss of the plane blade cascade, and improving the calculation accuracy of the aerodynamic performance of the plane blade cascade. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below.

[0039] Figure 1 A schematic diagram of a method for determining the aerodynamic performance of a plane cascade;

[0040] Figure 2 The different attack angle functions f(p) in the embodiment are verified for a method for determining the aerodynamic performance of a plane cascade. b ) Schematic diagram of changes with the number of iteration steps;

[0041] Figure 3 The back pressure p at different attack angles at the outlet of a plane blade cascade aerodynamic performance determination method is verified in the embodiment. b Schematic diagram of changes with the number of iteration steps;

[0042] Figure 4 A schematic diagram of a device for determining the aerodynamic performance of a plane blade cascade. DETAILED DESCRIPTION

[0043] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. In order to explain the present invention in more detail, a method, device, storage medium and equipment for determining the aerodynamic performance of a plane blade cascade provided by the present invention are specifically described below in combination with the drawings.

[0044] The compressor is an important component of the gas turbine engine, which is used in the fields of aerospace, defense and military industry. The performance of the aircraft engine has a decisive influence on the overall performance of the aircraft, and the compressor, as one of the core components of the engine, determines the overall performance of the aircraft. The plane cascade design method is a common method for compressor blade design. It is a method of designing the flow structure based on the comprehensive data of the plane cascade wind tunnel test. Therefore, the plane cascade design is the basis for the performance of the compressor blade.

[0045] The compressor is generally provided with moving blades and stationary blades, and the blade grid channels of the moving blades and stationary blades and the flow of the airflow relative to the moving blades and stationary blades have common characteristics: the airflow decelerates and expands in the channel expanding along the flow direction; the angle of the airflow is deflected from a large angle with the axial direction to a small angle with the axial direction.

[0046] In the optimization design process of compressor blades, a single row of blades can be used to simulate the flow of air in the moving blades or stationary blades in the elementary stage. This simulated blade row unfolded on a plane is the plane blade row of the compressor.

[0047] The cascade experiment is the main method to study the complex flow field structure and loss mechanism inside the cascade and to improve the aerodynamic performance of the cascade. Among them, the plane cascade can conveniently, economically and in detail obtain the isentropic Mach number distribution of the two-dimensional blade surface and the groove, the shock wave position, shape, intensity and various vortex structures in the channel and other basic flow phenomena, which is at the most basic position in gas dynamics.

[0048] Normally, the aerodynamic performance of a plane blade cascade is evaluated using the total pressure loss-angle of attack characteristic curve at a specific Mach number. However, the internal flow calculation of a plane blade cascade requires adjusting the outlet back pressure to obtain a specific inlet Mach number. In existing CFD calculations, in order to make the inlet Mach number reach a specific value, it is necessary to adjust the input outlet back pressure value multiple times so that the corresponding inlet Mach number reaches the specified value. Generally, four to five back pressure states are selected near the estimated required outlet back pressure, and the back pressure corresponding to the specific inlet Mach number is obtained by reverse interpolation. The above method has low calculation accuracy and requires multiple selections of back pressure states. The calculation accuracy depends on the experience of selecting the back pressure state values, and the calculation accuracy is difficult to control.

[0049] The invention discloses a method for determining the aerodynamic performance of a plane blade cascade, which can automatically adjust the outlet back pressure to achieve a preset inlet Mach number, so that the inlet Mach number solution process is automatized and the obtained aerodynamic performance of the plane blade cascade has higher accuracy.

[0050] First, as attached Figure 1 As shown, the present invention provides a method for determining aerodynamic performance of a plane cascade, comprising:

[0051] S11: Obtaining a preset inlet Mach number of the plane cascade and setting an initial value of the outlet back pressure;

[0052] The Mach number is the ratio of speed to the speed of sound. The speed of sound has different values ​​at different altitudes, temperatures, and atmospheric densities. It is a relative value. The Mach number is widely used in aerodynamics, and is generally used for aerospace vehicles such as airplanes and rockets.

[0053] When the Mach number Ma is less than 0.3, the pressure on the fluid is not enough to compress the fluid, which will only cause the fluid to flow. In this case, the density of the fluid will not change with the pressure. This flow field is called subsonic flow, and the flow field can be regarded as an incompressible flow field. General water flow and the flow of air in the atmosphere, such as turbulent rivers, typhoon wind fields and the movement of cars, are all incompressible flow fields. However, when the fluid moves at high speed (the flow velocity is close to or greater than the speed of sound), the density of the fluid will change with the pressure. At this time, the flow of gas is called a compressible flow field. When the Mach number satisfies 0.3≤Ma≤0.8, it is a subsonic compressible flow, when the Mach number satisfies 0.8≤Ma≤1.2, it is a transonic compressible flow, and when the Mach number Ma satisfies 1.2≤Ma≤5, it is a supersonic compressible flow. This kind of situation will only be encountered in aerodynamics. When the Mach number Ma satisfies Ma≥5, it is a hypersonic compressible flow.

[0054] The inlet Mach number is the ratio of the fluid velocity at the inlet of the leading edge of the plane blade cascade in the internal flow field of the compressor to the speed of sound.

[0055] The outlet back pressure is the pressure generated by the irregular movement of air molecules at the outlet of the trailing edge of the plane blade in the internal flow field of the compressor.

[0056] S12: Input the preset inlet Mach number into a first function model, refer to the initial value of the outlet back pressure for iterative calculation, and obtain the outlet back pressure. The first function model is

[0057]

[0058] Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b) is the actual inlet Mach number of the plane cascade;

[0059] S13: obtaining the actual inlet Mach number of the plane blade cascade according to the outlet back pressure;

[0060] S14: Obtaining the aerodynamic performance of the planar blade cascade according to the actual inlet Mach number.

[0061] The aerodynamic performance of the plane blade cascade is evaluated and determined based on a total pressure loss-angle of attack curve, and the total pressure loss-angle of attack curve is calculated based on an inlet Mach number and an outlet back pressure.

[0062] The above-mentioned method for determining the aerodynamic performance of a plane blade cascade converts the problem of adjusting the inlet Mach number by the outlet back pressure into the problem of solving the outlet back pressure value corresponding to the preset inlet Mach number, so that the corresponding outlet back pressure value can be solved according to the preset inlet Mach number, and then the accurate inlet Mach number can be obtained according to the accurate outlet back pressure value, and the total pressure loss of the plane blade cascade is calculated, thereby avoiding the repeated calculation of different outlet back pressure values ​​and their corresponding inlet Mach numbers in the traditional process of determining the aerodynamic performance of the plane blade cascade, and also reducing the problem of relying on experience to set the outlet back pressure value in the process of calculating the inlet Mach number.

[0063] In the above-mentioned method for determining the aerodynamic performance of a planar cascade, preferably, a preset inlet Mach number is input into the first function model, an initial value of the outlet back pressure is referenced for iterative calculation, and the outlet back pressure is obtained, and the iterative calculation can specifically be a secant method.

[0064] For the outlet back pressure obtained according to the first function model, there are four cases of the results of the model:

[0065] (1) There are two solutions. One solution corresponds to the direction of the inlet velocity pointing to the inside of the flow channel, which is the correct solution to the physical problem. The other solution corresponds to the direction of the inlet velocity pointing to the outside of the flow channel. The corresponding physical phenomenon is that the back pressure value is too large and the flow is reversed, which is an incorrect value.

[0066] (2) A solution, corresponding to the inlet velocity direction pointing to the interior of the flow channel, is the correct solution to the physical problem;

[0067] (3) One solution corresponds to the inlet velocity direction pointing to the outside of the flow channel. The corresponding physical phenomenon is that the back pressure value is too large and the flow is reversed;

[0068] (4) There is no solution, and the corresponding physical problem also has no solution.

[0069] Since the specific function form of the first function model is a non-explicit form, the above-mentioned Newton method needs to process a large amount of data and the steps are relatively complicated; when the secant method is used, its convergence speed is faster than that of the Newton method, and approaching the solution through a given initial value is more conducive to the convergence of the iterative process.

[0070] Specifically, the inputting the preset inlet Mach number into the first function model, calculating by using the secant method, and obtaining the outlet back pressure comprises:

[0071] S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the first actual inlet Mach number Initial value of the second actual inlet Mach number Given the convergence condition ε, calculate the first function model

[0072] Among them, the black box function has no explicit expression and the derivative is also unavailable. The corresponding actual inlet Mach number can be output after the black box function operation based on the input outlet back pressure.

[0073] S2: Let n = n + 1, calculate calculate in The update method is as follows:

[0074]

[0075] S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2;

[0076] S4: Calculation convergence, let And output the outlet back pressure p b ;

[0077] Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

[0078] In order to better demonstrate the technical effect that the method for determining the aerodynamic performance of the plane cascade proposed by the present invention has simple steps and obtains the inlet Mach number and the aerodynamic performance of the plane cascade with high accuracy, a verification example is given as follows:

[0079] See attached Figure 2 and attached Figure 3 , a verification example is given for the above-mentioned method for determining the aerodynamic performance of the plane cascade:

[0080] The inlet Mach number is set to 0.7 and the convergence condition is set to ε = 1.0 × 10 -5 , the inlet Mach number at 7 attack angles was calculated (the 7 attack angles were set to 0.0°, 1.0°, 2.0°, 2.5°, 3.0°, 4.0°, and 5.0°), and the function f(p b ) and the independent variable p b The changes are as follows: Figure 2 and attached Figure 3 As shown, attached Figure 2 and attached Figure 3 The number of iteration steps in 0 and 1 are the two initial values ​​of the first step, which is the first step of the iteration; Figure 2 It can be seen that the attack angles of 0.0°, 1.0°, and 4.0° iterate to the 5th step to reach the convergence state, which is equivalent to calculating the flow field 6 times; the attack angles of 2.0° and 2.5° iterate to the 4th step to reach the convergence state, which is equivalent to calculating the flow field 5 times; the attack angle of 3.0° iterates to the 3rd step to reach the convergence state, which is equivalent to calculating the flow field 4 times; the attack angle of 5.0° only iterates to the 2nd step to reach the convergence state, which is equivalent to calculating the flow field 3 times. The average number of flow field calculations in this embodiment is 5 times, which is similar to the number of calculations for manually adjusting the flow field, but its accuracy is very high, and there is no human intervention, which is suitable for the optimization design of planar blades.

[0081] Second, as attached Figure 4 As shown, the present invention provides a device for determining aerodynamic performance of a plane cascade, comprising:

[0082] Input module, used to obtain the preset inlet Mach number of the plane cascade and set the initial value of the outlet back pressure

[0083] The outlet back pressure acquisition module is used to input the preset inlet Mach number into the first function model, reference the outlet back pressure initial value for iterative calculation, and obtain the outlet back pressure. The first function model is

[0084]

[0085] Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b ) is the actual inlet Mach number of the plane cascade;

[0086] An inlet Mach number acquisition module is used to obtain the actual inlet Mach number of the plane cascade according to the outlet back pressure;

[0087] The aerodynamic performance determination module is used to obtain the aerodynamic performance of the planar blade cascade according to the actual inlet Mach number.

[0088] Preferably, the outlet back pressure acquisition module includes:

[0089] S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the actual inlet Mach number Given the convergence condition ε, calculate the first function model

[0090] Among them, the black box function has no explicit expression and the derivative is also unavailable. The corresponding actual inlet Mach number can be output after the black box function operation based on the input outlet back pressure.

[0091] S2: Let n = n + 1, calculate calculate in The update method is as follows:

[0092]

[0093] S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2;

[0094] S4: Calculation convergence, let And output the outlet back pressure p b ;

[0095] Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

[0096] In a third aspect, the present invention provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the steps of the method for determining the aerodynamic performance of any planar blade cascade in the first aspect.

[0097] The computer-readable storage medium may be an electronic memory such as a flash memory, an EEPROM (electrically erasable programmable read-only memory), an EPROM (erasable programmable read-only memory), a hard disk or a ROM. Optionally, the computer-readable storage medium includes a non-transitory computer-readable storage medium. The computer-readable storage medium has storage space for program codes for executing any of the method steps in the above method. These program codes may be read from or written into one or more computer program products, and the program codes may be compressed in an appropriate form.

[0098] In a fourth aspect, the present invention provides a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method for determining the aerodynamic performance of any planar blade cascade in the first aspect is performed.

[0099] The computer device includes a memory, a processor, and one or more computer programs, wherein the one or more computer programs can be stored in the memory and configured to be executed by one or more processors, and the one or more application programs are configured to execute the above-mentioned planar blade cascade aerodynamic performance determination method.

[0100] The processor may include one or more processing cores. The processor uses various interfaces and lines to connect the various parts of the entire computer device, and executes various functions of the computer device and processes data by running or executing instructions, programs, code sets or instruction sets stored in the memory, and calling data stored in the memory. Optionally, the processor can be implemented in at least one hardware form of digital signal processing (DSP), field programmable gate array (FPGA), and programmable logic array (PLA). The processor can integrate one or more combinations of a central processing unit (CPU), a reporting verifier (Graphics Processing Unit, GPU) and a modem. Among them, the CPU mainly processes the operating system, user interface and application programs; the GPU is responsible for rendering and drawing display content; and the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor, but may be implemented separately through a communication chip.

[0101] The memory may include a random access memory (RAM) or a read-only memory (ROM). The memory may be used to store instructions, programs, codes, code sets or instruction sets. The memory may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for implementing at least one function (such as a touch function, a sound playback function, an image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc. The data storage area may also store data created by the terminal device during use, etc.

[0102] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for determining the aerodynamic performance of a plane cascade, characterized in that: include: Get the preset inlet Mach number of the plane cascade and set the initial value of the outlet back pressure; The preset inlet Mach number is input into the first function model, the initial value of the outlet back pressure is referenced for iterative calculation, and the outlet back pressure is obtained. The first function model is Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b ) is the actual inlet Mach number of the plane cascade; Obtaining the actual inlet Mach number of the planar cascade according to the outlet back pressure; The aerodynamic performance of the planar blade cascade is obtained according to the actual inlet Mach number.

2. A method for determining aerodynamic performance of a plane cascade according to claim 1, characterized in that: The step of inputting the preset inlet Mach number into the first function model, referencing the initial value of the outlet back pressure for iterative calculation, and obtaining the outlet back pressure comprises: S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the actual inlet Mach number Given the convergence condition ε, calculate the first function model S2: Let n = n + 1, calculate calculate in The update method is as follows: S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2; S4: Calculation convergence, let And output the outlet back pressure p b ; Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

3. A device for determining the aerodynamic performance of a plane cascade, characterized in that: include: An input module is used to obtain the preset inlet Mach number of the plane cascade and set the initial value of the outlet back pressure; The outlet back pressure acquisition module is used to input the preset inlet Mach number into a first function model, reference the outlet back pressure initial value for iterative calculation, and obtain the outlet back pressure. The first function model is Among them, p b is the outlet back pressure of the plane cascade, Preset inlet Mach number for the flat cascade, g(p b ) is the actual inlet Mach number of the plane cascade; An inlet Mach number acquisition module, used for obtaining the actual inlet Mach number of the plane cascade according to the outlet back pressure; The aerodynamic performance determination module is used to obtain the aerodynamic performance of the planar blade cascade according to the actual inlet Mach number.

4. The device for determining the aerodynamic performance of a plane blade cascade according to claim 3, characterized in that: The outlet back pressure acquisition module includes: S1: Set the outlet back pressure to the initial value Input the black box function to get the initial value of the actual inlet Mach number Given the convergence condition ε, calculate the first function model S2: Let n = n + 1, calculate calculate in The update method is as follows: S3: Determine whether the convergence condition is met If yes, go to step S4, if no, go back to step S2; S4: Calculation convergence, let And output the outlet back pressure p b ; Where n is an integer, f(p b ) is the first function model, p b is the outlet back pressure of the plane blade cascade, and ε is the convergence condition.

5. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method for determining the aerodynamic performance of a planar cascade according to any one of claims 1 to 2 are implemented.

6. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, a method for determining the aerodynamic performance of a planar blade cascade according to any one of claims 1 to 2 is performed.

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