Evaluation method and device for compressor casing processing stability expansion capability

Abstract

The present invention provides an evaluation method and an evaluation device for the compressor casing processing and stabilization expansion capability, which are applied to the fields of compressors and aerodynamic thermodynamics. The method comprises: for each compressor model, performing RANS numerical simulation on the compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein different compressor models have different casing processing configurations; based on the three-dimensional flow field results, generating a three-dimensional control body according to the compressor model; constructing a momentum balance equation based on the three-dimensional control body, and calculating the axial momentum change of the three-dimensional control body; analyzing multiple axial momentum changes of multiple compressor models to obtain analysis results, wherein the analysis results characterize the stabilization expansion capability of the casing processing configuration.

Description

Technical Field

[0001] The present invention relates to the field of compressors and aerodynamic thermodynamics, and more specifically, to an evaluation method and an evaluation device for the processing and stabilization expansion capability of a compressor casing. Background Art

[0002] With the continuous pursuit of high performance of aircraft engines and gas turbines, the number of compressor stages has been reduced and the load has been increased. At the same time, due to the strong adverse pressure gradient and strong unsteadiness of the compressor, flow instability is very likely to occur, which brings severe challenges to the wide stability margin design. In order to solve the problem of the tip of the compressor blade stalling first, the casing treatment has been favored by researchers and has been widely studied. In terms of the shape of the casing treatment, the axial seam casing treatment has undergone the development of square, semicircular, and semi-heart-shaped, and the stability expansion ability has been significantly improved, and the negative impact on efficiency has gradually decreased. And with the continuous improvement of numerical calculation and computing power, the casing treatment has gradually transitioned from the early "trial and error" design to the quantitative design based on optimization algorithms. In the optimization design, in order to accurately obtain the margin widening amount of the casing treatment configuration, it is usually necessary to calculate the entire characteristic line, and it is necessary to calculate hundreds of different casing treatment configurations to complete one optimization, which consumes a huge amount of computing resources and is difficult to achieve rapid design.

[0003] It can be seen that there is an urgent need to develop a method for evaluating the casing processing and stabilization capability, which can predict the casing processing and stabilization capability through only one calculation and improve the optimization efficiency. Summary of the invention

[0004] In view of this, an embodiment of the present invention provides a method and a device for evaluating the stability expansion capability of a compressor casing.

[0005] One aspect of an embodiment of the present invention provides a method for evaluating the stability expansion capability of a compressor casing, the method comprising:

[0006] For each compressor model, a RANS numerical simulation is performed on the compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein the casing processing configurations of different compressor models are different;

[0007] Based on the above three-dimensional flow field results, a three-dimensional control volume is generated according to the above compressor model;

[0008] Constructing a momentum balance equation based on the three-dimensional control body, and calculating the axial momentum change of the three-dimensional control body;

[0009] The plurality of axial momentum variations of the plurality of compressor models are analyzed to obtain analysis results, wherein the analysis results characterize the stability expansion capability of the casing processing configuration.

[0010] According to an embodiment of the present invention, the compressor model includes a compressor body model and a casing processing model;

[0011] Among them, the RANS numerical simulation is performed on the above compressor model to obtain the three-dimensional flow field results corresponding to the different above compressor models, including:

[0012] Performing modeling processing on the compressor body to obtain the compressor body model;

[0013] The casing is constructed by using a spline curve method to obtain the casing processing model, wherein the spline curve method includes a B-spline or a Bezier curve;

[0014] The above-mentioned body model and the above-mentioned casing processing model are subjected to RANS numerical simulation to obtain the above-mentioned three-dimensional flow field result.

[0015] According to an embodiment of the present invention, a RANS numerical simulation is performed on the above-mentioned body model and the above-mentioned casing processing model to obtain the above-mentioned three-dimensional flow field result, including:

[0016] The airframe model and the casing processing model are processed by using a mesh generation technology, wherein meshes near the wall are encrypted to obtain a compressor calculation model;

[0017] Based on the preset test conditions, the above compressor calculation model is subjected to RANS numerical simulation to obtain the above three-dimensional flow field results.

[0018] According to an embodiment of the present invention, the above-mentioned preset test conditions include setting total temperature and total pressure boundary conditions at the inlet of the above-mentioned compressor calculation model, setting the solid wall as a no-slip boundary condition, the casing processing domain and the compressor domain in the above-mentioned compressor calculation model are connected by a frozen rotor, and setting a flow boundary condition at the outlet of the casing processing domain.

[0019] According to an embodiment of the present invention, the above-mentioned airframe model and the above-mentioned casing processing model are processed by using a mesh generation technology, wherein the mesh near the wall is encrypted to obtain a compressor calculation model, including:

[0020] The above-mentioned airframe model is processed by using mesh generation technology, a butterfly mesh is generated inside the casing processing model, and a HOH mesh is generated inside the blade channel of the above-mentioned airframe model. The meshes near the wall and the blade tip clearance are encrypted to accurately capture the flow field details of the rotor end area, thereby obtaining the above-mentioned compressor calculation model.

[0021] According to an embodiment of the present invention, based on the above three-dimensional flow field results, a three-dimensional control volume is generated according to the above compressor model, including:

[0022] When the above three-dimensional flow field results indicate that the casing processing model in the above compressor model affects the spanwise distribution of aerodynamic parameters in the blade tip area, a three-dimensional control body is generated according to the rotor blade tip area in the above compressor model, wherein the above three-dimensional control body is constructed in the rotor blade tip area, covering the blade tip gap leakage flow, casing processing suction and jet flow influence areas.

[0023] According to an embodiment of the present invention, the above three-dimensional control volume satisfies the following conditions:

[0024] In the radial direction, it covers the area above 80% of the blade height, including the casing wall;

[0025] In the axial direction, it covers the leading edge to the trailing edge of the blade and the upstream to the downstream area of ​​the casing processing;

[0026] In the circumferential direction, it covers the periodic interfaces on both sides.

[0027] According to an embodiment of the present invention, the momentum balance equation is as shown in formula (1):

[0028]

[0029] Among them, V z is the axial speed, V r is the radial velocity, V θ is the circumferential velocity, τ is the shear stress, A z A is the equal axial position surface. r A is a surface of equal radius. θ is the periodic interface, ρ is the fluid density, P is the pressure, ∑Δ(ρV z V r A r )、∑Δ(ρV z V θ A θ ) and ∑Δ(ρV z V z A z ) are all axial momentum changes, ∑Δ(PA z ) is the pressure term, ∑Δ(τ rz A r ),∑Δ(τ θz A θ ) and ∑Δ(τ zz A z ) are all axial shear stress terms.

[0030] According to an embodiment of the present invention, the plurality of axial momentum variations of the plurality of compressor models are analyzed to obtain analysis results, including:

[0031] According to the above-mentioned axial momentum variation and target correlation, radial suction and ejection action parameters of the casing processing configuration are determined;

[0032] According to the radial suction and injection action parameters, a stability expansion capacity coefficient of a compressor model including the casing processing configuration is generated.

[0033] Another aspect of an embodiment of the present invention provides a device for evaluating the compressor casing processing stability expansion capability, the device comprising:

[0034] A simulation module, for performing RANS numerical simulation on each compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein different compressor models have different casing processing configurations;

[0035] A generating module, used for generating a three-dimensional control volume according to the compressor model based on the three-dimensional flow field result;

[0036] A calculation module, used for constructing a momentum balance equation based on the three-dimensional control body and calculating the axial momentum change of the three-dimensional control body;

[0037] The analysis module is used to analyze the multiple axial momentum changes of the multiple compressor models to obtain analysis results, wherein the analysis results represent the stability expansion capability of the casing processing configuration.

[0038] According to an embodiment of the present invention, RANS numerical simulation is performed on compressor models of different casing processing configurations to obtain corresponding three-dimensional flow field results, and a corresponding three-dimensional control body is generated according to the compressor model based on the three-dimensional flow field results. The corresponding momentum balance equation is constructed to calculate the axial momentum change. The stabilization capabilities of different casing processing configurations can be evaluated according to the axial momentum change of different compressor models, thereby improving the optimization efficiency of the casing processing configuration. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The above and other objects, features and advantages of the present invention will become more apparent through the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:

[0040] Figure 1 A flow chart showing a method for evaluating the compressor casing processing stability expansion capability according to an embodiment of the present invention is shown;

[0041] Figure 2 A schematic diagram of the interface between the casing processing configuration and the rotor according to an embodiment of the present invention is shown;

[0042] Figure 3 A schematic diagram of a three-dimensional control volume in a rotor blade tip region according to an embodiment of the present invention is shown;

[0043] Figure 4 A schematic diagram showing the relationship between the axial momentum variation and the stability margin widening amount under different casing processing configurations according to an embodiment of the present invention is shown;

[0044] Figure 5 A structural block diagram of a device for evaluating the compressor casing processing stability expansion capability according to an embodiment of the present invention is shown.

[0045] In the above drawings, the meanings of the reference numerals are as follows:

[0046] 1—rotor; 2—three-dimensional control body; 3—casing handling configuration. DETAILED DESCRIPTION

[0047] Below, embodiments of the present invention will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present invention. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of embodiments of the present invention. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of concepts of the present invention.

[0048] The terms used herein are only for describing specific embodiments and are not intended to limit the present invention. The terms "comprise", "include", etc. used herein indicate the existence of the features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0049] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification, and should not be interpreted in an idealized or overly rigid manner.

[0050] When using expressions such as "at least one of A, B, and C, etc.", they should generally be interpreted according to the meaning of the expression commonly understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0051] Figure 1 A flow chart of a method for evaluating the compressor casing processing stability expansion capability according to an embodiment of the present invention is shown.

[0052] like Figure 1As shown, the method for evaluating the compressor casing processing stability expansion capability may include operations S101 to S104.

[0053] In operation S101, for each compressor model, a RANS numerical simulation is performed on the compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein different compressor models have different casing processing configurations;

[0054] In operation S102, based on the three-dimensional flow field result, a three-dimensional control volume is generated according to the compressor model;

[0055] In operation S103, a momentum balance equation is constructed based on the three-dimensional control body, and an axial momentum change of the three-dimensional control body is calculated;

[0056] In operation S104, multiple axial momentum variations of multiple compressor models are analyzed to obtain analysis results, wherein the analysis results represent the stability expansion capability of the casing processing configuration.

[0057] According to an embodiment of the present invention, the compressor may include but is not limited to a single-stage or multi-stage axial flow compressor, a diagonal flow compressor and a centrifugal compressor, etc., and the casing processing configuration may be semi-heart-shaped, semi-circular, square, etc. The present invention selects a low-speed single-rotor axial flow compressor as the research object, and the design parameters of the compressor are shown in Table 1.

[0058] Table 1 Design parameters of single compressor blade

[0059] parameter Numeric Design speed 2400rpm Design flow 2.9kg / s Number of moving blades 60 Leaf chord length 36.3mm Tip clearance 0.8mm Hub Ratio 0.75

[0060] According to an embodiment of the present invention, numerical simulations are performed on different compressor models under the same flow boundary conditions to obtain three-dimensional flow field results corresponding to different compressor models. Based on the three-dimensional flow results, corresponding three-dimensional control volumes can be constructed according to the corresponding compressor models. For example, the three-dimensional control volume can be divided in the rotor blade tip area. The RANS numerical simulation method refers to the Reynolds-averaged NS equations.

[0061] According to an embodiment of the present invention, after constructing a three-dimensional control body, a corresponding momentum balance equation, namely, an axial momentum balance equation, can be constructed based on the three-dimensional control body to calculate the corresponding axial momentum change, and parameters such as axial shear stress and pressure can also be calculated. The axial momentum change includes the radial change of axial momentum and the axial change of axial momentum.

[0062] According to an embodiment of the present invention, the axial momentum variation of different compressor models is analyzed, and the stability expansion capability of the casing treatment can be evaluated by calculating the axial momentum variation under a fixed flow condition.

[0063] According to an embodiment of the present invention, RANS numerical simulation is performed on compressor models of different casing processing configurations to obtain corresponding three-dimensional flow field results, and a corresponding three-dimensional control body is generated according to the compressor model based on the three-dimensional flow field results. The corresponding momentum balance equation is constructed to calculate the axial momentum change. The stabilization capabilities of different casing processing configurations can be evaluated according to the axial momentum change of different compressor models, thereby improving the optimization efficiency of the casing processing configuration.

[0064] According to an embodiment of the present invention, the compressor model includes a compressor body model and a casing processing model;

[0065] Among them, the RANS numerical simulation of the compressor model is carried out to obtain the three-dimensional flow field results corresponding to different compressor models, including:

[0066] Performing modeling processing on the compressor body to obtain a body model;

[0067] The casing is constructed by using a spline curve method to obtain a casing processing model, wherein the spline curve method includes a B-spline or a Bezier curve;

[0068] The RANS numerical simulation is performed on the airframe model and casing processing model to obtain the three-dimensional flow field results.

[0069] According to an embodiment of the present invention, the compressor model can be drawn using 3D drawing software, wherein the compressor body can be constructed using modeling software in the field of turbomachinery to obtain a body model, and the casing (i.e., casing treatment) is constructed using B-spline or Bezier curves to obtain a casing treatment model. In the modeling process, scripts can be used for automated processing to facilitate rapid adjustment of design parameters such as the shape, position, and opening rate of the casing treatment.

[0070] According to an embodiment of the present invention, a RANS numerical simulation is performed on the body model and the casing processing model to obtain a three-dimensional flow field result, including:

[0071] The airframe model and casing processing model are processed by using mesh generation technology, in which the mesh near the wall is encrypted to obtain the compressor calculation model;

[0072] Based on the preset test conditions, the compressor calculation model is simulated by RANS to obtain the three-dimensional flow field results.

[0073] According to an embodiment of the present invention, a body model and a casing processing model are processed using a mesh generation technology, wherein meshes near the wall are encrypted to obtain a compressor calculation model, including:

[0074] The airframe model is processed using mesh generation technology, a butterfly mesh is generated inside the casing processing model, and an HOH mesh is generated inside the blade channel of the airframe model. The mesh near the wall and the blade tip clearance is encrypted to accurately capture the flow field details of the rotor blade tip area under the casing processing condition, thereby obtaining the compressor calculation model. The mesh generation process can also be automated in the form of scripts.

[0075] According to an embodiment of the present invention, after the model is constructed, a RANS numerical simulation can be performed on it. During the simulation, a fixed preset test condition needs to be used. For example, total temperature and total pressure boundary conditions are set at the inlet of the compressor calculation model, the solid wall is set as a no-slip boundary condition, the casing processing domain and the compressor domain in the compressor calculation model are connected by a frozen rotor, and the flow boundary condition is set at the outlet of the casing processing domain, and the three-dimensional flow field result is solved under the same flow conditions.

[0076] According to an embodiment of the present invention, based on the three-dimensional flow field result, a three-dimensional control volume is generated according to the compressor model, including:

[0077] When the three-dimensional flow field results show that the casing treatment model in the compressor model affects the spanwise distribution of aerodynamic parameters in the blade tip area, a three-dimensional control volume is generated according to the rotor blade tip area in the compressor model, wherein the three-dimensional control volume is constructed in the rotor blade tip area, covering the blade tip gap leakage flow, casing treatment suction and injection flow influence areas.

[0078] According to the embodiment of the present invention, the three-dimensional flow field results show that the applied casing treatment model mainly affects the spanwise distribution of aerodynamic parameters in the blade tip area. In order to accurately characterize the effect of the casing treatment model, the three-dimensional control body should be selected in the rotor blade tip area. For example, the three-dimensional control body covers the area above 80% of the blade height in the radial direction, including the casing wall.

[0079] Figure 2 A schematic diagram of the interface between a casing processing configuration and a rotor according to an embodiment of the present invention is shown.

[0080] Reference Figure 2 The stabilization mechanism of the casing treatment is as follows: the low-energy fluid in the blade channel is sucked into the casing treatment in the downstream area of ​​the casing treatment, and re-injected into the mainstream in the upstream area of ​​the casing treatment, thereby suppressing the development of the tip gap leakage flow and widening the stability margin of the compressor. Specifically, the three-dimensional control body covers the leading edge to the trailing edge of the blade and the upstream to the downstream area of ​​the casing treatment in the axial direction. Specifically, the three-dimensional control body covers the periodic interfaces on both sides in the circumferential direction (see Figure 3 ), wherein the receiver processing configuration includes semi-heart-shaped, semi-circular, square and other forms.

[0081] In a specific embodiment, the three-dimensional control volume satisfies the following conditions:

[0082] In the radial direction, it covers the area above 80% of the blade height, including the casing wall;

[0083] In the axial direction, it covers the leading edge to the trailing edge of the blade and the upstream to the downstream area of ​​the casing processing;

[0084] In the circumferential direction, it covers the periodic interfaces on both sides.

[0085] Figure 3 A schematic diagram of a three-dimensional control volume in a rotor blade tip region according to an embodiment of the present invention is shown.

[0086] According to an embodiment of the present invention, the momentum balance equation is shown in formula (1):

[0087]

[0088] Among them, V z is the axial speed, V r is the radial velocity, V θ is the circumferential velocity, τ is the shear stress, A z A is the equal axial position surface. r A is a surface of equal radius. θ is the periodic interface, ρ is the fluid density, P is the pressure, ∑Δ(ρV z V r A r )、∑Δ(ρV z V θ A θ ) and ∑Δ(ρV z V z A z ) are all axial momentum changes, ∑Δ(PA z ) is the pressure term, ∑Δ(τ rz A r ),∑Δ(τ θz A θ ) and ∑Δ(τ zz A z ) are all axial shear stress terms.

[0089] According to an embodiment of the present invention, formula (1) indicates that the pressure, axial momentum change and shear stress are balanced in the blade end area. Figure 3 As shown, after the casing treatment is applied, there is suction and injection fluid at the interface, which helps to increase the axial momentum change, improve the compressor's ability to resist adverse pressure gradient, and thus widen the compressor's stability margin.

[0090] According to an embodiment of the present invention, multiple axial momentum changes of multiple compressor models are analyzed to obtain analysis results, including:

[0091] According to the axial momentum variation and target correlation, the radial suction and ejection action parameters of the casing processing configuration are determined;

[0092] According to the radial suction parameters and the injection action parameters, the expansion stability coefficient of the compressor model including the casing treatment configuration is generated.

[0093] According to an embodiment of the present invention, the target correlation relationship is that the greater the change in the axial momentum change, the stronger the radial suction and injection effects of the casing processing model, and thus the stronger the stabilization capability of the compressor model.

[0094] According to an embodiment of the present invention, based on the above-mentioned target correlation relationship, the radial suction and injection action parameters of the casing processing configuration can be determined according to the axial momentum change of each compressor model, and then the stabilization capacity coefficient of the compressor model including the casing processing configuration can be generated.

[0095] According to an embodiment of the present invention, affected by periodic boundary conditions, the change of axial momentum along the circumferential direction is 0, so the change of axial momentum after casing treatment mainly includes two parts: radial change of axial momentum and axial change of axial momentum.

[0096] Figure 4 A schematic diagram showing the relationship between the axial momentum change and the stability margin widening amount under different casing processing configurations according to an embodiment of the present invention is shown.

[0097] In a specific embodiment, the present invention selects three different casing processing configurations, and by calculating the entire characteristic line, accurately obtains the stability margin widening amount of each configuration, and at the same time extracts the axial momentum change of the rotor blade tip area under the same flow condition. Figure 4 It can be seen that there is an obvious correlation between the axial momentum change and the stability margin widening amount. The larger the axial momentum change, the larger the stability margin widening amount. Therefore, the stability expansion capability of the casing processing configuration can be evaluated by calculating the axial momentum change under the fixed flow condition. Specifically, the fixed flow condition in the embodiment of the present invention is selected as the design condition.

[0098] According to an embodiment of the present invention, the evaluation method of the present invention quickly evaluates the stability expansion capability of the casing processing by calculating the axial momentum change of the rotor blade top area, which helps to improve the optimization efficiency of the casing processing, shorten the optimization cycle, and has broad application prospects.

[0099] Figure 5 A structural block diagram of a device for evaluating the compressor casing processing stability expansion capability according to an embodiment of the present invention is shown.

[0100] like Figure 5As shown, the compressor casing processing stability expansion capability evaluation device 500 includes a simulation module 510 , a generation module 520 , a calculation module 530 , and an analysis module 540 .

[0101] A simulation module 510 is used to perform RANS numerical simulation on each compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein different compressor models have different casing processing configurations;

[0102] A generating module 520, for generating a three-dimensional control volume according to a compressor model based on the three-dimensional flow field result;

[0103] A calculation module 530 is used to construct a momentum balance equation based on the three-dimensional control body and calculate the axial momentum change of the three-dimensional control body;

[0104] The analysis module 540 is used to analyze multiple axial momentum changes of multiple compressor models to obtain analysis results, wherein the analysis results represent the stability expansion capability of the casing processing configuration.

[0105] According to an embodiment of the present invention, RANS numerical simulation is performed on compressor models of different casing processing configurations to obtain corresponding three-dimensional flow field results, and a corresponding three-dimensional control body is generated according to the compressor model based on the three-dimensional flow field results. The corresponding momentum balance equation is constructed to calculate the axial momentum change. The stabilization capabilities of different casing processing configurations can be evaluated according to the axial momentum change of different compressor models, thereby improving the optimization efficiency of the casing processing configuration.

[0106] According to the embodiments of the present invention, any multiple or at least part of the functions of any multiple of the modules can be implemented in one module. According to the embodiments of the present invention, any one or more of the modules can be split into multiple modules for implementation. According to the embodiments of the present invention, any one or more of the modules can be at least partially implemented as a hardware circuit, such as a field programmable gate array (FPGA), a programmable logic array (PLA), a system on a chip, a system on a substrate, a system on a package, an application specific integrated circuit (ASIC), or can be implemented by hardware or firmware of any other reasonable way of integrating or packaging the circuit, or implemented in any one of the three implementation modes of software, hardware and firmware or in any appropriate combination of any of them. Alternatively, according to the embodiments of the present invention, one or more of the modules can be at least partially implemented as a computer program module, and when the computer program module is run, the corresponding function can be executed.

[0107] For example, any multiple of the simulation module 510, the generation module 520, the calculation module 530, and the analysis module 540 can be combined in one module for implementation, or any one of the modules can be split into multiple modules. Alternatively, at least part of the functions of one or more of these modules can be combined with at least part of the functions of other modules / units / subunits and implemented in one module. According to an embodiment of the present invention, at least one of the simulation module 510, the generation module 520, the calculation module 530, and the analysis module 540 can be at least partially implemented as a hardware circuit, such as a field programmable gate array (FPGA), a programmable logic array (PLA), a system on a chip, a system on a substrate, a system on a package, an application specific integrated circuit (ASIC), or can be implemented by hardware or firmware such as any other reasonable way of integrating or packaging the circuit, or implemented in any one of the three implementation methods of software, hardware, and firmware or in a proper combination of any of them. Alternatively, at least one of the simulation module 510, the generation module 520, the calculation module 530, and the analysis module 540 can be at least partially implemented as a computer program module, and when the computer program module is run, the corresponding function can be executed.

[0108] It should be noted that the evaluation device part of the compressor casing processing stability expansion capability in the embodiment of the present invention corresponds to the evaluation method part of the compressor casing processing stability expansion capability in the embodiment of the present invention. The description of the evaluation device part of the compressor casing processing stability expansion capability specifically refers to the evaluation method part of the compressor casing processing stability expansion capability, which will not be repeated here.

[0109] The embodiments of the present invention are described above. However, these embodiments are only for the purpose of illustration, and are not intended to limit the scope of the present invention. Although each embodiment is described above, it does not mean that the measures in each embodiment cannot be used in combination. The scope of the present invention is defined by the attached claims and their equivalents. Without departing from the scope of the present invention, those skilled in the art may make various substitutions and modifications, which should all fall within the scope of the present invention.

Claims

1. A method for evaluating the compressor casing processing and expansion stability capability, characterized in that: The method comprises: For each compressor model, a RANS numerical simulation is performed on the compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein the casing processing configurations of different compressor models are different; Based on the three-dimensional flow field result, generating a three-dimensional control volume according to the compressor model; Constructing a momentum balance equation based on the three-dimensional control body, and calculating the axial momentum change of the three-dimensional control body; Analyzing a plurality of the axial momentum changes of a plurality of the compressor models to obtain analysis results, wherein the analysis results characterize the stability expansion capability of the casing processing configuration; The momentum balance equation is shown in formula (1), which is applicable to maintaining balance among pressure, axial momentum change and shear stress in the blade end area: (1) in, is the axial speed, is the radial velocity, is the circumferential speed, is the shear stress, is the equiaxial position surface, is a surface of equal radius, is a periodic interface, is the fluid density, P is the pressure, , and are the axial momentum changes, is the pressure term, , and Both are axial shear stress terms.

2. The method according to claim 1, characterized in that The compressor model includes a compressor body model and a casing processing model; The compressor model is subjected to RANS numerical simulation to obtain three-dimensional flow field results corresponding to different compressor models, including: Performing modeling processing on the compressor body to obtain the body model; The casing is constructed by using a spline curve method to obtain the casing processing model, wherein the spline curve method includes a B-spline or a Bezier curve; The RANS numerical simulation is performed on the body model and the casing processing model to obtain the three-dimensional flow field result.

3. The method according to claim 2, characterized in that Performing RANS numerical simulation on the body model and the casing processing model to obtain the three-dimensional flow field result includes: The airframe model and the casing processing model are processed by using a mesh generation technology, wherein meshes near the wall are encrypted to obtain a compressor calculation model; Based on the preset test conditions, the compressor calculation model is subjected to RANS numerical simulation to obtain the three-dimensional flow field result.

4. The method according to claim 3, characterized in that The preset test conditions include setting total temperature and total pressure boundary conditions at the inlet of the compressor calculation model, setting the solid wall as a no-slip boundary condition, the casing processing domain and the compressor domain in the compressor calculation model are connected by a frozen rotor, and setting a flow boundary condition at the outlet of the casing processing domain.

5. The method according to claim 3, characterized in that: The airframe model and the casing processing model are processed by using a grid generation technology, wherein the grid near the wall is encrypted to obtain a compressor calculation model, including: The airframe model is processed using mesh generation technology, a butterfly mesh is generated inside the casing processing model, and an HOH mesh is generated inside the blade channel of the airframe model. The meshes near the wall and the blade tip clearance are encrypted to accurately capture the flow field details of the rotor end area, thereby obtaining the compressor calculation model.

6. The method according to claim 1, characterized in that Based on the three-dimensional flow field result, a three-dimensional control volume is generated according to the compressor model, including: When the three-dimensional flow field results indicate that the casing processing model in the compressor model affects the spanwise distribution of aerodynamic parameters in the blade tip area, a three-dimensional control body is generated according to the rotor blade tip area in the compressor model, wherein the three-dimensional control body is constructed in the rotor blade tip area, covering the blade tip gap leakage flow, casing processing suction and jet flow influence areas.

7. The method according to claim 6, characterized in that The three-dimensional control volume satisfies the following conditions: In the radial direction, it covers the area above 80% of the blade height, including the casing wall; In the axial direction, it covers the leading edge to the trailing edge of the blade and the upstream to the downstream area of ​​the casing processing; In the circumferential direction, it covers the periodic interfaces on both sides.

8. The method according to claim 1, characterized in that Analyzing the multiple axial momentum changes of the multiple compressor models to obtain analysis results, including: Determining radial suction and ejection action parameters of the casing processing configuration according to the axial momentum variation and target correlation; According to the radial suction and injection action parameters, a stability expansion capability coefficient of a compressor model including the casing treatment configuration is generated.

9. A device for evaluating the compressor casing processing and expansion stability capability, characterized in that: The device comprises: A simulation module, for performing RANS numerical simulation on each compressor model to obtain three-dimensional flow field results corresponding to different compressor models, wherein different compressor models have different casing processing configurations; A generating module, configured to generate a three-dimensional control volume according to the compressor model based on the three-dimensional flow field result; A calculation module, used for constructing a momentum balance equation based on the three-dimensional control body and calculating the axial momentum change of the three-dimensional control body; An analysis module, used for analyzing a plurality of the axial momentum changes of a plurality of the compressor models to obtain analysis results, wherein the analysis results represent the stability expansion capability of the casing processing configuration; The momentum balance equation is shown in formula (2), which is applicable to maintaining balance among pressure, axial momentum change and shear stress in the blade end area: (2) in, is the axial speed, is the radial velocity, is the circumferential speed, is the shear stress, is the equiaxial position surface, is a surface of equal radius, is a periodic interface, is the fluid density, P is the pressure, , and are the axial momentum changes, is the pressure term, , and Both are axial shear stress terms.

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