Design Method and Apparatus for Compressor Total Pressure Distortion Simulation Board Based on Eddy Volume Influence

Abstract

This disclosure relates to a design method and apparatus for a compressor total pressure distortion simulation plate based on vorticity influence. The method includes acquiring a target distortion map and determining the contour data corresponding to the low-pressure region from the target distortion map; obtaining a reference distortion map through numerical simulation of the contour data and determining multiple contour lines based on the reference distortion map; constructing corresponding simulation plates based on the multiple contour lines and performing numerical simulations on the multiple simulation plates to obtain multiple distortion maps; determining the similarity between the multiple distortion maps and the target distortion map, and determining the target contour line based on the similarity; determining a first loss based on the distortion map corresponding to the target contour line, and determining a second loss based on the target distortion map; and determining the simulation plate constructed based on the target contour line as the target simulation plate when the first and second losses match. This can improve the accuracy of the distortion map corresponding to the target simulation plate.

Description

Technical Field

[0001] This disclosure relates to the technical field of aero-engines, and in particular to a design method and apparatus for a compressor total pressure distortion simulation board based on vorticity influence. Background Technology

[0002] Currently, the design of simulated plate total voltage distortion generators mainly relies on experience and distortion experiments, often by directly selecting the low total voltage region in the target distortion spectrum as the contour of the simulated plate.

[0003] Existing methods can generate distortion in a specific area of ​​the aerodynamic interface plane (AIP) to a certain extent. However, the distribution and magnitude of the loss in the distortion area often differ significantly from the target distortion pattern, making it difficult to meet the design accuracy requirements. Moreover, the design process requires repeated cycles of experimentation, adjustment, re-experimentation, and re-adjustment, resulting in a long design cycle and high cost for obtaining a simulation board that can generate the target distortion pattern. Summary of the Invention

[0004] In view of this, the present disclosure provides a design method and apparatus for a compressor total pressure distortion simulation plate based on vorticity influence, in order to solve the problems existing in the related art.

[0005] A first aspect of this disclosure provides a design method for a compressor total pressure distortion simulation plate based on vorticity influence. The method includes: acquiring a target distortion map and determining contour data corresponding to a low-pressure region from the target distortion map; performing numerical simulation on the contour data under a preset scenario to obtain a reference distortion map, and determining multiple contour lines based on the reference distortion map; constructing corresponding simulation plates based on the multiple contour lines, and placing the multiple simulation plates under a preset scenario for numerical simulation to obtain distortion maps corresponding to the multiple simulation plates; determining the similarity between the multiple distortion maps and the target distortion map, and determining the contour line corresponding to the distortion map that satisfies a preset threshold as the target contour line based on the similarity; determining a first loss based on the distortion map corresponding to the target contour line, and determining a second loss based on the target distortion map; and determining the simulation plate constructed based on the target contour line as the target simulation plate when the first loss and the second loss match.

[0006] A second aspect of this disclosure provides a design apparatus for a compressor total pressure distortion simulation plate based on vorticity influence, applied to the design method for a compressor total pressure distortion simulation plate based on vorticity influence as described in the first aspect. The apparatus includes: an acquisition module for acquiring a target distortion map and determining contour data corresponding to a low-pressure region from the target distortion map; a simulation module for performing numerical simulation on the contour data under a preset scenario to obtain a reference distortion map and determining multiple contour lines based on the reference distortion map; and a construction module for constructing corresponding simulation plates based on the multiple contour lines, and dividing them into... The system performs numerical simulations on multiple simulation boards in a preset scenario to obtain distortion maps corresponding to the multiple simulation boards. A similarity calculation module is used to determine the similarity between the multiple distortion maps and the target distortion map, and to determine the contour line corresponding to the distortion map that meets the preset threshold from the multiple distortion maps based on the similarity. A determination module is used to determine the first loss based on the distortion map corresponding to the target contour line, and to determine the second loss based on the target distortion map. If the first loss and the second loss match, the simulation board constructed based on the target contour line is determined as the target simulation board.

[0007] The above-mentioned at least one technical solution adopted in the embodiments of this disclosure can achieve the following beneficial effects: acquiring a target distortion map and determining the contour data corresponding to the low-pressure area from the target distortion map; performing numerical simulation on the contour data under a preset scenario to obtain a reference distortion map, and determining multiple contour lines based on the reference distortion map; constructing corresponding simulation boards based on the multiple contour lines respectively, and placing the multiple simulation boards under a preset scenario for numerical simulation to obtain distortion maps corresponding to the multiple simulation boards; determining the similarity between the multiple distortion maps and the target distortion map respectively, and determining the contour line corresponding to the distortion map that meets the preset threshold from the multiple distortion maps based on the similarity as the target contour line; determining a first loss based on the distortion map corresponding to the target contour line, and determining a second loss based on the target distortion map, and determining the simulation board constructed based on the target contour line as the target simulation board when the first loss and the second loss match. Based on this, the target contour line that most closely matches the target distortion spectrum can be determined from multiple contour lines by analyzing the contour and loss of the low-pressure region in the distortion spectrum. Then, a target simulation board can be constructed based on this target contour line. This improves the accuracy of the distortion spectrum corresponding to the target simulation board, shortens the design cycle of the total pressure distortion simulator, increases the design efficiency of the distortion spectrum, and reduces the experimental cost of total pressure distortion simulation. Attached Figure Description

[0008] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0009] Figure 1 A schematic diagram of the analog mesh structure of an analog mesh total voltage distortion generator provided as an exemplary embodiment of this disclosure;

[0010] Figure 2 A schematic diagram of the insert structure of an insert-type total voltage distortion generator provided as an exemplary embodiment of this disclosure;

[0011] Figure 3 A schematic diagram of the simulated plate structure of a simulated plate total voltage distortion generator is provided as an exemplary embodiment of this disclosure;

[0012] Figure 4 A schematic diagram showing the placement of a simulation plate for an air inlet, provided as an exemplary embodiment of this disclosure;

[0013] Figure 5 A schematic diagram of the structure of a numerical simulation model provided for an exemplary embodiment of this disclosure;

[0014] Figure 6 A schematic diagram illustrating the deflection of fluid velocity direction under an adverse pressure gradient, provided as an exemplary embodiment of this disclosure;

[0015] Figure 7 A schematic diagram of the fluid flow direction and pressure gradient distribution at the rear cross section of a plate, provided as an exemplary embodiment of this disclosure;

[0016] Figure 8A A schematic diagram of eddy current distribution generated by a first simulation plate provided as an exemplary embodiment of this disclosure;

[0017] Figure 8B A schematic diagram of eddy current distribution generated by a second type of simulation plate provided as an exemplary embodiment of this disclosure;

[0018] Figure 8C A schematic diagram of eddy current distribution generated by a third type of simulation plate provided as an exemplary embodiment of this disclosure;

[0019] Figure 8D A schematic diagram of the eddy current distribution generated by a fourth type of simulation plate provided as an exemplary embodiment of this disclosure;

[0020] Figure 9A schematic diagram of vorticity distribution at a position 0.5D behind a simulated plate, provided as an exemplary embodiment of this disclosure;

[0021] Figure 10A A schematic diagram of vortex distribution at position 0 behind a first-stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0022] Figure 10B A schematic diagram of vorticity distribution at a position 0.1D behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure;

[0023] Figure 10C A schematic diagram of vortex distribution at a position 0.25D behind a first-stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0024] Figure 10D A schematic diagram of vortex distribution at a position 0.75D behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure;

[0025] Figure 10E A schematic diagram of vorticity distribution at a 1D position behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure;

[0026] Figure 11A A schematic diagram of the surface-total pressure coefficient distribution at position 0 of the first-stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0027] Figure 11B A schematic diagram along the path of the surface relative total pressure coefficient at a position 0.1D behind the first stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0028] Figure 11C A schematic diagram along the path of the surface relative total pressure coefficient at a position 0.25D behind the first stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0029] Figure 11D A schematic diagram along the path of the surface relative total pressure coefficient at a position 0.75D behind the first stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0030] Figure 11E A schematic diagram along the path of the surface relative total pressure coefficient at a position 1D behind the first stage simulation plate, provided as an exemplary embodiment of this disclosure;

[0031] Figure 12A A schematic diagram illustrating the variation along the path of the low-pressure zone at position 1.1D behind the simulated plate under the influence of second-stage mixing, provided as an exemplary embodiment of this disclosure;

[0032] Figure 12BA schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.3D behind the simulated plate under the influence of second-stage mixing, provided as an exemplary embodiment of this disclosure;

[0033] Figure 12C A schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.5D behind the simulated plate under the influence of second-stage mixing, provided as an exemplary embodiment of this disclosure;

[0034] Figure 12D A schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.7D behind the simulated plate under the influence of second-stage mixing, provided as an exemplary embodiment of this disclosure;

[0035] Figure 12E A schematic diagram illustrating the variation of the low-pressure zone at a simulated plate position 2D under the influence of second-stage mixing, provided as an exemplary embodiment of this disclosure;

[0036] Figure 13 A flowchart illustrating a design method for a compressor total pressure distortion simulation board based on vorticity influence, provided as an exemplary embodiment of this disclosure;

[0037] Figure 14 A schematic diagram of the state of a target distortion map provided as an exemplary embodiment of this disclosure;

[0038] Figure 15A A schematic diagram of the shape of a low-pressure region contour in a target distortion map provided as an exemplary embodiment of this disclosure;

[0039] Figure 15B A schematic diagram of a desired vorticity distribution provided for an exemplary embodiment of this disclosure;

[0040] Figure 16A A schematic diagram of the shape of an intermediate simulation plate outline provided for an exemplary embodiment of this disclosure;

[0041] Figure 16B A schematic diagram of the vorticity distribution required for an intermediate simulation plate, provided as an exemplary embodiment of this disclosure;

[0042] Figure 17 A schematic diagram of a reference distortion spectrum obtained by numerical simulation calculation of an intermediate simulation board, provided as an exemplary embodiment of this disclosure;

[0043] Figure 18 A schematic diagram of a low-pressure region contour construction simulation plate based on a reference distortion map provided in an exemplary embodiment of this disclosure;

[0044] Figure 19 A schematic diagram of a surface relative to the total pressure coefficient profile provided for an exemplary embodiment of this disclosure;

[0045] Figure 20 A schematic diagram of a distortion pattern obtained from a final design, provided as an exemplary embodiment of this disclosure;

[0046] Figure 21 A flowchart illustrating a design method for a compressor total pressure distortion simulation board based on vorticity influence, provided as an exemplary embodiment of this disclosure;

[0047] Figure 22 This is a schematic diagram of the design device for a compressor total pressure distortion simulation plate based on vorticity influence, provided as an exemplary embodiment of this disclosure. Detailed Implementation

[0048] Embodiments of this disclosure will now be described in more detail with reference to the accompanying drawings. While some embodiments of this disclosure are shown in the drawings, it should be understood that this disclosure can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of this disclosure. It should be understood that the accompanying drawings and embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of protection of this disclosure.

[0049] It should be understood that the steps described in the method embodiments of this disclosure may be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of this disclosure is not limited in this respect.

[0050] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". Definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc., used in this disclosure are only used to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0051] It should be noted that the terms "a" and "a plurality of" used in this disclosure are illustrative rather than restrictive, and those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0052] The names of messages or information exchanged between multiple devices in the embodiments of this disclosure are for illustrative purposes only and are not intended to limit the scope of such messages or information.

[0053] Currently, with the increase in aircraft speed and altitude, the requirements for aircraft maneuverability are also becoming more stringent. However, when using existing engine models to simulate flight at higher speeds and altitudes, adverse changes in the airflow state within the compressor of the engine model can occur, leading to a sharp deterioration in the inlet flow field. This, in turn, affects the engine model and can cause aircraft malfunctions. Simultaneously, with the continuous increase in compressor load, the compressor becomes increasingly sensitive to inlet distortion, making its aerodynamic stability issues more prominent.

[0054] To address the aforementioned issues, existing technologies allow for compressor stability tests under various operating conditions during the compressor design phase. However, these stability tests require simulating various distortion patterns at the inlet. Analysis of the operating conditions and flight parameters of aero-gas turbine engine compression systems has revealed that total pressure distortion (TPD) is the largest external factor affecting aerodynamic stability. Therefore, the design method for the TPD generator, capable of rapidly and accurately generating TPD patterns, is crucial for engine stability testing.

[0055] Current total voltage distortion generators mainly include plug-in type total voltage distortion generators, analog plate type total voltage distortion generators, and analog mesh type total voltage distortion generators. The following is an introduction to these different types of total voltage distortion generators.

[0056] Figure 1 This is a schematic diagram of the analog mesh structure of an analog mesh total voltage distortion generator provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 1 As shown, the simulated mesh total pressure distortion generator was the earliest technology used for simulating total pressure distortion. It utilizes metal wire meshes of different diameters and porosities to assemble a complete screen, and generates total pressure distortion using the airflow wake behind the screen. Relatedly, Overall developed a program that combines screen cross-sections with different porosities, using isentropic flow area calculations to construct the total pressure distortion profile.

[0057] However, after constructing the initial screen in this way, it can be tested under actual operating conditions, and the resulting profile can be compared with the original desired total pressure field. The screen design, construction, and testing are then repeated until the desired profile is produced within an acceptable error range. This process typically requires 4-6 physical iterations. Relatedly, Keith et al. used an array of individually controllable wedges to form a distortion generator; their analytical model provides a fast and reliable configuration scheme for generating specific distortions. Anthony et al. improved the aerodynamics and flow control characteristics by utilizing a hexagonal element flow control grid composed of airfoil cross-sections, achieving greater design flexibility and accuracy.

[0058] Figure 2 This is a schematic diagram of the insert structure of an insert-type total voltage distortion generator provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 2 As shown, existing technologies for plate-type total pressure distortion generators have mature experience, with numerous experiments conducted using scaled-down simulation plates and the establishment of relevant databases. Li Liang studied a single crescent-shaped plate as the standard plate for evaluating inlet total pressure distortion, finding that the distortion it produces is conservative and stringent. Xia Aiguo et al. experimentally studied a dual-plate distortion generator to increase the distortion simulation range of the plate. Zhu Aidi et al. analyzed the flow field structure and distortion degree after the plate insertion, finding that the numerical simulation results and experimental results at the AIP section showed good agreement in terms of trend, but the accuracy of the distortion spectrum still needs further improvement.

[0059] In related technologies, Ye Wei et al. proposed a semi-empirical design method for designing simulation plates using plate test data. The approximate outline of the simulation plate is initially determined based on the shape of the filling pattern, and then the modification scheme of the simulation plate is determined based on the toroidal distortion intensity of the wind test results. Lu Deyu et al. experimentally studied the design of scaled simulation plates and concluded that the various distortion indices of the large and small models have good correlation. Zhu Aidi tried to use a certain contour line in the total pressure recovery coefficient pattern for the shape design of the simulation plate. The results showed that it could simulate the approximate distribution of high and low pressure areas, but the accuracy of the pattern and distortion index still needs to be improved. Furthermore, it is difficult to find a unified mapping relationship between the cross section calculated by Computational Fluid Dynamics (CFD) and the target distortion pattern.

[0060] As discussed above, due to the limited shape of the plug-in type total voltage distortion generator, the distribution of total voltage loss in the distortion spectrum it generates is difficult to control, and the accuracy of the resulting distortion spectrum cannot be guaranteed. In contrast, the simulated plate type total voltage distortion generator can generate a wider range of distortions and more diverse shapes. Furthermore, its shape, size, and other features can be flexibly adjusted according to the total voltage loss distribution of the target distortion spectrum, thus enabling a more accurate simulation of the target distortion spectrum.

[0061] Figure 3 This is a schematic diagram of the simulated plate structure of a simulated plate total voltage distortion generator provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 3As shown, the current design of simulated plate total pressure distortion generators mainly relies on experience and distortion experiments. Often, the low total pressure region in the target distortion spectrum is directly selected as the outline of the simulation plate. This method can generate distortion at the aerodynamic interface plane (AIP) to a certain extent. However, the distribution and magnitude of the distortion loss in the distortion region often differ significantly from the target distortion spectrum, making it difficult to meet the design accuracy requirements. Moreover, the design process requires repeated cycles of experimentation, adjustment, re-experimentation, and re-adjustment. The design cycle required to obtain a simulation plate that can generate the target distortion spectrum is long and costly.

[0062] Figure 4 This is a schematic diagram illustrating the placement of a simulation plate for an air intake, provided as an exemplary embodiment of this disclosure. Figure 4 As shown, airflow distortion in the intake duct typically has a significant impact on the performance of equipment such as engines. Therefore, the distortion map obtained through the simulation board can quantify the degree of distortion within the intake duct, providing an important basis for evaluating the intake duct's performance. The simulation board 401 is usually placed inside the intake duct 402, and the distortion map obtained through the simulation board can be used to...

[0063] To address the aforementioned issues, this disclosure provides a design method for a compressor total pressure distortion simulation plate based on the influence of vorticity. It primarily focuses on the design of the simulation plate in a simulated plate-type total pressure distortion generator. Specifically, based on the distribution and development pattern of fluid vorticity in the region behind the simulation plate, the shape and profile of the low-pressure area and the magnitude of loss in the low-pressure area can be adjusted, thereby improving the accuracy of the distortion map. Simultaneously, it can shorten the design cycle of the total pressure distortion simulator, improve the design efficiency of the distortion map, and reduce the experimental cost of total pressure distortion simulation.

[0064] Figure 5 This is a schematic diagram of the structure of a numerical simulation model provided as an exemplary embodiment of the present disclosure. For example... Figure 5 As shown, the simulation plate 502 can be placed inside the air intake duct 501, thereby obtaining the distortion pattern in the AIP section 503. Furthermore, considering the advantages of numerical simulation technology—its speed, low cost, and safety—the simulation plate can be designed using numerical simulation methods to simulate the target distortion pattern. In this embodiment, D represents the air intake duct diameter, the AIP section is taken at a position 2D behind the simulation plate, and 8D represents the length of the air intake duct 501, which is eight times the air intake duct diameter.

[0065] In practical applications, due to the obstruction of the fluid by the simulation plate, a backflow zone will form in a certain area downstream of the simulation plate. The backflow fluid in the backflow zone is a fluid with high total pressure and high energy under the traditional definition of total pressure. However, this part of the fluid is very detrimental to the operation of the engine. In order to accurately represent the magnitude of this fluid loss, the concept of "effective total pressure" is used. In the embodiments of this disclosure, it can be specifically represented as follows:

[0066]

[0067] Wherein, EPt represents the effective total pressure at a certain point in this cross section, P is the local static pressure, ρ is the fluid density, u represents the fluid velocity in the horizontal direction, v represents the fluid velocity in the vertical direction, and w represents the fluid velocity in the direction of the main flow. In the embodiments of this disclosure, the effective total pressure defined in this way is used instead of the traditional total pressure.

[0068] To intuitively represent the mapping relationship between the simulation plate and the total pressure loss, this embodiment of the disclosure also introduces a dimensionless parameter "surface relative total pressure coefficient PPT", which can be specifically defined as:

[0069]

[0070] Where EPt represents the effective total pressure at a point on this cross section, Pt max Pt represents the maximum effective total pressure at this cross-section. min This represents the minimum effective total pressure of this cross-section. Furthermore, in the related content following the embodiments of this disclosure, it is specified that the portion with a relative total pressure coefficient less than 0.2 is defined as a low-pressure zone, the portion greater than 0.9 is defined as a high-pressure zone, and the remaining portions are defined as transition zones.

[0071] Regarding the measurement of distortion magnitude, the embodiments disclosed herein use the critical circumferential total pressure distortion index DC(120) from Rolls-Royce:

[0072]

[0073] Where EPt0 is the average effective total pressure of the inlet cross-section flow rate, EPt low P0 is the average effective total pressure of the flow rate in the 120-degree distortion zone at the AIP section, and P0 is the average static pressure at the inlet.

[0074] In practical applications, due to the existence of Kelvin-Helmholtz instability, vorticity is stronger at the boundary between high and low pressure zones, and gradually decreases with mixing along the flow path. Therefore, vorticity has a greater impact on flow and mixing near the simulation plate, while the vorticity and pressure gradient in the flow field continuously decrease as the fluid continues to mix downstream. At this point, the influence of vorticity and pressure gradient on the total pressure loss distribution also gradually decreases. To refine the influencing factors of low-pressure zone changes during flow, this embodiment of the present disclosure divides the study of the influence on the total pressure loss distribution at the AIP section into two stages according to the magnitude of vorticity:

[0075] The first stage is mainly affected by the distribution of total pressure loss due to vorticity and pressure gradient, while vorticity gradually decreases as the process progresses.

[0076] In the second stage, the pressure gradient and vorticity no longer have a significant impact on the flow field. The main factor affecting the total pressure loss distribution in this stage is the mixing between the fluids in the high-pressure zone and the low-pressure zone.

[0077] Based on this, according to the research conclusions of Antoniou et al., the separation of the flow behind the plate begins at the leading edge of the simulated plate and forms a large backflow zone behind the plate. The direction of fluid flow behind the simulated plate is from the low-pressure zone at the bottom to the high-pressure zone.

[0078] Figure 6 This is a schematic diagram illustrating the deflection of fluid velocity direction under an adverse pressure gradient, provided as an exemplary embodiment of this disclosure. Figure 6 As shown, when the fluid flows against the pressure gradient, the velocity component in the pressure gradient direction v2 decreases, which causes the fluid velocity direction v1 to deflect and become v1'.

[0079] Figure 7 This is a schematic diagram illustrating the fluid flow direction and pressure gradient distribution at a simulated cross-section behind a plate, provided as an exemplary embodiment of this disclosure. Figure 7 As shown, the streamlines in the region near the back section of the simulation plate mainly intersect the pressure gradient profile radially. Since the streamlines and the pressure gradient have different angles, the direction of fluid motion will be deflected to different degrees, which manifests as the formation of vortices in the normal section.

[0080] Because the fluid generates vortices during the flow against the pressure gradient, the distribution of the vortices basically coincides with the transition zone with a large pressure gradient, that is, near the boundary between the high-pressure zone and the low-pressure zone. Therefore, in the first process, from the location of the simulation plate to the vicinity of the 1D section, the strong vortex structure will continuously affect the shape change of the low-pressure zone at the boundary of the low-pressure zone.

[0081] Figure 8A A schematic diagram of the eddy current distribution generated by a first simulation plate provided for an exemplary embodiment of this disclosure. Figure 8B A schematic diagram of the eddy current distribution generated by a second simulation plate provided as an exemplary embodiment of this disclosure. Figure 8C A schematic diagram of the eddy current distribution generated by a third simulation plate provided as an exemplary embodiment of this disclosure. Figure 8D A schematic diagram of the eddy current distribution generated by a fourth type of simulated plate provided as an exemplary embodiment of this disclosure. (See diagram below.) Figures 8A to 8D The figure shows the vortex distribution generated at the edges of several simulated plates of different shapes. The fluid flow direction is perpendicular to the paper and inwards; the red portion indicates a clockwise vortex direction, and the blue portion indicates a counter-clockwise vortex direction.

[0082] The embodiments disclosed herein are as follows Figure 8A Taking the simulation plate as an example, we will conduct flow field analysis and explain in detail the impact on the vortex flow field and the changes in the low-pressure area.

[0083] Figure 9 This is a schematic diagram of the vorticity distribution at a position 0.5D behind a simulated plate, provided as an exemplary embodiment of this disclosure. Figure 10A This is a schematic diagram of vortex distribution at position 0 of a first-stage simulation plate, provided as an exemplary embodiment of the present disclosure. Figure 10B This is a schematic diagram of vortex distribution at a position 0.1D behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure. Figure 10C This is a schematic diagram of vortex distribution at a position 0.25D behind a first-stage simulation plate, provided as an exemplary embodiment of this disclosure. Figure 10D This is a schematic diagram of vortex distribution at a position 0.75D behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure. Figure 10E This is a schematic diagram of vortex distribution at a position 1D behind a first-stage simulation board, provided as an exemplary embodiment of this disclosure. Figure 11A This is a schematic diagram showing the distribution of the surface relative total pressure coefficient at position 0 of the first-stage simulation plate, provided as an exemplary embodiment of the present disclosure. Figure 11B This is a schematic diagram of the surface-total pressure coefficient at a position 0.1D behind the first-stage simulation plate, provided as an exemplary embodiment of the present disclosure. Figure 11C This is a schematic diagram of the surface-total pressure coefficient at a position 0.25D behind the first-stage simulation plate, provided as an exemplary embodiment of the present disclosure. Figure 11D This is a schematic diagram of the surface-total pressure coefficient at a position 0.75D behind the first-stage simulation plate, provided as an exemplary embodiment of the present disclosure. Figure 11E This is a schematic diagram of the surface-total pressure coefficient at a position 1D behind the first stage simulation plate, provided as an exemplary embodiment of the present disclosure.

[0084] like Figure 9 , Figures 10A to 10E and Figures 11A to 11EAs shown, during the first stage of development, as the region moves downstream, the location of the boundary between the high-pressure and low-pressure areas changes almost synchronously with the location of the vortex. In other words, the vortex consistently influences the contour changes of the low-pressure area at its boundary. Figure 9 As shown in the figure, there are three pairs of vortices at the edge of the low-pressure area. Figure 9 Taking the vortex in the middle part of the middle section as an example, Figure 9 The fluid flow direction is towards the back of the paper. Based on the right-hand rule, the vortex on the left is a positive vortex, and the one on the right is a negative vortex. The outline of the low-pressure region, located in the middle of this pair of vortices, will expand outward at an accelerated rate due to the vortex's influence. Therefore, after the first stage of vortex influence, the outline of the low-pressure region forms a convex shape in the middle.

[0085] Similarly, for the vortices on both sides of the simulation board, the middle portion of the vortices on both sides will promote the outward expansion of the low-pressure area. Therefore, at the end of the first stage, the affected... Figure 9 The influence of the three groups on the vortex causes the profile of the low-pressure area to change mainly in Figure 10E The shape, which bulges outward in three directions, forms... Figure 11E The distribution cloud map of the relative total pressure coefficient at position 1D.

[0086] Figure 12A This is a schematic diagram illustrating the variation along the path of the low-pressure zone at position 1.1D behind the simulated plate under the influence of a second-stage mixing, provided as an exemplary embodiment of this disclosure. Figure 12B This is a schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.3D behind the simulated plate under the influence of a second-stage mixing, provided as an exemplary embodiment of this disclosure. Figure 12C This is a schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.5D behind the simulated plate under the influence of a second-stage mixing, provided as an exemplary embodiment of this disclosure. Figure 12D This is a schematic diagram illustrating the variation along the path of the low-pressure zone at a position 1.7D behind the simulated plate under the influence of a second-stage mixing, provided as an exemplary embodiment of this disclosure. Figure 12E This is a schematic diagram illustrating the variation along the path of the low-voltage zone at a simulated 2D position behind the plate under the influence of a second-stage mixing, as provided in an exemplary embodiment of this disclosure. Figures 12A-12E As shown, in the second stage, since the vorticity and normal pressure gradient are already very small, they no longer have a significant impact on the shape of the low-pressure zone in the direction perpendicular to the flow. At this time, the main factor affecting the shape change of the low-pressure zone is the mixing effect of the fluids in the high-pressure and low-pressure zones. Mixing makes the total pressure distribution of the fluid at the interface between the high-pressure and low-pressure zones in the flow field more uniform, that is, the originally uneven low-pressure zone contour curve becomes gentler, and at the same time, it reduces the total area of ​​the low-pressure zone.

[0087] In summary, in the flow field behind the simulated plate, the plate obstructs the airflow, creating high-pressure and low-pressure regions. This leads to the formation of vortices under a significant pressure gradient. Due to the influence of these vortices, the low-pressure region near the center of the vortex exhibits an outward expansion. After the first stage, the vortex volume gradually decreases to a lower level. In the second stage, the low-pressure region is mainly affected by the mixing of fluid from the high-pressure region, resulting in a smoother profile and a smaller area of ​​the low-pressure region.

[0088] Based on this, the embodiments of this disclosure can study the shape profile of the low-pressure region and the magnitude of the loss in the low-pressure region based on the flow field laws such as the development and change of vorticity and pressure gradient behind the simulated plate, and then propose an improved method to improve the accuracy of the design distortion pattern.

[0089] Figure 13 This is a schematic flowchart illustrating a design method for a compressor total pressure distortion simulation board based on vorticity effects, provided as an exemplary embodiment of this disclosure. Figure 13 As shown, it specifically includes:

[0090] S1301, acquire the target distortion map, and dimensionlessly convert the data in the target distortion map. Then, extract the contour data of the low-pressure area from the dimensionless data as the contour data of the intermediate simulation board.

[0091] Figure 14 This is a schematic diagram of the state of a target distortion map provided as an exemplary embodiment of the present disclosure. Figure 15A This is a schematic diagram of the shape of the low-pressure region contour of a target distortion map provided as an exemplary embodiment of the present disclosure. Figure 15B This is a schematic diagram illustrating a desired vorticity distribution as provided in an exemplary embodiment of this disclosure. For example... Figure 14 , Figure 15A and Figure 15B As shown, the embodiments of this disclosure can accurately simulate the shape and contour of the low-pressure area in the distortion spectrum.

[0092] Specifically, this can be achieved by analyzing the shape of the low-pressure region in the target distortion pattern, such as... Figure 15A As shown, it can be divided into three parts according to left, center, and right. Figure 15A The image shows that the left and right sides are relatively flat, while the middle section expands outwards compared to the left and right. Therefore, based on the influence of vortex distribution on the low-pressure area, it can be deduced that a strong pair of counter-vortices is needed in the outward expansion of the middle low-pressure area. This pair of counter-vortices should be able to cause the low-pressure area in the middle to expand outwards, thus allowing us to utilize... Figure 15B The simulated plate profile and eddy current distribution are shown.

[0093] like Figure 15BAs shown, the central region of the simulation plate is relatively flat. Because the fluid on the back of the simulation plate flows radially from the low-pressure area to the high-pressure area, and as... Figure 6 The relationship between the fluid velocity direction and the pressure gradient direction is shown. In the middle region of the simulation plate, the airflow on the left will deflect to the left to form a counterclockwise vortex, while the airflow on the right will deflect to the right to form a clockwise vortex. As this pair of vortices develops along the path, the shape of the low-pressure area will expand outward in the middle part to approximate the outline of the low-pressure area in the target distortion pattern.

[0094] The next goal is to achieve, as Figure 15B The simulated plate shape outline shown is extracted, and its outline characteristics are observed. It is also divided into three parts: left, middle, and right. The middle part is relatively straight, while the left and right parts bulge outwards compared to the middle part. To obtain such a shape outline, one can start with the low-pressure area outline in the target distortion map.

[0095] Figure 16A This is a schematic diagram of the shape of an intermediate simulation plate outline provided for an exemplary embodiment of the present disclosure. Figure 16B This is a schematic diagram of the eddy current distribution required for an intermediate simulation plate, provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 16A and Figure 16B As shown, the low-pressure region of the target distortion spectrum can be extracted as the contour of the simulation plate for analysis, such as... Figure 16B As shown, the contours on the left and right sides are relatively straight. When the fluid in the recirculation zone flows through these areas, it forms two sets of opposing vortices under the influence of the normal pressure gradient. In the middle region, the contour expands slightly outward, forming a micro-arc shape. Here, the streamlines are parallel to the pressure gradient direction, and vortices that would otherwise affect the shape and contour of the low-pressure zone are largely absent. Therefore, Figure 16B The simulated plate of this shape can generate a set of opposing vortices in both the left and right regions. The contour of the low-pressure area is formed as required by the stretching of these two sets of opposing vortices. Figure 16A The shape profile, i.e. the desired shape profile.

[0096] Therefore, to obtain the low-pressure region contour of the target distortion map, it is first necessary to obtain... Figure 15B The shape outline shown, and Figure 15B The shape profile shown can be obtained from the low-pressure area shape profile of the target distortion map, and then the profile data of the intermediate simulation board can be determined, that is, the profile shape of the intermediate simulation board can be determined.

[0097] S1302, Numerical analysis is performed on the contour data of the intermediate simulation plate to obtain a reference distortion map.

[0098] Figure 17 This is a schematic diagram of a reference distortion spectrum obtained by numerical simulation calculation of an intermediate simulation board, which is provided as an exemplary embodiment of this disclosure. Figure 18This is a schematic diagram of a low-pressure region contour construction simulation plate based on a reference distortion map, provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 17 and Figure 18 As shown, a contour of a simulation plate can be constructed based on the contour data of the low-pressure area of ​​the target distortion spectrum in step S1301. After numerical simulation of the simulation plate, a reference distortion spectrum can be obtained. Then, a simulation plate constructed based on the low-pressure area shape of the reference distortion spectrum can generate a reference distortion spectrum that is close to the shape of the low-pressure area of ​​the target distortion spectrum.

[0099] In some embodiments, comparing the shape profiles of the reference distortion map and the target distortion map reveals that, by utilizing the influence of vorticity distribution twice, the shape and distribution of the low-pressure region in the designed reference distortion map are basically consistent with the target distortion map. When the shape of the low-pressure region in the constructed reference distortion map is similar to the target distortion map, losses may occur due to decreased control performance or increased errors caused by various factors during the operation of the simulation control board. Therefore, it is necessary to adjust the magnitude of the low-pressure region loss to make it similar to the target distortion map.

[0100] S1303, dimensionless transformation is performed on the data corresponding to the reference distortion map to obtain multiple contour lines;

[0101] Figure 19 This is a schematic diagram of a surface-to-total pressure coefficient profile provided as an exemplary embodiment of this disclosure. (See diagram below.) Figure 19 As shown, the reference distortion spectrum obtained by S1302 can be dimensionless according to the surface relative total pressure coefficient, and the contour line with the surface relative total pressure coefficient in the range of 0.1 to 0.2 can be taken.

[0102] Specifically, the target value range and interval of the contour lines can be determined first. This means selecting contour lines with a relative total pressure coefficient between 0.1 and 0.2. Simultaneously, the data corresponding to the reference distortion map can be dimensionless to determine the distortion value of each image point. Then, interpolation algorithms, such as linear interpolation, bilinear interpolation, or more complex interpolation methods, can be used to interpolate between data points to more accurately determine the location of the contour lines. Finally, starting from an initial point, the path of the contour lines can be gradually traced using the algorithm, resulting in multiple contour lines. Multiple contour lines can then be determined based on these multiple contour lines. It should be understood that the values ​​on the contour lines are equal everywhere.

[0103] Thus, multiple contour lines can be obtained, which are a set of curves with similar shapes but different enclosing areas. Simulation boards constructed using this series of curves as contours have the following characteristics: the shapes and contours of these simulation boards are all similar to... Figure 15BThe simulated plates shown have similar shapes and outlines. The degree to which these simulated plates obstruct airflow varies monotonically with the area of ​​the simulated plate, and the area of ​​the simulated plate varies monotonically with the total pressure coefficient relative to the surface. Therefore, the magnitude of the loss can be controlled by adjusting the area of ​​the simulated plate.

[0104] Because they have similar shapes and outlines, the distribution of vorticity they generate, as well as the distribution and shape of the low-pressure area in the reference distortion map, are basically similar.

[0105] S1304 uses a bisection method to determine the target contour line from multiple contour lines.

[0106] In some embodiments, since the magnitude of the loss increases monotonically with the area of ​​the simulation board, when designing the simulation board, the bisection method can be used to select the contour line within the range of 0.1 to 0.2. This allows for the adjustment of the distortion index, the area of ​​the low-pressure zone, and the average total pressure of the low-pressure zone without changing the shape and contour of the low-pressure zone, making it closer to the target distortion spectrum.

[0107] Specifically, the distortion index, low-pressure area, and average total pressure of the low-pressure area can be continuously adjusted to modify the distortion maps corresponding to different contour lines until a distortion map shows a similarity to the target distortion map that meets a preset threshold. The contour line corresponding to the distortion map whose similarity to the target distortion map meets the preset threshold is then identified as the target contour line. The preset threshold can be 95%, 93%, or 90%, and can be set according to the actual situation.

[0108] S1305, determine the first loss corresponding to the distortion spectrum of the target contour line at the AIP section, and determine the second loss corresponding to the target distortion spectrum at the AIP section. If the first loss and the second loss meet the preset conditions, determine the simulation board corresponding to the target contour line as the target simulation board.

[0109] In some embodiments, if the difference between the first loss and the second loss does not meet the requirements of a preset threshold, the candidate distortion map can be replaced, i.e., the contour line can be reselected. This ensures that the loss magnitude can be adjusted while maintaining the loss distribution and low-pressure area shape contour in the distortion map, and ultimately the target simulation board can be constructed based on the target contour line.

[0110] Figure 20 This is a schematic diagram of a final design-derived distortion pattern provided for an exemplary embodiment of this disclosure. (See diagram below.) Figure 20As shown in the embodiments of this disclosure, the distortion pattern design results are illustrated when the relative total pressure coefficient is selected as 0.10, 0.12, and 0.14. The loss of the total pressure distortion pattern at the AIP section is shown in Table 1. Table 1 shows that for simulation plates constructed with different contour lines, as the area of ​​the simulation plate increases, the distortion index and the area of ​​the low-pressure region increase, while the average total pressure of the section and the average total pressure of the low-pressure region decrease. From the results in the table, the simulation plate constructed with the contour line selected as the relative total pressure coefficient is 0.12 in this embodiment of the disclosure has the closest loss to the target distortion pattern. The final designed distortion pattern is shown in Table 1. Figure 20 As shown.

[0111] Table 1 Comparison of Target Flow Field and Design Flow Field Data

[0112]

[0113] Based on this, the embodiments of this disclosure can adjust the shape and contour of the low-pressure region in the compressor total pressure distortion pattern by analyzing the flow field laws such as the changes in vorticity and pressure gradient behind the simulated plate. By controlling the area of ​​the simulated plate, the magnitude of the total pressure loss in the low-pressure region can be controlled, thereby improving the simulation accuracy of the distortion pattern. This method uses numerical simulation to study the influence of pressure gradient and streamlines on the generation and distribution of vorticity in stages, thus achieving precise control over the shape and contour of the low-pressure region and the magnitude of the loss in the total pressure distortion pattern.

[0114] Specifically, firstly, the embodiments of this disclosure can accurately simulate the shape and contour of the low-pressure region in the target distortion map. The shape of the low-pressure region in the target distortion map can be extracted, and a central simulation plate can be constructed using this shape as the contour. This plate is divided into three parts: left, middle, and right. The left and right sides of the central simulation plate are relatively straight, while the middle part expands outwards compared to the left and right sides. This simulation plate will generate a set of vortex structures in each of the left and right parts, and these two sets of vortices will cause the low-pressure regions in the left and right parts to expand outwards.

[0115] After constructing the intermediate simulation plate, numerical simulation calculations can be performed on it to obtain a reference distortion spectrum. This spectrum can then be dimensionless to obtain a series of isolines representing the relative total pressure coefficient. Next, specific isolines can be selected as contours to construct another simulation plate. This shape generates a set of vortices in the central region, which makes the low-pressure area shape approximate the low-pressure area shape of the target distortion spectrum. Through numerical simulation calculations, a spectrum closely resembling the target distortion spectrum can be obtained. By utilizing the influence of vorticity distribution twice, the shape of the low-pressure area in the designed distortion spectrum is basically consistent with the target distortion spectrum. Once the low-pressure area shape of the constructed distortion spectrum is similar to the target spectrum, the magnitude of the low-pressure area loss needs to be adjusted to closely match the target spectrum.

[0116] Finally, the reference distortion map can be dimensionless based on the surface relative total pressure coefficient. Contour lines with surface relative total pressure coefficients in the range of 0.1-0.2 are selected; these are a set of curves with similar shapes but different enclosed areas. Therefore, this embodiment of the present disclosure can control the magnitude of the loss by selecting contour lines with different values ​​of surface relative total pressure coefficients in the reference map. By constructing a simulation board using contour lines with different values ​​and performing numerical simulation calculations, the final designed loss magnitude and the loss magnitude of the target distortion map can meet the accuracy requirements.

[0117] The design method for a compressor total pressure distortion simulation board based on vorticity influence provided in this disclosure can be executed by a terminal or by a chip applied to the terminal.

[0118] For example, the aforementioned terminals may include one or more of the following: mobile phones, tablets, wearable devices, in-vehicle devices, laptops, ultra-mobile personal computers (UMPCs), netbooks, PDAs (personal digital assistants), and wearable devices based on augmented reality (AR) and / or virtual reality (VR) technologies. They may also include, but are not limited to, remote control devices, wearable devices, streetlights, home appliances, and other smart terminals. This disclosure does not impose specific limitations on these aspects.

[0119] Figure 21 This is a schematic flowchart illustrating a design method for a compressor total pressure distortion simulation board based on vorticity effects, provided as an exemplary embodiment of this disclosure. Figure 21 As shown, it specifically includes:

[0120] S2101, acquire the target distortion map and determine the contour data corresponding to the low-pressure area from the target distortion map.

[0121] Specifically, the low-pressure region of the target distortion map can be extracted as the contour of the simulation plate for analysis, such as... Figure 16B As shown, the contours on the left and right sides are relatively straight. When the fluid in the recirculation zone flows through this area, it forms two sets of opposing vortices under the influence of the normal pressure gradient. The middle region, however, forms a slight arc due to the outward expansion of the contour. Here, the streamlines are parallel to the pressure gradient direction, and vortices that would otherwise affect the shape of the low-pressure zone are not formed. Therefore, Figure 16B The simulated plate of this shape can generate a set of opposing vortices in both the left and right regions. The contour of the low-pressure area is formed as required by the stretching of these two sets of opposing vortices. Figure 16A The shape profile, i.e. the desired shape profile.

[0122] S2102, Perform numerical simulation on the contour data under a preset scenario to obtain a reference distortion map, and determine multiple contour lines based on the reference distortion map.

[0123] In some embodiments, a simulated plate contour can be constructed based on the contour data of the low-pressure region of the target distortion map in step S2101. Under a preset scenario, numerical simulation is performed on the shape of the simulated plate corresponding to this contour, thereby obtaining a reference distortion map. Then, a simulated plate constructed using the low-pressure region shape of the reference distortion map can generate a reference distortion map that closely approximates the shape of the low-pressure region of the target distortion map. It should be understood that the preset scenario can be a simulated flight scenario, allowing for numerical simulation of the fluid dynamics corresponding to the air intake during flight. Through numerical simulation, the contour data can be accurately expressed in the form of a mathematical model. This helps to gain a deeper understanding of the geometric characteristics of the contour, such as length, curvature, and area.

[0124] When multiple contour lines are determined based on the reference distortion map, the reference distortion map can be dimensionless according to the surface relative total pressure coefficient, and the contour lines with the surface relative total pressure coefficient in the range of 0.1 to 0.2 can be selected.

[0125] Specifically, the target value range and interval of the contour lines can be determined first. This means selecting contour lines with a relative total pressure coefficient between 0.1 and 0.2. Simultaneously, the data corresponding to the reference distortion map can be dimensionless to determine the distortion value of each image point. Then, interpolation algorithms, such as linear interpolation, bilinear interpolation, or more complex interpolation methods, can be used to interpolate between data points to more accurately determine the location of the contour lines. Finally, starting from an initial point, the path of the contour lines can be gradually traced using the algorithm, resulting in multiple contour lines. Multiple contour lines can then be determined based on these multiple contour lines. It should be understood that the values ​​on the contour lines are equal everywhere.

[0126] S2103, construct corresponding simulation boards based on multiple contour lines, and place multiple simulation boards in a preset scene for numerical simulation to obtain the distortion spectrum corresponding to multiple simulation boards.

[0127] In some embodiments, multiple contour lines can be used to construct a corresponding simulation board, which is then placed in a preset scene for numerical simulation to obtain the distortion spectrum corresponding to each simulation board. Here, the multiple contour lines are a set of curves with similar shapes but different enclosing areas. The simulation board constructed using this series of curves as contours has the following characteristics:

[0128] The shapes and outlines of these simulation boards are all similar to Figure 15BThe simulated plates shown have similar shapes and contours. The degree to which these contour lines impede airflow varies monotonically with the area of ​​the simulated plate, which in turn varies monotonically with the relative total pressure coefficient. Therefore, the magnitude of the loss can be controlled by adjusting the area of ​​the simulated plate. Furthermore, since the multiple contour lines have similar shapes and contours, the resulting vorticity distribution locations, as well as the distribution and shape of the low-pressure region in the reference distortion map, are basically similar.

[0129] S2104, determine the similarity between multiple distortion maps and the target distortion map, and determine the contour line corresponding to the distortion map that meets the preset threshold from the multiple distortion maps based on the similarity as the target contour line.

[0130] Specifically, data from multiple distortion maps and the target distortion map can be obtained separately, and the similarity between each data point can be determined. The similarity of a distortion map can be determined by the mean of the similarity of each data point in the distortion map. Based on this, the similarity between each distortion map and the target distortion map can be determined separately.

[0131] After determining the similarity between each distortion map and the target distortion map, the contour line corresponding to the distortion map with a similarity that meets a preset threshold can be selected as the target contour line. Alternatively, the contour line corresponding to the distortion map with the highest similarity can be directly selected as the target contour line. Specifically, the preset threshold can be 95%, 93%, or 90%, and can be set according to the actual situation.

[0132] S2105, determine the first loss based on the distortion map corresponding to the target contour line, and determine the second loss based on the target distortion map. If the first loss and the second loss match, determine the simulation board constructed based on the target contour line as the target simulation board.

[0133] In some embodiments, the first loss is the loss of the distortion pattern corresponding to the target contour line at the aerodynamic interface, and the second loss is the loss of the target distortion pattern at the aerodynamic interface. Based on this, when the first loss and the second loss are the same, it can be determined that the first loss and the second loss match; alternatively, the difference between the first loss and the second loss can be directly obtained. When the difference between the first loss and the second loss is less than a preset difference, it can also be considered that the first loss and the second loss match, and the simulation board constructed based on the target contour line is determined to be the target simulation board.

[0134] Based on this, the embodiments of this disclosure can study the flow field laws such as the development and change of vorticity and pressure gradient behind the simulation plate, focusing on the shape profile of the low-pressure area and the magnitude of the loss in the low-pressure area, and thus propose a design method for a compressor total pressure distortion simulation plate based on the influence of vorticity.

[0135] In some embodiments, determining multiple contour lines based on a reference distortion map includes: dimensionlessly transforming the reference distortion map according to the surface relative total pressure coefficient, and determining multiple contour lines with the relative total pressure coefficient within a preset range.

[0136] Specifically, the reference distortion map can be dimensionless according to the surface relative total pressure coefficient, and the contour line with the surface relative total pressure coefficient in the range of 0.1 to 0.2 can be selected.

[0137] In practical applications, the target value range and interval of the contour lines can be determined first. This means selecting contour lines with a relative total pressure coefficient between 0.1 and 0.2. Simultaneously, the data corresponding to the reference distortion map can be dimensionless to determine the distortion value of each image point. Then, interpolation algorithms, such as linear interpolation, bilinear interpolation, or more complex methods, can be used to interpolate between data points to more accurately determine the location of the contour lines. Finally, starting from an initial point, the path of the contour lines can be gradually traced using the algorithm to obtain multiple contour lines. Multiple contour lines can then be determined based on these multiple contour lines. It should be understood that the values ​​on the contour lines are equal everywhere.

[0138] Thus, multiple contour lines can be obtained, which are a set of curves with similar shapes but different enclosing areas. Simulation boards constructed using this series of curves as contours have the following characteristics: the shapes and contours of these simulation boards are all similar to... Figure 15B The simulated plates shown have similar shapes and contours; the degree to which these contours obstruct airflow varies monotonically with the area of ​​the simulated plate, which in turn varies monotonically with the relative total pressure coefficient. Therefore, the magnitude of the loss can be controlled by adjusting the area of ​​the simulated plate. Furthermore, because their shapes and contours are similar, the distribution location of the vorticity they generate, as well as the distribution and shape of the low-pressure region in the reference distortion map, are basically similar.

[0139] In some embodiments, the data in the target distortion map is dimensionless, and then the contour data of the low-pressure area is extracted from the dimensionless data.

[0140] In practical applications, to obtain the low-pressure region profile of the target distortion map, it is first necessary to obtain... Figure 15B The shape outline shown, and Figure 15B The shape profile shown can be obtained from the low-pressure area shape profile of the target distortion map, and then the profile data of the intermediate simulation board can be determined, that is, the profile shape of the intermediate simulation board can be determined.

[0141] In some embodiments, if the first loss and the second loss do not match, the target contour line is re-determined from multiple distortion maps based on similarity.

[0142] Specifically, if the difference between the first loss and the second loss does not meet the preset threshold requirement, the target contour line can be reselected based on the similarity. This ensures that the loss magnitude can be adjusted while maintaining the loss distribution and low-pressure area shape in the distortion map, ultimately allowing the construction of a target simulation board based on the target contour line.

[0143] In summary, the embodiments disclosed herein aim to adjust the shape and profile of the low-pressure region in the compressor total pressure distortion pattern by analyzing the distribution and development patterns of vorticity. By controlling the area of ​​the simulation plate, the magnitude of total pressure loss within the low-pressure region is controlled, thereby improving the simulation accuracy of the distortion pattern. This method can use numerical simulation to study the influence of pressure gradients and streamlines on the generation and distribution of vorticity in stages, thus achieving precise control over the shape and profile of the low-pressure region and the magnitude of pressure loss in the total pressure distortion pattern.

[0144] First, the low-pressure region contour of the target distortion map can be extracted. A simulation board is constructed based on this contour, and numerical simulation calculations are performed to obtain a reference map. Then, the reference map is dimensionless to obtain a series of contour lines relative to the total pressure coefficient. Specific contour lines are selected as the contour to construct another simulation board, and numerical simulation calculations are performed. This yields a total pressure distortion map with a low-pressure region shape and contour similar to the target distortion map. Then, the magnitude of the loss is calculated. Specifically, the magnitude of the loss can be controlled by selecting contour lines with different values ​​of the relative total pressure coefficient from the reference map. Ultimately, this embodiment can accurately simulate the shape and magnitude of the low-pressure region in the target distortion map, reducing the need for repeated experiments during the design process, effectively shortening the design cycle, improving design efficiency, and reducing testing costs. It is suitable for stability testing of aero-engines.

[0145] The foregoing primarily describes the solutions provided by the embodiments of this disclosure from the perspective of the server. It is understood that, in order to implement the above functions, the server includes the corresponding hardware structures and / or software modules for executing each function. Those skilled in the art should readily recognize that, based on the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein, this disclosure can be implemented in hardware or a combination of hardware and computer software. Whether a function is executed in hardware or by computer software driving hardware depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this disclosure.

[0146] This disclosure embodiment can divide the server into functional units according to the above method example. For example, it can divide each function into separate functional modules, or it can integrate two or more functions into one management module. The integrated module can be implemented in hardware or as a software functional module. It should be noted that the module division in this disclosure embodiment is illustrative and only represents one logical functional division. In actual implementation, there may be other division methods.

[0147] By dividing each functional module according to its corresponding function, an exemplary embodiment of this disclosure provides a design apparatus for a compressor total pressure distortion simulation board based on vorticity influence. This design apparatus for a compressor total pressure distortion simulation board based on vorticity influence can be a server or a chip applied to a server. Figure 22 This is a schematic diagram of a design device for a compressor total pressure distortion simulation plate based on vorticity influence, provided as an exemplary embodiment of this disclosure. Figure 22 As shown, the design device 2200 for the compressor total pressure distortion simulation board based on vorticity influence includes:

[0148] The acquisition module 2201 is used to acquire the target distortion map and determine the contour data corresponding to the low-pressure area from the target distortion map;

[0149] The simulation module 2202 is used to perform numerical simulation on the contour data under a preset scenario, obtain a reference distortion map, and determine multiple contour lines based on the reference distortion map.

[0150] The construction module 2203 is used to construct corresponding simulation boards based on multiple contour lines, and to place multiple simulation boards in a preset scene for numerical simulation to obtain the distortion spectrum corresponding to multiple simulation boards.

[0151] The similarity calculation module 2204 is used to determine the similarity between the multiple distorted maps and the target distorted map, and to determine the contour line corresponding to the distorted map that meets the preset threshold from the multiple distorted maps as the target contour line based on the similarity.

[0152] The determination module 2205 is used to determine a first loss based on the distortion map corresponding to the target contour line, and to determine a second loss based on the target distortion map. If the first loss and the second loss match, the simulation board constructed based on the target contour line is determined to be the target simulation board.

[0153] In an alternative embodiment, the simulation module 2202 is further configured to dimensionlessly transform the reference distortion spectrum according to the surface relative total pressure coefficient, and determine multiple contour lines with the surface relative total pressure coefficient within a preset range.

[0154] In one alternative approach, the first loss is the loss of the distortion spectrum corresponding to the target contour at the aerodynamic interface, and the second loss is the loss of the target distortion spectrum at the aerodynamic interface.

[0155] In an alternative approach, the acquisition module 2201 is further configured to perform dimensionless processing on the data in the target distortion map, and then extract the contour data of the low-pressure area from the dimensionless data.

[0156] In one alternative approach, if the first loss and the second loss do not match, the target contour is re-determined from a plurality of said distortion maps based on similarity.

[0157] This disclosure also provides an electronic device, including: at least one processor; a memory for storing at least one processor-executable instruction; wherein the at least one processor is used to execute the instruction to implement the steps of the method disclosed in this disclosure.

[0158] In embodiments of this disclosure, computer program code for performing the operations of this disclosure can be written in one or more programming languages ​​or a combination thereof. These programming languages ​​include, but are not limited to, object-oriented programming languages ​​such as Java, Smalltalk, and C++, as well as conventional procedural programming languages ​​such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network (including a local area network (LAN) or a wide area network (WAN)), or it can be connected to an external computer.

[0159] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0160] The modules, components, or units described in the embodiments of this disclosure can be implemented in software or hardware. The names of the modules, components, or units do not necessarily constitute a limitation on the module, component, or unit itself.

[0161] The functions described above in this document can be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary hardware logic components that can be used include: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), system-on-a-chip (SoCs), complex programmable logic devices (CPLDs), and so on.

[0162] The above description is merely an embodiment of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0163] While specific embodiments of this disclosure have been described in detail by way of example, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of this disclosure. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of this disclosure. The scope of this disclosure is defined by the appended claims.

Claims

1. A design method for a compressor total pressure distortion simulation board based on vorticity influence, characterized in that, include: Obtain the target distortion map and determine the contour data corresponding to the low-pressure area from the target distortion map; Numerical simulation is performed on the contour data under a preset scenario to obtain a reference distortion map, and multiple contour lines are determined based on the reference distortion map. Each simulation board is constructed based on multiple contour lines, and each simulation board is placed in a preset scene for numerical simulation to obtain the distortion spectrum corresponding to the multiple simulation boards. The similarity between the distortion maps corresponding to the multiple simulation plates and the target distortion map is determined respectively, and the contour line corresponding to the distortion map that meets the preset threshold is determined from the multiple distortion maps based on the similarity as the target contour line; A first loss is determined based on the distortion map corresponding to the target contour line, and a second loss is determined based on the target distortion map. If the first loss and the second loss match, the simulation board constructed based on the target contour line is determined as the target simulation board.

2. The method according to claim 1, characterized in that, The determination of multiple contour lines based on the reference distortion map includes: The reference distortion map is dimensionless according to the surface relative total pressure coefficient, and multiple contour lines with the surface relative total pressure coefficient within a preset range are determined.

3. The method according to claim 1, characterized in that, The first loss is the loss of the distortion spectrum corresponding to the target contour at the aerodynamic interface, and the second loss is the loss of the target distortion spectrum at the aerodynamic interface.

4. The method according to claim 1, characterized in that, The method further includes: If the difference between the first loss and the second loss is less than a preset threshold, the first loss and the second loss are determined to be a match.

5. The method according to claim 1, characterized in that, The step of determining the contour data corresponding to the low-pressure area from the target distortion map includes: The data in the target distortion map is dimensionless, and then the contour data of the low-pressure area is extracted from the dimensionless data.

6. The method according to claim 1, characterized in that, The method further includes: If the first loss and the second loss do not match, the target contour line is re-determined from multiple distortion maps based on similarity.

7. A design device for a compressor total pressure distortion simulation board based on vorticity influence, characterized in that, include: The acquisition module is used to acquire the target distortion map and determine the contour data corresponding to the low-pressure area from the target distortion map; The simulation module is used to perform numerical simulation on the contour data under a preset scenario, obtain a reference distortion map, and determine multiple contour lines based on the reference distortion map. The construction module is used to construct corresponding simulation boards based on multiple contour lines, and to place multiple simulation boards in a preset scene for numerical simulation to obtain the distortion spectrum corresponding to multiple simulation boards. The similarity calculation module is used to determine the similarity between the distortion maps corresponding to the multiple simulation plates and the target distortion map, and to determine the contour line corresponding to the distortion map that meets the preset threshold from the multiple distortion maps based on the similarity as the target contour line. The determination module is used to determine a first loss based on the distortion map corresponding to the target contour line, and to determine a second loss based on the target distortion map. If the first loss and the second loss match, the simulation board constructed based on the target contour line is determined as the target simulation board.

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