Method and device for designing total pressure distortion analog board of gas compressor based on vorticity influence

Abstract

The invention relates to a method and a device for designing a total pressure distortion simulation board of a gas compressor based on vorticity influence. Comprising the following steps: acquiring a target distortion map, and determining contour data corresponding to a low-voltage region from the target distortion map; performing numerical simulation on the contour data to obtain a reference distortion map, and determining a plurality of contour lines based on the reference distortion map; respectively constructing corresponding analog boards based on the plurality of contour lines, and respectively carrying out numerical simulation on the plurality of analog boards to obtain a plurality of distortion maps; determining similarities between the plurality of distortion maps and a target distortion map, and determining a target contour line according to the similarities; and determining a first loss according to the distortion atlas corresponding to the target contour line, determining a second loss according to the target distortion atlas, and determining the analog board constructed based on the target contour line as a target analog board under the condition that the first loss is matched with the second loss. Therefore, the accuracy of the distortion atlas corresponding to the target analog board can be improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aeroengines, and in particular to a design method and device for a compressor total pressure distortion simulation board based on vortex influence. Background Art

[0002] At present, the design of simulated plate total pressure distortion generator mainly relies on experience and distortion tests, often by directly selecting the low total pressure area in the target distortion spectrum as the contour of the simulated plate.

[0003] The methods in the prior art can produce distortion in a specific area of ​​the aerodynamic interface (AIP) to a certain extent. However, the distribution and size of the loss in the distortion zone are often quite different from the target distortion spectrum, resulting in difficulty in meeting the design accuracy requirements. In addition, the design process requires repeated cycles of testing-adjustment-retesting-readjustment, and ultimately the design cycle required to obtain a simulation board that can produce the target distortion spectrum is long and costly. Summary of the invention

[0004] In view of this, an embodiment of the present disclosure provides a design method and device for a compressor total pressure distortion simulation board based on vortex influence to solve the problems existing in the related art.

[0005] According to a first aspect of an embodiment of the present disclosure, there is provided a method for designing a compressor total pressure distortion simulation board based on vortex influence, the method comprising: obtaining a target distortion spectrum, and determining contour data corresponding to a low-pressure area from the target distortion spectrum; numerically simulating the contour data under a preset scenario to obtain a reference distortion spectrum, and determining a plurality of contour lines based on the reference distortion spectrum; constructing corresponding simulation boards based on a plurality of contour lines respectively, and placing a plurality of simulation boards under a preset scenario for numerical simulation respectively, to obtain distortion spectra corresponding to a plurality of simulation boards; determining the similarity between a plurality of distortion spectra and a target distortion spectrum respectively, and determining a contour line corresponding to a distortion spectrum that meets a preset threshold from a plurality of distortion spectra based on the similarity as a target contour line; determining a first loss based on the distortion spectrum corresponding to the target contour line, and determining a second loss based on the target distortion spectrum, and determining a simulation board constructed based on the target contour line as a target simulation board when the first loss and the second loss match.

[0006] According to a second aspect of the disclosed embodiment, there is provided a design device for a compressor total pressure distortion simulation board based on vortex influence, which is applied to the design method for a compressor total pressure distortion simulation board based on vortex influence as in the first aspect, and the device comprises: an acquisition module for acquiring a target distortion map and determining contour data corresponding to a low-pressure area from the target distortion map; a simulation module for numerically simulating the contour data under a preset scenario, obtaining a reference distortion map, and determining a plurality of contour lines based on the reference distortion map; a construction module for constructing corresponding simulation boards based on a plurality of contour lines, and determining the contour data corresponding to the low-pressure area from the target distortion map; and a construction module for constructing corresponding simulation boards based on a plurality of contour lines respectively. Placing multiple simulation boards in preset scenarios for numerical simulation to obtain distortion maps corresponding to the multiple simulation boards; a similarity calculation module is used to respectively determine the similarities between the multiple distortion maps and the target distortion map, and determine the contour line corresponding to the distortion map that meets a preset threshold from the multiple distortion maps according to the similarity as the target contour line; a determination module is used to determine a first loss according to the distortion map corresponding to the target contour line, and determine a second loss according to the target distortion map, and when the first loss and the second loss match, determine that the simulation board constructed based on the target contour line is the target simulation board.

[0007] According to a third aspect of an embodiment of the present disclosure, a computer device is provided, including a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the above-mentioned method for designing a compressor total pressure distortion simulation board based on vortex influence.

[0008] In a fourth aspect of an embodiment of the present disclosure, a computer-readable storage medium is provided, on which a computer program / instruction is stored, and when the computer program / instruction is executed by a processor, the steps of the method for designing a compressor total pressure distortion simulation board based on vortex influence are implemented.

[0009] According to a fifth aspect of the present disclosure, a computer program product is provided, which, when executed by a processor, implements the steps of the above-mentioned method for designing a compressor total pressure distortion simulation board based on vortex influence.

[0010] The above-mentioned at least one technical scheme adopted in the embodiments of the present disclosure can achieve the following beneficial effects: obtaining a target distortion map, and determining 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 a plurality of contour lines based on the reference distortion map; constructing corresponding simulation boards based on a plurality of contour lines respectively, and placing a plurality of simulation boards under a preset scenario for numerical simulation respectively, to obtain distortion maps corresponding to a plurality of simulation boards; determining the similarity between a plurality of distortion maps and a target distortion map respectively, and determining the contour line corresponding to the distortion map that meets a preset threshold from a plurality of 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 when the first loss and the second loss match, determining the simulation board constructed based on the target contour line as the target simulation board. Based on this, the target contour line closest to the target distortion map can be determined from multiple contour lines through the contour of the low-pressure area in the distortion map and the loss of the low-pressure area, and then the target simulation board can be constructed according to the target contour line. In this way, the accuracy of the distortion map corresponding to the target simulation board can be improved, and at the same time, the design cycle of the total pressure distortion simulator can be shortened, the design efficiency of the distortion map can be improved, and the experimental cost of the total pressure distortion simulation can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0012] Figure 1 A schematic diagram of a simulated network structure of a simulated network type total pressure distortion generator provided by an exemplary embodiment of the present disclosure;

[0013] Figure 2 A schematic diagram of a plug-in structure of a plug-in type total pressure distortion generator provided by an exemplary embodiment of the present disclosure;

[0014] Figure 3 A schematic diagram of a simulation plate structure of a simulation plate type total pressure distortion generator provided by an exemplary embodiment of the present disclosure;

[0015] Figure 4 A schematic diagram of a placement position of a simulation plate of an air inlet provided by an exemplary embodiment of the present disclosure;

[0016] Figure 5 A schematic diagram of the structure of a numerical simulation model provided for an exemplary embodiment of the present disclosure;

[0017] Figure 6 A schematic diagram of a fluid velocity direction being deflected under an adverse pressure gradient provided by an exemplary embodiment of the present disclosure;

[0018] Figure 7 A schematic diagram of a fluid flow direction and pressure gradient distribution in a cross section behind a simulation plate provided by an exemplary embodiment of the present disclosure;

[0019] Fig. 8A A schematic diagram of vorticity distribution generated by a first simulation plate provided for an exemplary embodiment of the present disclosure;

[0020] Figure 8B A schematic diagram of vorticity distribution generated by a second simulation plate provided for an exemplary embodiment of the present disclosure;

[0021] Figure 8C A schematic diagram of vorticity distribution generated by a third simulation plate provided for an exemplary embodiment of the present disclosure;

[0022] Fig.8D A schematic diagram of vorticity distribution generated by a fourth simulation plate provided for an exemplary embodiment of the present disclosure;

[0023] Fig. 9 A schematic diagram of a vorticity distribution diagram at a position 0.5D behind a simulation plate provided by an exemplary embodiment of the present disclosure;

[0024] Fig. 10A A schematic diagram of vorticity distribution at position 0 behind a simulation plate in the first stage provided by an exemplary embodiment of the present disclosure;

[0025] Fig. 10B A schematic diagram of vorticity distribution at a position 0.1D behind a simulation plate in the first stage provided by an exemplary embodiment of the present disclosure;

[0026] Fig. 10C A schematic diagram of vorticity distribution at a position 0.25D behind a simulation plate in the first stage provided by an exemplary embodiment of the present disclosure;

[0027] Fig. 10D A schematic diagram of vorticity distribution at a position 0.75D behind a simulation plate in the first stage provided by an exemplary embodiment of the present disclosure;

[0028] Fig. 10E A schematic diagram of vorticity distribution at a position 1D behind a simulation plate in the first stage provided by an exemplary embodiment of the present disclosure;

[0029] Fig.11A A schematic diagram of the distribution of the relative total pressure coefficient of the surface at the position 0 behind the first stage simulation plate provided by an exemplary embodiment of the present disclosure;

[0030] Fig. 11B A schematic diagram of the relative total pressure coefficient of the surface at a position 0.1D behind the first stage simulation plate provided by an exemplary embodiment of the present disclosure;

[0031] Fig. 11C A schematic diagram of the relative total pressure coefficient of the surface at a position 0.25D behind the first stage simulation plate provided by an exemplary embodiment of the present disclosure;

[0032] Fig.11D A schematic diagram of the relative total pressure coefficient of the surface at a position 0.75D behind the first stage simulation plate provided by an exemplary embodiment of the present disclosure;

[0033] Fig.11E A schematic diagram of the relative total pressure coefficient of the surface at a position 1D behind the first stage simulation plate provided by an exemplary embodiment of the present disclosure;

[0034] Fig. 12A A schematic diagram of the change of the low pressure area at a position 1.1D behind the simulation plate under the influence of the second stage mixing provided by an exemplary embodiment of the present disclosure;

[0035] Fig. 12B A schematic diagram of the change of the low pressure area at a position 1.3D behind the simulation plate under the influence of the second stage mixing provided by an exemplary embodiment of the present disclosure;

[0036] Fig. 12C A schematic diagram of the change of the low pressure area at a position 1.5D behind the simulation plate under the influence of mixing in the second stage provided by an exemplary embodiment of the present disclosure;

[0037] Fig.12D A schematic diagram of the change of the low pressure area at a position 1.7D behind the simulation plate under the influence of the second stage mixing provided by an exemplary embodiment of the present disclosure;

[0038] Fig.12E A schematic diagram of the change of the low pressure area at a 2D position behind the simulation plate under the influence of the second stage mixing provided by an exemplary embodiment of the present disclosure;

[0039] Fig.13 A schematic flow chart of a design method of a compressor total pressure distortion simulation board based on vortex effect provided by an exemplary embodiment of the present disclosure;

[0040] Fig.14 A state diagram of a target distortion map provided by an exemplary embodiment of the present disclosure;

[0041] Fig.15A A schematic diagram of the shape of a low-pressure area contour of a target distortion map provided by an exemplary embodiment of the present disclosure;

[0042] Fig. 15B A schematic diagram of a required vorticity distribution provided for an exemplary embodiment of the present disclosure;

[0043] Fig.16A A schematic diagram of the shape of an intermediate simulation board outline provided for an exemplary embodiment of the present disclosure;

[0044] Fig. 16B A schematic diagram of vorticity distribution required for an intermediate simulation plate provided by an exemplary embodiment of the present disclosure;

[0045] Fig.17 A schematic diagram of a reference distortion spectrum obtained by numerical simulation calculation of an intermediate simulation board provided by an exemplary embodiment of the present disclosure;

[0046] Fig.18 A schematic diagram of a structure of a simulation plate for constructing a low-pressure area contour of a reference distortion map provided by an exemplary embodiment of the present disclosure;

[0047] Fig.19 A schematic diagram of a contour line of a relative total pressure coefficient of a surface provided by an exemplary embodiment of the present disclosure;

[0048] Fig. 20 A schematic diagram of a distortion spectrum obtained by a final design provided by an exemplary embodiment of the present disclosure;

[0049] Fig.21 A schematic flow chart of a design method of a compressor total pressure distortion simulation board based on vortex effect provided by an exemplary embodiment of the present disclosure;

[0050] Fig. 22 A schematic structural diagram of a dance video generation device provided by an exemplary embodiment of the present disclosure;

[0051] Fig.23 A schematic diagram of the structure of an electronic device provided for an exemplary embodiment of the present disclosure;

[0052] Fig.24 A schematic diagram of the structure of a computer system provided for an exemplary embodiment of the present disclosure;

[0053] Fig.25 A schematic diagram of a computer program product provided for an exemplary embodiment of the present disclosure. DETAILED DESCRIPTION

[0054] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0055] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0056] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0057] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0058] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0059] At present, with the increase of aircraft flight speed and flight altitude, the requirements for aircraft maneuverability will also be higher. In this process, when the existing engine model is used to control the aircraft for simulated flight at a faster flight speed and higher flight altitude, the air flow state in the compressor in the engine model will change unfavorably, resulting in a sharp deterioration of the inlet flow field, which in turn affects the engine model and further causes aircraft failure. At the same time, with the continuous increase of compressor load, the compressor becomes more and more sensitive to intake distortion, making the aerodynamic stability problem of the compressor more and more prominent.

[0060] In view of the above problems, the existing technology can conduct stability tests on compressors for various working conditions during the compressor design stage. During the stability test, it is necessary to simulate various corresponding distortion spectra at the air inlet. In the process of analyzing the operating conditions and flight conditions of the compression system of aviation gas turbine engines, it is found that total pressure distortion is the largest external destabilizing factor affecting its aerodynamic stability. Therefore, whether the design method of the total pressure distortion generator can quickly and accurately generate the total pressure distortion spectrum is the top priority for engine stability testing.

[0061] The current total pressure distortion generators mainly include plug-in type total pressure distortion generators, simulated plate type total pressure distortion generators and simulated mesh type total pressure distortion generators, etc. The following introduces the above different types of total pressure distortion generators.

[0062] Figure 1 The following is a schematic diagram of a simulated network structure of a simulated network total pressure distortion generator provided by an exemplary embodiment of the present disclosure. Figure 1 As shown in Figure 1, the simulated mesh total pressure distortion generator is the earliest total pressure distortion simulation technology. It uses wire meshes of different diameters and porosities to assemble a complete screen and uses the airflow wake behind the screen to generate total pressure distortion. This distortion generation method is widely used in the United States, the United Kingdom, Germany and other countries. In related, Overall has developed a program that combines screen sections of different porosities and uses isentropic flow area calculation to construct a total pressure distortion profile.

[0063] However, once the initial screen has been constructed in this way, it can be tested under actual operating conditions and the resulting profile compared to the original desired total pressure field. The screen design, construction, and testing are then repeated until the desired profile is achieved within an acceptable error range, a process that typically requires 4-6 physical iterations. Relatedly, Keith et al. used an array of individually controllable wedges to form a distortion generator, and their analytical model provided a fast and reliable configuration scheme to generate specific distortions. Anthony et al. used a hexagonal unit flow control grid composed of airfoil cross sections to improve aerodynamic and flow control characteristics and obtain greater design flexibility and accuracy.

[0064] Figure 2 The schematic diagram of the plug-in structure of a plug-in type total pressure distortion generator provided by an exemplary embodiment of the present disclosure is as follows. Figure 2As shown, the existing technology has mature experience in the research of plug-in type total pressure distortion generators, and many experiments with scaled simulation boards have been conducted and relevant databases have been established. Most domestic engine research and development units adopt the plug-in type adjustable distortion simulator introduced from Russia in the 1990s. Li Liang studied a single crescent-shaped plug-in as a standard plug-in for the inlet total pressure distortion evaluation experiment and found that the distortion it produced was conservative and strict; Xia Aiguo and others conducted experimental research on double-plug-in type distortion generators in order to increase the distortion simulation range of the plug-in; Zhu Aidi and others analyzed the flow field structure and distortion degree after the plug-in and found that the numerical simulation results and experimental results of the AIP section were in good agreement in terms of trend, but the accuracy of the distortion spectrum needs to be further improved.

[0065] In the related technology, Ye Wei et al. proposed a semi-empirical design method for simulation board design using plug-in plate experimental data. The approximate outline of the simulation board was preliminarily determined according to the shape of the filling map, and then the modification plan of the simulation board was determined according to the annular distortion intensity of the blowing test results; Lu Deyu et al. experimentally studied the design of scaled simulation boards and concluded that the distortion indices of large and small models have a good correlation; Zhu Aidi tried to use a contour line in the total pressure recovery coefficient map to design the simulation board. The results showed that the approximate distribution of high and low pressure areas can be simulated, but the accuracy of the map and distortion index needs to be improved, and it is difficult to find a unified mapping relationship between the cross-section calculated by computational fluid dynamics (CFD) and the target distortion map.

[0066] From the above content, it can be seen that due to the single shape of the plug-in type total pressure distortion generator, the total pressure loss distribution in the distortion spectrum it can produce is not easy to control, and the accuracy of the obtained distortion spectrum cannot be guaranteed. Compared with the plug-in type total pressure distortion generator, the analog plate type total pressure distortion generator can produce a wide range of distortions and various shapes, and can flexibly adjust its shape contour, size and other characteristics according to the total pressure loss distribution of the target distortion spectrum, so that the target distortion spectrum can be simulated more accurately.

[0067] Figure 3 The schematic diagram of the simulation plate structure of a simulation plate type total pressure distortion generator provided by an exemplary embodiment of the present disclosure is as follows. Figure 3As shown in FIG. 1 , the current design of a simulation plate type total pressure distortion generator mainly relies on experience and distortion tests, and often directly selects the low total pressure area in the target distortion spectrum as the contour of the simulation plate. This method can produce distortion at the aerodynamic interface (AIP) to a certain extent, but the distribution and size of the loss in the distortion zone are often quite different from the target distortion spectrum, resulting in difficulty in meeting the design accuracy requirements. In addition, the design process requires repeated cycles of testing-adjustment-retesting-readjustment, and ultimately the design cycle required to obtain a simulation plate that can generate the target distortion spectrum is long and the cost is high.

[0068] Figure 4 A schematic diagram of the placement of a simulation plate of an air inlet provided by an exemplary embodiment of the present disclosure. Figure 4 As shown, under normal circumstances, airflow distortion in the intake duct will have a significant impact on the performance of the engine and other equipment. Therefore, the distortion spectrum obtained by the simulation board can be used to quantify the degree of distortion in the intake duct, providing an important basis for evaluating the performance of the intake duct. The simulation board 401 is usually placed in the intake duct 402, and the distortion spectrum can be obtained by the simulation board.

[0069] In response to the above problems, the embodiments of the present disclosure provide a design method for a compressor total pressure distortion simulation plate based on vortex influence, which is mainly aimed at the design of a simulation plate in a simulation plate type total pressure distortion generator. Specifically, according to the distribution and development law of the fluid vortex in the area behind the simulation plate, the shape contour of the low-pressure area in the distortion spectrum and the loss size of the low-pressure area can be adjusted, thereby improving the accuracy of the distortion spectrum. At the same time, it can also shorten the design cycle of the total pressure distortion simulator, improve the design efficiency of the distortion spectrum, and reduce the experimental cost of the total pressure distortion simulation.

[0070] Figure 5 The structure diagram of a numerical simulation model provided by an exemplary embodiment of the present disclosure is shown in FIG. Figure 5 As shown, the simulation board 502 can be placed in the air inlet 501, and then the distortion spectrum can be obtained in the AIP section 503. In addition, considering the characteristics of the numerical simulation technology being fast, low-cost and safe, the simulation board can be designed by the numerical simulation method, thereby completing the simulation of the target distortion spectrum. In the embodiment disclosed herein, D represents the diameter of the air inlet, the AIP section is taken as the position 2D behind the simulation board, and 8D represents that 8 times the diameter of the air inlet is the length of the air inlet 501.

[0071] In practical applications, due to the obstruction of the simulation plate to the fluid, a recirculation zone will be formed in a certain area downstream of the simulation plate, and the backflow fluid in the recirculation zone is a fluid with a higher total pressure and greater energy under the definition of traditional total pressure. However, this part of the fluid is very unfavorable for the operation of the engine. In order to correctly express the loss of this part of the fluid, the concept of "effective total pressure" is borrowed, which can be specifically expressed in the embodiment of the present disclosure as follows:

[0072]

[0073] Among them, EPt represents the effective total pressure at a certain point of this cross section, P is the local static pressure, ρ is the fluid density, u represents the velocity of the fluid in the horizontal direction, v represents the velocity of the fluid in the vertical direction, and w represents the velocity of the fluid in the mainstream flow direction. In the embodiments of the present disclosure, this defined effective total pressure is used instead of the traditional total pressure.

[0074] In order to intuitively express the mapping relationship between the simulation plate and the total pressure loss, the embodiment of the present disclosure also introduces a dimensionless parameter "surface relative total pressure coefficient PPt", which can be specifically defined as:

[0075]

[0076] Among them, EPt represents the effective total pressure at a certain point on this section, Pt max Indicates the maximum effective total pressure of this section, Pt min Indicates the minimum value of the effective total pressure of this section. In addition, in the relevant content of the embodiment of the present disclosure, it is stipulated that the part with a relative total pressure coefficient less than 0.2 is defined as a low pressure area, the part with a relative total pressure coefficient greater than 0.9 is defined as a high pressure area, and the other parts are defined as transition areas.

[0077] As for the measurement of the distortion size, the embodiment of the present disclosure adopts the critical circumferential total pressure distortion index DC(120) of Rolls-Royce of the United Kingdom:

[0078]

[0079] Among them, EPt0 is the average effective total pressure of the inlet cross-sectional flow, EPt low is the average effective total pressure of the flow in the 120-degree distortion zone at the AIP section, and P0 is the average inlet static pressure.

[0080] In practical applications, due to the existence of Kelvin-Helmholtz instability, the vorticity is stronger at the junction of high and low pressure areas, and the vorticity gradually decreases with the mixing along the way. Therefore, the vorticity has a greater impact on the flow and mixing near the simulation plate, and as the fluid continues to mix downstream, the vorticity and pressure gradient in the flow field continue to decrease. At this time, the influence of vorticity and pressure gradient on the total pressure loss distribution is also gradually reduced. In order to refine the influencing factors of the change of low pressure areas during the flow process, the embodiment of the present disclosure is divided into two stages according to the size of the vorticity when studying the influence of the total pressure loss distribution at the AIP section:

[0081] In the first stage, the distribution of total pressure loss is mainly affected by vorticity and pressure gradient, and the vorticity gradually decreases along the process;

[0082] In the second stage, the pressure gradient and vortex no longer have a significant effect on the flow field. The main factor affecting the total pressure loss distribution in this stage is the mixing between the high-pressure and low-pressure fluids.

[0083] Based on this, through the research conclusions of Antoniou et al., it can be seen that the separation of the flow behind the plate begins at the leading edge of the simulation plate, and a large recirculation area is formed behind the plate. The direction of fluid flow behind the simulation plate is from the low-pressure area at the bottom to the high-pressure area.

[0084] Figure 6 A schematic diagram of a fluid velocity direction being deflected under an adverse pressure gradient is provided as an exemplary embodiment of the present disclosure. Figure 6 As shown, when the fluid flows against the pressure gradient, the velocity component in the pressure gradient direction v2 decreases, causing the fluid velocity direction v1 to deflect and become v1'.

[0085] Figure 7 The schematic diagram of the fluid flow direction and pressure gradient distribution of the cross section behind the simulation plate provided by an exemplary embodiment of the present disclosure. Figure 7 As shown, the streamlines in the cross-sectional area near the simulation plate mainly intersect with the pressure gradient contour line radially. Due to the different angles between the streamlines and the pressure gradient direction, the movement direction of the fluid will be deflected to varying degrees, which is manifested as the formation of vortices in the normal section.

[0086] Since vortices are generated when the fluid flows against the pressure gradient, the distribution position of the vortices basically coincides with the transition zone with a larger pressure gradient, that is, near the junction of 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 cross section, the stronger vortex structure will continuously affect the shape change of the low-pressure zone at the boundary of the low-pressure zone.

[0087] Fig. 8A A schematic diagram of vorticity distribution generated by a first simulation plate provided as an exemplary embodiment of the present disclosure. Figure 8B A schematic diagram of vorticity distribution generated by a second simulation plate provided as an exemplary embodiment of the present disclosure. Figure 8C A schematic diagram of vortex distribution generated by a third simulation plate provided as an exemplary embodiment of the present disclosure. Fig.8D A schematic diagram of the vortex distribution generated by the fourth simulation plate provided by an exemplary embodiment of the present disclosure. Figures 8A to 8D The figure shows the vorticity distribution generated by the edges of several different shapes of simulation plates. The fluid flow direction is perpendicular to the paper surface and inward. The red part indicates that the vortex direction is clockwise, and the blue part indicates that the vortex direction is counterclockwise.

[0088] The present disclosure embodiment Fig. 8A The flow field analysis is carried out using the simulation plate in the figure as an example, and the influence of the vortex on the flow field and the changes in the low-pressure area is explained in detail.

[0089] Fig. 9 A schematic diagram of a vorticity distribution diagram at a position 0.5D behind a simulation plate provided as an exemplary embodiment of the present disclosure. Fig. 10A A schematic diagram of vorticity distribution at position 0 behind a first-stage simulation plate provided for an exemplary embodiment of the present disclosure. Fig. 10B A schematic diagram of vorticity distribution at a position 0.1D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig. 10C A schematic diagram of vorticity distribution at a position 0.25D behind a first-stage simulation plate provided for an exemplary embodiment of the present disclosure. Fig. 10D A schematic diagram of vorticity distribution at a position 0.75D behind a first-stage simulation plate provided for an exemplary embodiment of the present disclosure. Fig.10E A schematic diagram of vorticity distribution at a position 1D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig.11A A schematic diagram of the along-the-path distribution of the relative total pressure coefficient of the surface at position 0 behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig. 11B A schematic diagram of the relative total pressure coefficient of the surface at a position 0.1D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig. 11C A schematic diagram of the relative total pressure coefficient of the surface at a position 0.25D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig.11D A schematic diagram of the relative total pressure coefficient of the surface at a position 0.75D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure. Fig.11E A schematic diagram of the relative total pressure coefficient of the surface at a position 1D behind a first-stage simulation plate provided by an exemplary embodiment of the present disclosure.

[0090] like Fig. 9 , Figures 10A to 10E and Figures 11A to 11EAs shown in Figure 1, during the development of the first stage, as the flow moves downstream, the position of the boundary between the high-pressure area and the low-pressure area changes synchronously with the position of the vortex, that is, the vortex can always affect the contour change of the low-pressure area at the boundary of the low-pressure area. Fig. 9 As shown in the figure, there are three pairs of vortices at the edge of the low pressure area. Fig. 9 Take the middle part of the vortex as an example, Fig. 9 The flow direction of the fluid in the middle points to the back of the paper. Based on the right-hand rule, the vortex on the left is a positive vortex, and the vortex on the right is a negative vortex. The outline of the low-pressure area in the middle of this set of vortices will accelerate outward expansion under the promotion of the vortex. Therefore, after the first stage of the influence of the vortex, the outline of the low-pressure area in the middle part forms a convex shape in the middle.

[0091] The same is true for the vortices on the left and right sides of the simulation plate. The middle part of the vortices on the left and right sides will promote the expansion of the low pressure area. Fig. 9 The influence of the three groups on the vortex, the contour of the low pressure area becomes mainly Fig. 10E The three directions shown are convex outward, thus forming Fig.11E Distribution cloud diagram of the relative total pressure coefficient of the surface at the 1D position.

[0092] Fig. 12A A schematic diagram of the change along the path of a low-pressure zone at a position 1.1D behind a simulation plate under the influence of second-stage mixing provided by an exemplary embodiment of the present disclosure. Fig. 12B A schematic diagram of the change along the path of a low-pressure zone at a position 1.3D behind a simulation plate under the influence of second-stage mixing provided by an exemplary embodiment of the present disclosure. Fig. 12C A schematic diagram of the change along the path of a low-pressure zone at a position 1.5D behind a simulation plate under the influence of second-stage mixing provided by an exemplary embodiment of the present disclosure. Fig.12D A schematic diagram of the change along the path of a low-pressure zone at a position 1.7D behind a simulation plate under the influence of second-stage mixing provided by an exemplary embodiment of the present disclosure. Fig.12E A schematic diagram of the change of the low pressure area at the 2D position behind the simulation plate under the influence of the second stage mixing provided by an exemplary embodiment of the present disclosure. Figures 12A to 12E As shown in the figure, in the second stage, the vorticity and the normal pressure gradient are already very small, so that they no longer have a significant impact on the shape of the low-pressure area in the direction perpendicular to the flow. At this time, the main factor affecting the change in the shape of the low-pressure area is the mixing of the fluids in the high-pressure and low-pressure areas. Mixing makes the total pressure distribution of the fluid at the junction of the high-pressure area and the low-pressure area in the flow field uniform, that is, the originally uneven contour curve of the low-pressure area becomes smooth, and at the same time, the total area of ​​the low-pressure area is reduced.

[0093] In summary, in the flow field behind the simulation plate, due to the obstruction of the simulation plate to the airflow, high-pressure and low-pressure areas are formed behind the simulation plate, thereby forming a counter-vortex under the action of a large pressure gradient, and due to the influence of the vortex, the contour of the low-pressure area near the middle part of the counter-vortex shows an outward expansion change. After the first stage, the vortex volume gradually decreases to a lower level. In the second stage, the low-pressure area is mainly affected by the mixing of the high-pressure area fluid, and the contour of the low-pressure area becomes gentle and the range of the low-pressure area is reduced.

[0094] Based on this, the embodiments of the present disclosure can study the shape contour of the low-pressure area and the size of the loss in the low-pressure area based on the flow field laws such as the development and changes of the vortex and pressure gradient behind the simulation plate, and then propose an improved method to improve the accuracy of the design distortion map.

[0095] Fig.13 A schematic flow chart of a design method for a compressor total pressure distortion simulation board based on vortex effect is provided as an exemplary embodiment of the present disclosure. Fig.13 As shown, specifically including:

[0096] S1301, obtaining a target distortion map, and dimensionlessly converting the data in the target distortion map, and then extracting the contour data of the low-pressure area from the dimensionlessly converted data as the contour data of the intermediate simulation board.

[0097] Fig.14 A state diagram of a target distortion map provided by an exemplary embodiment of the present disclosure. Fig.15A A schematic diagram of the shape of a low-pressure area contour of a target distortion map provided by an exemplary embodiment of the present disclosure. Fig. 15B A schematic diagram of a required vortex distribution is provided for an exemplary embodiment of the present disclosure. Fig.14 , Fig.15A and Fig. 15B As shown, the embodiment of the present disclosure can achieve accurate simulation of the shape contour of the low-pressure area of ​​the distortion spectrum.

[0098] Specifically, the shape of the low-pressure area of ​​the target distortion map can be analyzed, such as Fig.15A As shown, it can be divided into three parts according to left, middle and right. Fig.15A The left and right parts are relatively straight, while the middle part is expanding outwards compared to the left and right parts. Therefore, using the influence of vortex distribution on the low-pressure area, it can be known that there needs to be a set of strong counter-vortices in the part where the low-pressure area in the middle expands outwards. This set of counter-vortices should be able to make the low-pressure area in the middle expand outwards, so Fig. 15B The simulated plate profile and vorticity distribution are shown.

[0099] like Fig. 15BAs shown in Figure 2, the middle area of ​​the simulation plate is relatively straight. The fluid on the back of the simulation plate flows radially from the low-pressure area to the high-pressure area, and, as shown in Figure 2, Figure 6 As shown in the figure, in the middle area of ​​the simulation plate, the airflow on the left side will be deflected to the left to form a counterclockwise vortex, while the airflow on the right side will be deflected to the right to form a clockwise vortex. This set of vortices in the middle area of ​​the simulation plate will cause the shape of the low-pressure area to expand outward in the middle part during its development to approach the outline of the low-pressure area in the target distortion map.

[0100] The next goal is to obtain Fig. 15B The shape contour of the simulation board shown in the figure is extracted and its contour features 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 are more convex than the middle part. To obtain such a shape contour, we can start with the contour of the low-pressure area in the target distortion map.

[0101] Fig.16A A schematic diagram of the shape of an intermediate simulation board outline provided by an exemplary embodiment of the present disclosure. Fig. 16B A schematic diagram of the vorticity distribution required for an intermediate simulation plate provided by an exemplary embodiment of the present disclosure. Fig.16A and Fig. 16B As shown in Figure 2, the low-pressure area of ​​the target distortion map can be extracted as the contour of the simulation board for analysis, such as Fig. 16B As shown in the figure, the contours on the left and right sides are relatively straight. When the fluid in the recirculation zone flows through this area, two sets of vortices are formed under the action of the normal pressure gradient. In the middle area, the contour slightly expands outward to form a micro-arc. The streamlines here are parallel to the direction of the pressure gradient, and basically no vortices are formed that affect the shape of the low-pressure area. Therefore, Fig. 16B The simulated plate of the shape can generate a set of counter-vortices in the left and right areas respectively. The contour of the low-pressure area is stretched by the two sets of counter-vortices to form the required Fig.16A The shape outline is the desired shape outline.

[0102] Based on this, if we want to obtain the low-pressure area contour of the target distortion map, we first need to obtain Fig. 15B The shape outline shown, Fig. 15B The shape contour shown can be obtained from the shape contour of the low-pressure area of ​​the target distortion map, and then the contour data of the intermediate simulation plate can be determined, that is, the contour shape of the intermediate simulation plate can be determined.

[0103] S1302, performing numerical analysis on the contour data of the intermediate simulation board to obtain a reference distortion spectrum.

[0104] Fig.17 A schematic diagram of a reference distortion spectrum obtained by numerical simulation calculation of an intermediate simulation board provided in an exemplary embodiment of the present disclosure. Fig.18A schematic diagram of a structure of a reference distortion spectrum low-pressure area contour construction simulation board provided by an exemplary embodiment of the present disclosure. Fig.17 and Fig.18 As shown, the outline of a simulation plate can be constructed according to the contour data of the low-pressure area of ​​the target distortion map in step S1301. After numerical simulation of the simulation plate, a reference distortion map can be obtained. Then, the simulation plate constructed with the shape of the low-pressure area of ​​the reference distortion map can produce a reference distortion map that is close to the shape of the low-pressure area of ​​the target distortion map.

[0105] In some embodiments, the shape profile of the reference distortion map and the target distortion map can also be compared to find that, by using the influence of the vorticity distribution twice, the shape and distribution of the low-pressure area in the designed reference distortion map are basically consistent with the target distortion map. When the shape of the low-pressure area of ​​the constructed reference distortion map is similar to the target distortion map, the control performance of the simulated control board decreases or the error increases due to various factors during operation, thereby causing losses. Therefore, it is also necessary to adjust the size of the low-pressure area loss to make it close to the target distortion map.

[0106] S1303, non-dimensionalizing the data corresponding to the reference distortion map to obtain a plurality of contour lines;

[0107] Fig.19 This is a schematic diagram of a relative total pressure coefficient contour line provided by an exemplary embodiment of the present disclosure. Fig.19 As shown, the reference distortion spectrum obtained in S1302 can be dimensionless according to the surface relative total pressure coefficient, and the contour line of the surface relative total pressure coefficient in the range of 0.1 to 0.2 is obtained.

[0108] Specifically, the target value range and interval of the contour line can be determined first, that is, the contour line with the relative total pressure coefficient of the surface in the range of 0.1 to 0.2 can be taken. At the same time, the data corresponding to the reference distortion spectrum can be dimensionless to determine the distortion value of each image point. Then, an interpolation algorithm, such as linear interpolation, bilinear interpolation or more complex interpolation methods, can be used to interpolate between data points to more accurately determine the position where the contour line passes. Finally, starting from an initial point, the path of the contour line can be gradually traced according to the algorithm, and then multiple contour lines can be obtained, and then multiple contour lines can be determined based on multiple contour lines. It should be understood that the values ​​on the contour line are equal everywhere.

[0109] Thus, multiple contour lines can be obtained, which are a group of curves with similar shapes but different enclosed areas. The simulation board constructed with this series of curves as the contour has the following characteristics: the shape contours of these simulation boards are similar to Fig. 15BThe simulated plates shown have similar shape contours, and the degree of resistance to airflow of the simulated plates constructed by these contour lines varies monotonically with the area of ​​the simulated plates, and the area of ​​the simulated plates varies monotonically with the relative total pressure coefficient of the surface. Therefore, the size of the loss can be controlled by adjusting the area of ​​the simulated plates.

[0110] Since their shapes and contours are similar, the locations of the vorticity distributions they generate and the distribution and shapes of the low-pressure areas in the reference distortion maps are basically similar.

[0111] S1304, using a binary search method to determine a target contour line from multiple contour lines.

[0112] In some embodiments, since the loss size increases monotonically with the area of ​​the simulation board, when designing the simulation board, the binary method can be used to select the contour line within the range of 0.1 to 0.2, thereby achieving the adjustment of the distortion index, the area of ​​the low-pressure area and the average total pressure of the low-pressure area without changing the shape of the low-pressure area, so that it is closer to the target distortion map.

[0113] Specifically, the distortion maps corresponding to different contours can be adjusted by continuously adjusting the distortion index, the area of ​​the low pressure area, and the average total pressure of the low pressure area until the similarity between the distortion map and the target distortion map meets the preset threshold, and the contour corresponding to the distortion map whose similarity with the target distortion map meets the preset threshold is determined as the target contour. The preset threshold can be 95%, 93%, or 90%, which can be set according to actual conditions.

[0114] S1305, determining the first loss corresponding to the distortion map corresponding to the target contour line at the AIP section, and determining the second loss corresponding to the target distortion map at the AIP section, and when the first loss and the second loss meet preset conditions, determining that the simulation board corresponding to the target contour line is the target simulation board.

[0115] In some embodiments, if the difference between the first loss and the second loss does not meet the requirement of the preset threshold, the candidate distortion map can be replaced, that is, the contour line can be reselected. In this way, the loss size can be adjusted under the condition that the loss distribution and the shape contour of the low-pressure area in the distortion map remain basically unchanged, and finally the target simulation board can be constructed based on the target contour line.

[0116] Fig. 20 FIG. 1 is a schematic diagram of a distortion spectrum obtained by a final design provided by an exemplary embodiment of the present disclosure. Fig. 20As shown, the disclosed embodiment lists the distortion spectrum design results when the relative total pressure coefficient of the selected surface is 0.10, 0.12, and 0.14, and the loss size of the total pressure distortion spectrum at the AIP section is shown in Table 1. It can be seen from Table 1 that for the simulation plates constructed by selecting different contour lines, as the area of ​​the simulation plate increases, the distortion index in the generated distortion spectrum increases, the area of ​​the low-pressure zone increases, and the average total pressure of the cross section and the average total pressure of the low-pressure zone decrease. From the results in the table, it can be seen that in the disclosed embodiment, the simulation plate constructed by selecting the contour line with a relative total pressure coefficient of 0.12 is closest to the loss size of the target distortion spectrum, and the distortion spectrum finally designed is as shown. Fig. 20 shown.

[0117] Table 1 Comparison of target flow field and design flow field data

[0118]

[0119] Based on this, the disclosed embodiment can adjust the shape contour of the low-pressure area in the total pressure distortion map of the compressor based on the flow field laws such as the change of vorticity and pressure gradient after the simulation plate, and control the total pressure loss in the low-pressure area by controlling the area of ​​the simulation plate, thereby improving the simulation accuracy of the distortion map. This method uses numerical simulation to study the influence of pressure gradient and streamline on the generation and distribution of vorticity in stages, thereby achieving precise control of the shape contour and loss size of the low-pressure area in the total pressure distortion map.

[0120] Specifically, first, the disclosed embodiment can accurately simulate the shape contour of the low-pressure area of ​​the target distortion map. The shape of the low-pressure area of ​​the target distortion map can be extracted, and the middle simulation board is constructed with the shape as the contour, which is divided into three parts according to left, middle and right. The left and right parts of the middle simulation board are relatively straight, while the middle part is outwardly expanded compared to the left and right. Such a simulation board will cause the left and right parts to generate a set of counter-vortex structures respectively, and these two sets of counter-vortices can cause the low-pressure areas of the left and right parts to expand outward.

[0121] After constructing the intermediate simulation plate, the intermediate simulation plate can also be numerically simulated to obtain a reference distortion spectrum, and then the spectrum is dimensionless to obtain a series of contour lines of the relative total pressure coefficient of the surface. Then, a specific contour line can be selected as the outline to construct the simulation plate again. The simulation plate of this shape can produce a set of counter-vortices in the middle area, and this set of counter-vortices can make the shape of the low-pressure area close to the shape of the low-pressure area of ​​the target distortion spectrum. Through numerical simulation calculations, a spectrum close to the target distortion spectrum can be obtained. By utilizing the influence of the vorticity distribution twice, the shape of the low-pressure area in the designed distortion spectrum is basically consistent with the target distortion spectrum. When the shape of the low-pressure area of ​​the constructed distortion spectrum is similar to the target spectrum, it is also necessary to adjust the size of the low-pressure area loss to make it close to the target spectrum.

[0122] Finally, the reference distortion spectrum can be dimensionless according to the relative total pressure coefficient of the surface, and the contour lines of the relative total pressure coefficient of the surface in the range of 0.1-0.2 are taken. They are a set of curves with similar shapes but different enclosed areas. Therefore, the embodiment of the present disclosure can use the contour lines of the relative total pressure coefficient of the surface with different values ​​in the reference spectrum to achieve the control of the loss size, and by selecting the contour lines of different values ​​to construct a simulation board and perform numerical simulation calculations, it can be achieved that the loss size of the final design and the loss size of the target distortion spectrum meet the accuracy requirements.

[0123] The embodiment of the present disclosure provides a method for designing a compressor total pressure distortion simulation board based on vortex influence, which can be executed by a terminal or by a chip applied to the terminal.

[0124] Exemplarily, the above-mentioned terminals may include one or more of mobile phones, tablet computers, wearable devices, vehicle-mounted devices, laptop computers, ultra-mobile personal computers (UMPCs), netbooks, personal digital assistants (PDAs), and wearable devices based on augmented reality (AR) and / or virtual reality (VR) technology, and may also include but not be limited to remote control devices, wearable devices, street lamps, home appliances and other smart terminals, which are not specifically limited in the embodiments of the present disclosure.

[0125] Fig.21 A schematic flow chart of a design method for a compressor total pressure distortion simulation board based on vortex effect is provided as an exemplary embodiment of the present disclosure. Fig.21 As shown, specifically including:

[0126] S2101, obtaining a target distortion map, and determining contour data corresponding to the low-pressure area from the target distortion map.

[0127] Specifically, the low-pressure area of ​​the target distortion map can be extracted as the contour of the simulation board for analysis, such as Fig. 16B As shown in the figure, the contours on the left and right sides are relatively straight. When the fluid in the recirculation zone flows through this area, two sets of vortices are formed under the action of the normal pressure gradient. The middle area is slightly expanded outward to form a micro-arc. The streamlines here are parallel to the direction of the pressure gradient, and basically no vortices that affect the shape of the low-pressure area are formed. Therefore, Fig. 16B The simulated plate of the shape can generate a set of counter-vortices in the left and right areas respectively. The contour of the low-pressure area is stretched by the two sets of counter-vortices to form the required Fig.16A The shape outline is the desired shape outline.

[0128] S2102, performing numerical simulation on the contour data under a preset scenario to obtain a reference distortion map, and determining a plurality of contour lines based on the reference distortion map.

[0129] In some embodiments, the contour of a simulation plate can be constructed based on the contour data of the low-pressure area of ​​the target distortion map in step S2101. In a preset scenario, the shape of the simulation plate corresponding to the contour is numerically simulated, and then a reference distortion map can be obtained. Then, the simulation plate constructed with the shape of the low-pressure area of ​​the reference distortion map can produce a reference distortion map that is close to the shape of the low-pressure area of ​​the target distortion map. It should be understood that the preset scenario can be a simulated flight scenario, and then a numerical simulation of the fluid dynamics corresponding to the air inlet during flight can be performed. Through numerical simulation, the contour data can be accurately expressed in the form of a mathematical model. This helps to have a deeper understanding of the geometric features of the contour, such as length, curvature, area, etc.

[0130] 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 contour lines with surface relative total pressure coefficients in the range of 0.1 to 0.2 are taken.

[0131] Specifically, the target value range and interval of the contour line can be determined first, that is, the contour line with the relative total pressure coefficient of the surface in the range of 0.1 to 0.2 can be taken. At the same time, the data corresponding to the reference distortion spectrum can be dimensionless to determine the distortion value of each image point. Then, an interpolation algorithm, such as linear interpolation, bilinear interpolation or more complex interpolation methods, can be used to interpolate between data points to more accurately determine the position where the contour line passes. Finally, starting from an initial point, the path of the contour line can be gradually traced according to the algorithm, and then multiple contour lines can be obtained, and then multiple contour lines can be determined based on multiple contour lines. It should be understood that the values ​​on the contour line are equal everywhere.

[0132] S2103, constructing corresponding simulation boards based on the multiple contour lines respectively, and placing the multiple simulation boards in preset scenes for numerical simulation respectively, to obtain distortion maps corresponding to the multiple simulation boards.

[0133] In some embodiments, a simulation board corresponding to a plurality of contour lines can be constructed and placed in a preset scene for numerical simulation, thereby obtaining a distortion spectrum corresponding to each simulation board. The plurality of contour lines are a set of curves with similar shapes but different enclosed areas. The simulation board constructed with this series of curves as the contour has the following characteristics:

[0134] The shapes and outlines of these analog boards are similar to Fig. 15BThe simulated plates shown have similar shapes and contours, and the degree of obstruction to the airflow of the simulated plates constructed by these contour lines varies monotonically with the area of ​​the simulated plates, and the area of ​​the simulated plates varies monotonically with the relative total pressure coefficient of the surface, so the size of the loss can be controlled by adjusting the area of ​​the simulated plates. In addition, since the shapes and contours of the multiple contour lines are similar, the distribution positions of the vorticity generated by them and the distribution and shape of the low-pressure areas in the reference distortion map are basically similar.

[0135] S2104, respectively determining similarities between the multiple distortion maps and the target distortion map, and determining, based on the similarities, from the multiple distortion maps, a contour line corresponding to a distortion map that meets a preset threshold as the target contour line.

[0136] Specifically, data from multiple distortion maps and a target distortion map can be obtained respectively, and the similarity between the data can be determined. The similarity of a distortion map can be determined by the mean of the similarities of the data in the distortion map. Based on this, the similarity between each distortion map and the target distortion map can be determined respectively.

[0137] After determining the similarity between each distortion map and the target distortion map, the contour corresponding to the distortion map whose similarity meets the preset threshold can be determined as the target contour, and the contour corresponding to the distortion map with the highest similarity can be directly selected as the target contour. Specifically, the preset threshold can be 95%, 93% or 90%, which can be set according to actual conditions.

[0138] S2105, determining a first loss according to the distortion map corresponding to the target contour line, and determining a second loss according to the target distortion map, and when the first loss and the second loss match, determining that the simulation board constructed based on the target contour line is the target simulation board.

[0139] In some embodiments, the first loss is the loss corresponding to the distortion map corresponding to the target contour at the pneumatic interface, and the second loss is the loss corresponding to the target distortion map at the pneumatic 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; the difference between the first loss and the second loss can also be directly obtained. When the difference between the first loss and the second loss is less than the 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 is determined to be the target simulation board.

[0140] Based on this, the embodiments of the present disclosure can study the shape contour of the low-pressure area and the size of the loss in the low-pressure area based on the flow field laws such as the development and change of the vortex and pressure gradient behind the simulation plate, and then propose a design method for the compressor total pressure distortion simulation plate based on the influence of vortex.

[0141] In some embodiments, determining a plurality of contour lines based on a reference distortion map includes: non-dimensionalizing the reference distortion map according to a relative total pressure coefficient of a surface, and determining a plurality of contour lines whose relative total pressure coefficients are within a preset range.

[0142] Specifically, the reference distortion spectrum can be dimensionless according to the surface relative total pressure coefficient, and the contour line of the surface relative total pressure coefficient in the range of 0.1 to 0.2 can be obtained.

[0143] In practical applications, the target value range and interval of the contour line can be determined first, that is, the contour line with the relative total pressure coefficient of the surface in the range of 0.1 to 0.2 can be taken. At the same time, the data corresponding to the reference distortion spectrum can be dimensionless to determine the distortion value of each image point. Then, an interpolation algorithm, such as linear interpolation, bilinear interpolation or more complex interpolation methods, can be used to interpolate between data points to more accurately determine the position where the contour line passes. Finally, starting from an initial point, the path of the contour line can be gradually traced according to the algorithm, and then multiple contour lines can be obtained, and then multiple contour lines can be determined based on multiple contour lines. It should be understood that the values ​​on the contour line are equal everywhere.

[0144] Thus, multiple contour lines can be obtained, which are a group of curves with similar shapes but different enclosed areas. The simulation board constructed with this series of curves as the contour has the following characteristics: the shape contours of these simulation boards are similar to Fig. 15B The simulated plates shown in the figure have similar shapes and contours; the degree of airflow obstruction of the simulated plates constructed by these contours varies monotonically with the area of ​​the simulated plates, and the area of ​​the simulated plates varies monotonically with the relative total pressure coefficient of the surface, so the size of the loss can be controlled by adjusting the area of ​​the simulated plates. In addition, since their shapes and contours are similar, the distribution positions of the vorticity generated by them and the distribution and shape of the low-pressure areas in the reference distortion map are basically similar.

[0145] 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.

[0146] In practical applications, if we want to obtain the low-pressure area contour of the target distortion map, we first need to obtain Fig. 15B The shape outline shown, Fig. 15B The shape contour shown can be obtained from the shape contour of the low-pressure area of ​​the target distortion map, and then the contour data of the intermediate simulation plate can be determined, that is, the contour shape of the intermediate simulation plate can be determined.

[0147] In some embodiments, when the first loss and the second loss do not match, the target contour is re-determined from the plurality of distortion maps according to similarities.

[0148] Specifically, if the difference between the first loss and the second loss does not meet the preset threshold, the target contour line can be reselected according to the similarity. In this way, the loss size can be adjusted under the condition that the loss distribution and the shape of the low-pressure area in the distortion map remain basically unchanged, and finally the target simulation board can be constructed based on the target contour line.

[0149] In summary, the disclosed embodiments aim to adjust the shape contour of the low-pressure area in the total pressure distortion map of the compressor through the distribution and development law of the vorticity, and control the total pressure loss in the low-pressure area by controlling the area of ​​the simulation plate, thereby improving the simulation accuracy of the distortion map. This method can use numerical simulation methods to study the influence of pressure gradient and streamline on the generation and distribution of vorticity in stages, thereby achieving precise control of the shape contour and loss size of the low-pressure area in the total pressure distortion map.

[0150] First, the contour of the low-pressure area of ​​the target distortion map can be extracted, and a simulation board can be constructed based on the contour and numerical simulation calculations can be performed to obtain a reference map. The reference map is then dimensionless to obtain a series of contour lines of the relative total pressure coefficient of the surface. Specific contour lines are selected as contours to construct the simulation board again, and numerical simulation calculations are performed to obtain a total pressure distortion map whose shape contour of the low-pressure area is similar to the target distortion map. The loss size is then calculated. Specifically, the control of the loss size can be achieved by selecting contour lines of the relative total pressure coefficient of the surface with different values ​​in the reference map. Ultimately, the disclosed embodiment can accurately simulate the shape and loss size of the low-pressure area in the target distortion map, reduce the need for repeated experiments in the design process, effectively shorten the design cycle, improve design efficiency, and reduce test costs, and is suitable for stability testing of aircraft engines.

[0151] The above mainly introduces the solution provided by the embodiment of the present disclosure from the perspective of the server. It is understandable that, in order to implement the above functions, the server includes hardware structures and / or software modules corresponding to the execution of each function. Those skilled in the art should easily realize that, in combination with the units and algorithm steps of each example described in the embodiments disclosed herein, the present disclosure can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the present disclosure.

[0152] The embodiments of the present disclosure may divide the server into functional units according to the above method examples. For example, each functional module may be divided corresponding to each function, or two or more functions may be integrated into one management module. The above integrated modules may be implemented in the form of hardware or in the form of software functional modules. It should be noted that the division of modules in the embodiments of the present disclosure is schematic and is only a logical functional division. There may be other division methods in actual implementation.

[0153] In the case of dividing each functional module according to each function, an exemplary embodiment of the present disclosure provides a device for generating a dance video, which may be a server or a chip applied to a server. Fig. 22 A schematic diagram of a design device for a compressor total pressure distortion simulation board based on vortex effect provided by an exemplary embodiment of the present disclosure. Fig. 22 As shown, the design device 2200 of the compressor total pressure distortion simulation board based on vortex influence includes:

[0154] An acquisition module 2201 is used to acquire a target distortion map and determine contour data corresponding to a low-pressure area from the target distortion map;

[0155] A simulation module 2202 is used to perform numerical simulation on the contour data under a preset scenario to obtain a reference distortion map, and determine a plurality of contour lines based on the reference distortion map;

[0156] A construction module 2203 is used to construct corresponding simulation boards based on the plurality of contour lines, and to place the plurality of simulation boards in a preset scene for numerical simulation to obtain distortion maps corresponding to the plurality of simulation boards;

[0157] The similarity calculation module 2204 is used to respectively determine the similarities between the plurality of distortion maps and the target distortion map, and determine, according to the similarities, from the plurality of distortion maps, the contour line corresponding to the distortion map that meets a preset threshold as the target contour line;

[0158] The determination module 2205 is used to determine a first loss according to the distortion map corresponding to the target contour line, and determine a second loss according to the target distortion map, and when the first loss and the second loss match, determine that the simulation board constructed based on the target contour line is the target simulation board,

[0159] In an optional manner, the simulation module 2202 is further used to dimensionally transform the reference distortion map according to the surface relative total pressure coefficient, and determine a plurality of contour lines whose surface relative total pressure coefficient is within a preset range.

[0160] In an optional manner, the first loss is the loss corresponding to the distortion map corresponding to the target contour line at the aerodynamic interface, and the second loss is the loss corresponding to the target distortion map at the aerodynamic interface.

[0161] In an optional manner, the acquisition module 2201 is further used to dimensionally transform the data in the target distortion map, and then extract the contour data of the low-pressure area from the dimensionally transformed data.

[0162] In an optional manner, when the first loss and the second loss do not match, the target contour is re-determined from the plurality of distortion maps according to similarity.

[0163] An embodiment of the present disclosure also provides an electronic device, comprising: at least one processor; a memory for storing instructions executable by at least one processor; wherein the at least one processor is used to execute instructions to implement the steps of the above method disclosed in the embodiment of the present disclosure.

[0164] Fig.23 The structure diagram of an electronic device provided by an exemplary embodiment of the present disclosure is shown in FIG. Fig.23 As shown, the electronic device 2300 includes at least one processor 2301 and a memory 2302 coupled to the processor 2301 , and the processor 2301 can execute corresponding steps in the above method disclosed in the embodiment of the present disclosure.

[0165] The processor 2301 may also be referred to as a central processing unit (CPU), which may be an integrated circuit chip having signal processing capabilities. Each step in the method disclosed in the embodiment of the present disclosure may be completed by an integrated logic circuit of hardware in the processor 2301 or by instructions in the form of software. The processor 2301 may be a general-purpose processor, a digital signal processor (DSP), an ASIC, a field-programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. A general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in the embodiment of the present disclosure may be directly embodied as being executed by a hardware decoding processor, or may be executed by a combination of hardware and software modules in a decoding processor. The software module may be located in a memory 2302, such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, or other mature storage media in the art. The processor 2301 reads the information in the memory 2302 and completes the steps of the method in combination with its hardware.

[0166] In addition, when various operations / processes according to the present disclosure are implemented by software and / or firmware, they can be transmitted from a storage medium or a network to a computer system having a dedicated hardware structure, for example, Fig.24 The computer system 2400 shown is installed with the programs constituting the software, and when the various programs are installed, the computer system can execute various functions, including the functions described above. Fig.24 A schematic diagram of the structure of a computer system provided by an exemplary embodiment of the present disclosure.

[0167] Computer system 2400 is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. Electronic devices can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0168] like Fig.24 As shown, the computer system 2400 includes a computing unit 2401, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 2402 or a computer program loaded from a storage unit 2408 to a random access memory (RAM) 2403. In the RAM 2403, various programs and data required for the operation of the computer system 2400 can also be stored. The computing unit 2401, the ROM 2402, and the RAM 2403 are connected to each other via a bus 2404. An input / output (I / O) interface 2405 is also connected to the bus 2404.

[0169] A plurality of components in the computer system 2400 are connected to the I / O interface 2405, including: an input unit 2406, an output unit 2407, a storage unit 2408, and a communication unit 2409. The input unit 2406 may be any type of device capable of inputting information to the computer system 2400, and the input unit 2406 may receive input digital or character information, and generate key signal inputs related to user settings and / or function control of the electronic device. The output unit 2407 may be any type of device capable of presenting information, and may include, but is not limited to, a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The storage unit 2408 may include, but is not limited to, a disk, an optical disk. The communication unit 2409 allows the computer system 2400 to exchange information / data with other devices over a network such as the Internet, and may include, but is not limited to, a modem, a network card, an infrared communication device, a wireless communication transceiver, and / or a chipset, for example, a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0170] The computing unit 2401 may be a variety of general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 2401 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 2401 performs the various methods and processes described above. For example, in some embodiments, the above methods disclosed in the embodiments of the present disclosure may be implemented as a computer software program, which is tangibly included in a machine-readable medium, such as a storage unit 2408. In some embodiments, part or all of the computer program may be loaded and / or installed on an electronic device via ROM 2402 and / or communication unit 2409. In some embodiments, the computing unit 2401 may be configured to perform the above methods disclosed in the embodiments of the present disclosure by any other appropriate means (e.g., by means of firmware).

[0171] The embodiment of the present disclosure also provides a computer-readable storage medium, wherein when the instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the above method disclosed in the embodiment of the present disclosure.

[0172] The computer-readable storage medium in the disclosed embodiments may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. The computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or equipment, or any suitable combination of the foregoing. More specifically, the computer-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0173] The computer-readable medium may be included in the electronic device, or may exist independently without being incorporated into the electronic device.

[0174] Fig.25 Schematic diagram of a computer program product provided by an exemplary embodiment of the present disclosure. Fig.25 As shown, the computer program product 2500 includes a computer program 2501, wherein the computer program 2501 implements the above method disclosed in the embodiment of the present disclosure when executed by a processor.

[0175] In embodiments of the present disclosure, computer program codes for performing the operations of the present disclosure may be written in one or more programming languages ​​or combinations thereof, including but not limited to object-oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as "C" language or similar programming languages. The program code may be executed entirely on a user's computer, partially on a user's computer, as an independent software package, partially on a user's computer, partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may 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 may be connected to an external computer.

[0176] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0177] The modules, components or units involved in the embodiments described in the present disclosure may be implemented by software or hardware, wherein the names of the modules, components or units do not, in some cases, limit the modules, components or units themselves.

[0178] The functions described above herein may be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chip (SOCs), complex programmable logic devices (CPLDs), and the like.

[0179] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, a technical solution formed by replacing the above features with the technical features with similar functions disclosed in the present disclosure (but not limited to).

[0180] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A design method for a compressor total pressure distortion simulation board based on vortex influence, characterized in that: include: Acquire a target distortion map, and determine 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 a plurality of contour lines based on the reference distortion map; Constructing corresponding simulation panels based on the plurality of contour lines respectively, and placing the plurality of simulation panels in preset scenes for numerical simulation respectively, to obtain distortion spectra corresponding to the plurality of simulation panels; Determine the similarities between the plurality of distortion maps and the target distortion map respectively, and determine, according to the similarities, from the plurality of distortion maps, a contour line corresponding to a distortion map that meets a preset threshold as the target contour line; A first loss is determined according to a distortion map corresponding to the target contour line, and a second loss is determined according to the target distortion map. When the first loss and the second loss match, a simulation board constructed based on the target contour line is determined to be a target simulation board.

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

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

4. The method according to claim 1, characterized in that: The method further comprises: When the difference between the first loss and the second loss is smaller than a preset threshold, it is determined that the first loss and the second loss match.

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

6. The method according to claim 1, characterized in that The method further comprises: <24P09941CN> In the case where the first loss and the second loss do not match, the target contour is re-determined from the plurality of distortion maps according to similarity.

7. A design device for a compressor total pressure distortion simulation board based on vortex influence, characterized in that: include: An acquisition module, used for acquiring a target distortion map and determining contour data corresponding to a low-pressure area from the target distortion map; A simulation module, used to perform numerical simulation on the contour data under a preset scenario, obtain a reference distortion map, and determine a plurality of contour lines based on the reference distortion map; A construction module, used to construct corresponding simulation boards based on the plurality of contour lines, and place the plurality of simulation boards in a preset scene for numerical simulation to obtain distortion maps corresponding to the plurality of simulation boards; A similarity calculation module is used to respectively determine the similarities between the plurality of distortion maps and the target distortion map, and determine, according to the similarities, from the plurality of distortion maps, a contour line corresponding to the distortion map that meets a preset threshold as the target contour line; A determination module is used to determine a first loss according to a distortion map corresponding to the target contour line, and to determine a second loss according to the target distortion map. When the first loss and the second loss match, a simulation board constructed based on the target contour line is determined to be a target simulation board.

8. A computer device comprising a memory, a processor and a computer program stored in the memory, characterized in that: The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program / instruction stored thereon, characterized in that: When the computer program / instruction is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product comprising a computer program / instructions, characterized in that When the computer program / instruction is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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