Modeling design method for low-cost integrated centrifugal compressor diffuser

Abstract

The invention discloses a modeling design method for a low-cost integrated centrifugal compressor diffuser, and relates to the field of aero-engine centrifugal compressor diffusers. In order to solve the technical problems that in the prior art, the cost of a conventional blade diffuser manufacturing process is high, the workload during whole machine assembly is increased due to excessive bolt structures, and the reliability is reduced, the technical scheme is that the three-dimensional structure design method for the low-cost integrated centrifugal compressor diffuser model is provided. The method comprises the steps that pneumatic parameters and geometric parameters of an inlet and an outlet of the diffuser are collected; collecting molded lines of a preset casing and a hub; and obtaining a three-dimensional structure of the blade according to the aerodynamic parameters, the geometric parameters and the molded lines of the preset casing and the hub. A step of optimizing the obtained channel construction angle and area distribution of the three-dimensional structure; and based on the optimized blade design, a three-dimensional diffuser structure is obtained through a circumferential array. The centrifugal compressor diffuser is suitable for being applied to design work of the integrated centrifugal compressor diffuser.

Description

Technical Field

[0001] The invention relates to the field of centrifugal compressor diffusers for aircraft engines, and in particular to the design of low-cost integrated centrifugal compressor diffusers. Background Art

[0002] As an important impeller machine, the centrifugal compressor compresses the air to increase its pressure through the rotation of the impeller. Due to its high pressure ratio, compact rhythm, and large stable working range, the centrifugal compressor is widely used in small and medium-sized aircraft engines.

[0003] With the continuous improvement of aircraft engine performance, the requirements for compressor pressure ratio are getting higher and higher. Under high pressure ratio conditions, the airflow at the impeller outlet shows strong non-uniformity in the circumferential and span directions, which further deteriorates the flow environment in the diffuser. As an important component of the centrifugal compressor, the stability of the internal flow of the diffuser will affect the stability of the overall operation of the centrifugal compressor. Widely used diffusers include vane diffusers and vaneless diffusers. Compared with vaneless diffusers, vane diffusers have stronger pressure diffusion capacity and higher efficiency. Under the same pressure ratio, the size of vane diffusers is more compact. In addition, vane diffusers can well control the airflow direction at the diffuser outlet and create good flow conditions for the downstream combustion chamber. Combining the above characteristics, vane diffusers are often used in centrifugal compressors of aircraft engines.

[0004] Conventional blade diffusers include a separate radial diffuser section and an axial straightening section. The radial section is generally composed of wedge-shaped radial blades, and the axial section is generally composed of axial guide blades. The two need to be connected through a bladeless turning section. Its working characteristics are: the pressure of the airflow in the radial diffuser section is greatly increased, the airflows mix with each other after flowing out of the radial section, turn axially in the meridian plane through the bladeless turning section, and finally the airflow turns at a large angle in the axial straightening section and flows to the combustion chamber. In this process, due to the multiple turns in the flow direction of the airflow, backflow and mixing will occur near the bladeless turning position, which will cause large flow losses and lead to a decrease in the aerodynamic performance of the diffuser.

[0005] The axial and radial sections of conventional blade diffusers need to be manufactured in sections, which will increase the cost of the diffuser manufacturing process. The radial and axial sections need to be installed with connecting structures, and the parts need to be connected with bolt structures. Too many bolt structures will increase the workload during the assembly of the whole machine. The reliability inspection of the connection strength of the bolt structure is another major problem, resulting in reduced reliability. Summary of the invention

[0006] In order to solve the technical problems existing in the prior art, the axial section and radial section of the conventional blade diffuser need to be manufactured in sections, which increases the cost of the diffuser manufacturing process, and the various parts need to be connected by bolt structures. Too many bolt structures will increase the workload during the assembly of the whole machine, resulting in reduced reliability. The technical solution provided by the present invention is as follows:

[0007] A low-cost integrated centrifugal compressor diffuser modeling three-dimensional structure design method, the method comprising:

[0008] The steps of collecting aerodynamic parameters and geometric parameters of the diffuser inlet and outlet;

[0009] Steps for collecting the profiles of the preset casing and hub;

[0010] The step of obtaining the three-dimensional structure of the blade according to the aerodynamic parameters and geometric parameters, and the profiles of the preset casing and hub.

[0011] Furthermore, a preferred embodiment is provided, in which the profiles of the casing and the hub are determined according to the preset meridian flow channel and hub profiles.

[0012] Furthermore, a preferred embodiment is provided, in which the blade is designed based on the centerline thickness method, and the three-dimensional structure of the blade is formed by controlling the centerline curvature distribution and the channel area distribution.

[0013] Based on the same inventive concept, the present invention also provides a low-cost integrated centrifugal compressor diffuser modeling three-dimensional structure design device, the device comprising:

[0014] A module for collecting aerodynamic and geometric parameters of the diffuser inlet and outlet;

[0015] Module for collecting the profiles of the preset casing and hub;

[0016] According to the aerodynamic parameters and geometric parameters, as well as the profiles of the preset casing and hub, a module of the three-dimensional structure of the blade is obtained.

[0017] Based on the same inventive concept, the present invention also provides a low-cost integrated centrifugal compressor diffuser modeling design method, the method comprising:

[0018] The step of optimizing the channel configuration angle and area distribution of the obtained three-dimensional structure;

[0019] Based on the optimized blade design, a three-dimensional diffuser structure is obtained by circumferential array.

[0020] Based on the same inventive concept, the present invention also provides a low-cost integrated centrifugal compressor diffuser modeling design device, the device comprising:

[0021] Modules for optimizing the channel configuration angle and area distribution of the resulting three-dimensional structure;

[0022] Based on the optimized blade design, a module with a complete three-dimensional diffuser structure is obtained by arraying along the circumferential direction.

[0023] Based on the same inventive concept, the present invention also provides an integrated centrifugal compressor diffuser, and the diffuser is prepared by: using the obtained three-dimensional diffuser structure, the three-dimensional blade structure is processed by an integrated manufacturing method.

[0024] Based on the same inventive concept, the present invention also provides a computer storage medium for storing a computer program, and when the computer reads the computer program, the computer executes the described method.

[0025] Based on the same inventive concept, the present invention also provides a computer, including a processor and a storage medium. When the processor reads a computer program stored in the storage medium, the computer executes the method described.

[0026] Based on the same inventive concept, the present invention also provides a computer program product, which is a computer program. When the computer program is executed, the method described above is implemented.

[0027] Compared with the prior art, the technical solution provided by the present invention is beneficial in that:

[0028] The integrated fusion structure is used to integrate the radial part, axial part and turning connection part, which reduces the number of bolt structures and significantly improves the connection reliability of the diffuser. Compared with the traditional multi-stage design, this method reduces the risk of bolt loosening or connection leakage during assembly, ensuring the stability and safety of the system.

[0029] The blade design based on the centerline thickness method optimizes the three-dimensional structure of the blade and improves the aerodynamic performance of the diffuser by controlling the distribution of the centerline curvature and the channel area. Compared with the method based on simple blade design in existing research, this optimized design can more effectively control the flow path of the airflow, reduce flow separation and turbulence, and thus improve system efficiency.

[0030] By controlling the distribution of channel construction angles, the separation and mixing of airflow is effectively reduced, and flow losses are reduced. Compared with the design of fixed channel angles in traditional diffusers, dynamically adjusting the channel construction angle can better match the airflow characteristics, thereby reducing energy losses and significantly improving the overall working efficiency and stability of the diffuser.

[0031] The three-dimensional blade structure is arrayed along the circumference, and the diffuser is integrally formed through an integrated manufacturing method, which reduces the processing and manufacturing costs. Compared with traditional segmented processing and assembly, this manufacturing method reduces the processing steps and the use of connectors, thereby shortening the manufacturing cycle, reducing production costs, and improving processing accuracy and overall convenience.

[0032] The invention is suitable for use in the design of integrated centrifugal compressor diffusers. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 The overall schematic diagram of the diffuser.

[0034] Figure 2 Schematic diagram of the axial blade structure of the diffuser blade.

[0035] Figure 3 Schematic diagram of the radial blade structure of the diffuser blade.

[0036] Figure 4 This is a schematic diagram of the meridian flow channel structure design.

[0037] Figure 5 This is the distribution diagram of the curvature and turning angle of the mid-arc.

[0038] Figure 6 Schematic diagram of channel structure angle distribution.

[0039] Figure 7 Schematic diagram of channel area distribution. DETAILED DESCRIPTION

[0040] In order to make the advantages and benefits of the technical solution provided by the present invention more clearly reflected, the technical solution provided by the present invention is now further described in detail with reference to the accompanying drawings, specifically:

[0041] Embodiment 1: This embodiment provides a low-cost integrated centrifugal compressor diffuser modeling three-dimensional structure design method, the method comprising:

[0042] The steps of collecting aerodynamic parameters and geometric parameters of the diffuser inlet and outlet;

[0043] Steps for collecting the profiles of the preset casing and hub;

[0044] The step of obtaining the three-dimensional structure of the blade according to the aerodynamic parameters and geometric parameters, and the profiles of the preset casing and hub.

[0045] Embodiment 2: This embodiment further limits the low-cost integrated centrifugal compressor diffuser three-dimensional structural design method provided in embodiment 1, and determines the contours of the casing and the hub according to the preset meridian flow channel and hub contours.

[0046] Implementation method three: This implementation method is a further limitation of the low-cost integrated centrifugal compressor diffuser three-dimensional structural design method provided in implementation method one. The blades are designed based on the centerline thickness method, and the three-dimensional structure of the blades is formed by controlling the center arc curvature distribution and the channel area distribution.

[0047] Embodiment 4: This embodiment provides a low-cost integrated centrifugal compressor diffuser modeling three-dimensional structure design device, the device comprising:

[0048] A module for collecting aerodynamic and geometric parameters of the diffuser inlet and outlet;

[0049] Module for collecting the profiles of the preset casing and hub;

[0050] According to the aerodynamic parameters and geometric parameters, as well as the profiles of the preset casing and hub, a module of the three-dimensional structure of the blade is obtained.

[0051] Embodiment 5: This embodiment provides a low-cost integrated centrifugal compressor diffuser modeling design method, the method comprising:

[0052] A step of optimizing the channel structural angle and area distribution of the three-dimensional structure obtained in the first embodiment;

[0053] Based on the optimized blade design, a three-dimensional diffuser structure is obtained by circumferential array.

[0054] Specifically,

[0055] The main purpose of this embodiment is to solve the technical problems of large flow loss, high processing cost and low reliability of conventional diffusers, so a low-cost integrated centrifugal compressor diffuser modeling design method is proposed. The diffuser manufactured using this modeling design method has the characteristics of high diffusion efficiency, convenient processing, low cost and strong structural reliability. This embodiment greatly improves the working performance and strength of the diffuser and reduces the processing and manufacturing cost.

[0056] The radial section and axial section blades of a conventional diffuser are built into an integrated structure, the turning section of the diffuser is transformed from a bladeless structure to a bladed structure, and the number of connecting structures is reduced.

[0057] According to the specific flow conditions, the channel area distribution and channel structural angle distribution are controlled to fine-tune the blade shape and optimize the flow conditions between the blades.

[0058] Based on the existing advanced CAD and CAM technologies, the constructed integrated diffuser structure is processed and manufactured.

[0059] include:

[0060] 1. Estimation of aerodynamic and geometric parameters

[0061] First, according to the airflow state parameters at the impeller outlet, the relevant aerodynamic thermodynamic calculation formulas are used to estimate the diffuser's inlet and outlet aerodynamic parameters and geometric parameters. These parameters include the diffuser's inlet and outlet areas, outlet total pressure, diffuser inlet and outlet heights, etc. This step provides basic data for subsequent designs, ensuring the rationality and efficiency of the subsequent design process.

[0062] 2. Meridian flow channel design and hub profile reverse analysis

[0063] After obtaining the inlet and outlet parameters, the casing profile is designed by combining straight lines and arcs according to the casing design requirements. Then, the hub profile is inversely calculated according to the required height distribution to complete the overall shape design of the meridian flow channel. This ensures the controllability and flexibility of the flow channel, allowing the airflow to pass smoothly through the diffuser.

[0064] 3. Blade design based on the centerline thickness method

[0065] Next, the blade profile is designed using a design method based on the centerline thickness method. By controlling the curvature distribution of the center arc line and the change in the channel area, the three-dimensional shape of the blade can be more finely controlled. The curvature distribution of the center arc line is determined by a 5th-order non-uniform B-spline curve, and the thickness distribution is generated by a Bezier curve and superimposed on the center arc line to form the final blade shape. At the leading and trailing edges of the blade, circular arcs and elliptical arcs are used for smooth processing to ensure smooth airflow.

[0066] 4. Channel structural angle and area distribution optimization

[0067] In order to further improve the aerodynamic performance of the diffuser, it is necessary to optimize the channel's structural angle and area distribution. By using a nearly linear channel structural angle distribution, the separation and backflow of the airflow can be reduced, thereby reducing flow losses. At the same time, the area distribution of the channel is controlled to be convex to ensure that the airflow can quickly complete the decompression process, reducing friction losses and local losses at turns.

[0068] 5. Acquisition and array of three-dimensional blade structures

[0069] After completing the design and optimization of the blades, the three-dimensional blade structure is modeled based on existing CAD / CAM technology. The optimized blades are arrayed along the circumference to form a complete three-dimensional structure of the diffuser. The integrated manufacturing method can reduce the number of manufacturing steps and the use of assembly parts, thereby reducing manufacturing costs and improving processing efficiency.

[0070] 6. Manufacturing and Assembly

[0071] Finally, the diffuser is processed as a whole using existing manufacturing technology to ensure that the designed three-dimensional blade structure can be accurately realized. Compared with the traditional segmented manufacturing and assembly method, one-piece manufacturing reduces the number of bolt connections, improves product reliability, and reduces overall production costs.

[0072] Embodiment 6: This embodiment provides a low-cost integrated centrifugal compressor diffuser modeling design device, the device comprising:

[0073] Module for optimizing the channel configuration angle and area distribution of the three-dimensional structure obtained in the first embodiment;

[0074] Based on the optimized blade design, a module with a complete three-dimensional diffuser structure is obtained by arraying along the circumferential direction.

[0075] Embodiment 7: This embodiment provides an integrated centrifugal compressor diffuser, and the diffuser is prepared by: using the three-dimensional diffuser structure obtained in embodiment 5, and processing the three-dimensional blade structure in an integrated manufacturing manner.

[0076] Embodiment 8: This embodiment provides a computer storage medium for storing a computer program. When the computer reads the computer program, the computer executes the method provided in embodiment 1.

[0077] Embodiment 9: This embodiment provides a computer, including a processor and a storage medium. When the processor reads a computer program stored in the storage medium, the computer executes the method provided in embodiment 1.

[0078] Embodiment 10: This embodiment provides a computer program product, which is a computer program. When the computer program is executed, the method provided in embodiment 1 is implemented.

[0079] Implementation Method XI: Combination Figure 1-7 This embodiment is described in detail by using specific examples to further describe the technical solution provided above. Specifically:

[0080] Modeling design method described step by step

[0081] This embodiment proposes a low-cost integrated centrifugal compressor diffuser modeling design method to solve the technical problems of conventional diffusers such as large flow loss, complex processing, high cost, and poor reliability. The following are the main steps of the modeling design method:

[0082] 1. Estimate the aerodynamic and geometric parameters of the diffuser inlet and outlet.

[0083] 2. Design the meridian runner and reverse the hub profile.

[0084] 3. Use the centerline thickness method for blade design.

[0085] 4. Optimize channel structure angle distribution and channel area distribution.

[0086] 5. Obtain and optimize the three-dimensional blade structure and complete manufacturing.

[0087] The detailed steps are as follows:

[0088] Step 1: Estimate the aerodynamic and geometric parameters of the diffuser inlet and outlet

[0089] According to the airflow state parameters and calculation formula at the impeller outlet, the aerodynamic parameters and geometric parameters of the diffuser inlet and outlet are estimated, including the inlet and outlet area, outlet total pressure, inlet and outlet height, etc.

[0090] These parameters provide the necessary basis for the subsequent blade profile and flow channel design.

[0091] Step 2: Design the meridian flow channel and reverse the hub profile

[0092] According to the method of casing profile design, select a profile structure that combines straight lines and arcs.

[0093] According to the required height distribution, the hub profile is inversely calculated to complete the shape design of the meridian channel. This step is aimed at improving the controllability and flexibility of the flow channel.

[0094] Step 3: Blade design (using the centerline thickness method)

[0095] The blade shape is controlled by the curvature distribution of the median camber line to achieve a more refined design. The median camber line uses a 5th-order non-uniform B-spline curve to give a given curvature distribution.

[0096] The thickness distribution is generated by a three-point controlled Bezier curve, which is superimposed on the mid-arc line to form the blade shape. The leading and trailing edges are smoothed with circular and elliptical arcs to ensure smooth flow.

[0097] Step 4: Optimize channel structure angle distribution and channel area distribution

[0098] The channel structure angle and channel area distribution directly affect the flow state of the airflow and the blade performance.

[0099] A nearly linear structural angle distribution is adopted to suppress the generation of reflux and separation zones, and the channel area distribution is controlled to be convex, ensuring that the friction loss during the pressure reduction process is minimized, while avoiding the boundary layer separation caused by excessive growth of the front section area.

[0100] Step 5: Obtain and optimize the 3D blade structure and complete manufacturing

[0101] Based on the parameters and designs obtained in the above steps, a three-dimensional model is constructed using existing CAD / CAM technology, and the optimized blades are arrayed circumferentially to generate a complete diffuser structure.

[0102] Finally, the diffuser blades were manufactured in an integrated manner, which significantly reduced the number of times the bolt structure was used and improved the reliability of the connection.

[0103] The embodiment is:

[0104] like Figure 1 As shown, this embodiment provides a centrifugal compressor diffuser with a low-cost integrated design. According to the problems of the conventional diffuser, it is considered to change the diffuser structure. The radial section, the bladeless turning section and the axial section in the conventional blade diffuser are integrated, wherein the radial section blade and the axial section blade are integrated to form an integrated structure blade.

[0105] Firstly, based on the basic principles of aerodynamic thermodynamics and empirical formulas, the aerodynamic parameters and geometric parameters of the diffuser inlet and outlet are calculated according to the state parameters of the impeller outlet airflow, including the diffuser inlet and outlet area, outlet total pressure, diffuser outlet diameter, and diffuser inlet and outlet height.

[0106] Secondly, for the design of the meridian flow channel, the conventional segmented diffuser adopts a constant blade height design, but the constant blade height design reduces the controllability of the diffuser flow channel. This example adopts a variable blade height design, which can make more precise adjustments to the diffuser flow channel, thereby increasing the flexibility and controllability of the design. The casing profile of this example adopts a construction method of a straight line part plus an arc part, such as Figure 4 After determining the casing profile, the hub profile is inversely calculated based on the height distribution to complete the shape design of the meridian channel.

[0107] For the diffuser camber line, the camber line can be indirectly generated by controlling the curvature distribution of the camber line, so as to achieve a more precise control effect on the blade profile. In order to facilitate the control of the curvature distribution of the camber line, a 5th-order non-uniform B-spline curve is first used to give the distribution of the camber line curvature along the arc length. The distribution of the turning angle along the arc length can be calculated through the curvature of the camber line, such as Figure 5As shown, S in the figure represents the dimensionless relative arc length. The De Boor recursive algorithm is used to generate a 5th-order non-uniform B-spline curve, and the curvature distribution of the middle arc line is generated through the recursive relationship. Before designing, the shape of the middle arc line needs to be constrained according to the existing parameters. The thickness distribution is generated by a Bezier curve with 3 control points. The curve is smoothed and the thickness distribution is superimposed on the middle arc line to generate the suction surface and pressure surface profiles to complete the initial design of the blade. The leading edge and trailing edge of the blade should be smoothed. This example uses circular arcs and elliptical arcs to smooth the leading edge and trailing edge of the blade, and processes them by giving the radius of the circular arc and the major axis length and major-minor axis ratio of the elliptical arc. Since the three-dimensional blade generated by this blade construction method cannot meet the existing work requirements, this example optimizes the blade profile by controlling the channel area distribution and the channel construction angle distribution to achieve higher performance of the diffuser.

[0108] The distribution of the channel construction angle affects the torsion angle of the blade, and thus affects the flow state of the airflow in the channel. If the distribution of the channel construction angle conforms to the rule of first fast and then slow, the front back of the blade forms a large positive curvature, and the airflow speed passing through here is greatly increased, forming a low-pressure area in front of the blade back. Due to the existence of the adverse pressure gradient, a large separation area will be formed behind the blade back, causing greater losses. If the distribution of the channel construction angle conforms to the rule of first slow and then fast, the channel construction angle changes too fast at the rear, and at the same time, the rear part of the meridian flow channel expands to form a convex surface at the blade root. These two unfavorable factors lead to a recirculation zone at the rear of the blade root, which is not conducive to the circulation of the fluid. In summary, this example adopts a distribution law of the channel construction angle that is close to linear, such as Figure 6 Compared with the above two distribution laws, the flow field between the blades is more superior, and the separation area and recirculation area at the rear are significantly suppressed.

[0109] In a conventional blade diffuser, a vortex area close to the dead water zone will appear at the blunt trailing edge of the radial wedge-shaped blade. The blades of the radial section and the axial section are connected in one piece, and the new blade formed extends from the diffuser inlet to the diffuser outlet, avoiding the blunt tail of the radial blade and eliminating the vortex area near the blunt trailing edge. During the design process, the local loss and mixing loss are reduced by adjusting the channel area distribution. If the airflow can complete the pressure reduction process faster, the speed will decrease rapidly, and the friction loss during the flow process and the local loss at the turning point will be reduced. Therefore, the area distribution of the channel is controlled to be an upward convex area distribution, such as Figure 7 As shown. However, in order to avoid the front section area growing too fast, which will cause the boundary layer to separate, the growth rate of the front section area should be controlled not to be too fast. Based on the above parameters, the centerline coordinates of the meridian flow channel are calculated to obtain the cross-sectional line of the diffuser's three-dimensional channel structure; the thickness of the blade needs to be checked to ensure that the suction surface and pressure surface of the blade do not intersect.

[0110] Finally, based on the above data, the optimized three-dimensional blade structure is obtained. According to the existing advanced CAD / CAM technology, the geometric parameters of the blade can be accurately controlled, and the obtained three-dimensional blades are arrayed along the circumferential direction to obtain all the blade structures on the diffuser. In this example, UG is used to construct a three-dimensional model for processing and manufacturing.

[0111] The technical solution provided by the present invention is further described in detail above through several specific implementation modes in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific implementation modes described above are not intended to be used as limitations on the present invention. Any reasonable modification and improvement of the present invention, combination of implementation modes and equivalent substitution within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A low-cost integrated centrifugal compressor diffuser three-dimensional structure design method, characterized in that: The method comprises: The steps of collecting aerodynamic parameters and geometric parameters of the diffuser inlet and outlet; Steps for collecting the profiles of the preset casing and hub; The step of obtaining the three-dimensional structure of the blade according to the aerodynamic parameters and geometric parameters, and the profiles of the preset casing and hub.

2. The low-cost integrated centrifugal compressor diffuser three-dimensional structure design method according to claim 1 is characterized in that: Determine the contours of the casing and hub based on the preset meridian runner and hub contours.

3. The low-cost integrated centrifugal compressor diffuser three-dimensional structure design method according to claim 1, characterized in that: The blade is designed based on the centerline thickness method, and the three-dimensional structure of the blade is formed by controlling the distribution of the center arc curvature and the channel area distribution.

4. A low-cost integrated centrifugal compressor diffuser modeling three-dimensional structure design device, characterized in that: The device comprises: A module for collecting aerodynamic and geometric parameters of the diffuser inlet and outlet; Module for collecting the profiles of the preset casing and hub; According to the aerodynamic parameters and geometric parameters, as well as the profiles of the preset casing and hub, a module of the three-dimensional structure of the blade is obtained.

5. A low-cost integrated centrifugal compressor diffuser design method, characterized in that: The method comprises: A step of optimizing the channel configuration angle and area distribution of the three-dimensional structure obtained in claim 1; Based on the optimized blade design, a three-dimensional diffuser structure is obtained by circumferential array.

6. Low-cost integrated centrifugal compressor diffuser design device, characterized in that: The device comprises: A module for optimizing the channel configuration angle and area distribution of the three-dimensional structure obtained in claim 1; Based on the optimized blade design, a module with a complete three-dimensional diffuser structure is obtained by arraying along the circumferential direction.

7. An integrated centrifugal compressor diffuser, characterized in that: The preparation method of the diffuser is: using the three-dimensional diffuser structure obtained according to claim 5, and processing the three-dimensional blade structure in an integrated manufacturing method.

8. A computer storage medium for storing a computing program, characterized in that: When the computer reads the computer program, the computer executes the method of claim 1.

9. A computer, comprising a processor and a storage medium, characterized in that: When the processor reads the computer program stored in the storage medium, the computer executes the method of claim 1 .

10. A computer program product, being a computer program, characterized in that When the computer program is executed, the method of claim 1 is implemented.

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