Radial air inlet cavity structure suitable for vortex suppression and drainage of turbomachinery

Abstract

The utility model discloses a radial air inlet chamber structure suitable for vortex suppression and drainage of turbomachinery, which is characterized in that the wall surface of a cylindrical flow guide basin in an air inlet chamber is arranged to be non-smooth, and particularly, the wall surface of the lower half part of the flow guide basin, which is easy to generate a falling vortex, is arranged to be a non-smooth wall surface structure, so that the purpose of suppressing fluid from flowing around the cylindrical flow guide basin is achieved; the effect of a falling vortex structure similar to a Karman vortex street is formed, and the non-smooth structure guides airflow to enter the blade grid at a proper angle, so that the flow loss in the air inlet cavity is reduced, the uniformity of airflow at the outlet of the cavity, namely the inlet of the blade grid, in the circumferential direction is improved, and the harm of low-frequency disturbance caused by unsteady flow of the air inlet cavity is eliminated; efficient, stable and safe operation of the turbomachinery is facilitated, and the turbomachinery air inlet cavity structure is suitable for systems of fire coal, fuel gas, aero-engines, compressed air energy storage, supercritical carbon dioxide power generation, organic working medium Rankine cycle, natural gas excess pressure utilization, geothermal energy utilization and the like.

Description

Technical Field

[0001] The utility model belongs to the technical field of the air inlet structure of impeller machinery, and relates to an air inlet chamber structure for impeller machinery. Specifically, it is a radial air inlet chamber structure that can suppress the shedding vortex and guide the air flow direction. This structure suppresses the formation of the shedding vortex and improves the air flow organization form by setting a non-smooth cylindrical wall surface on the lower half surface of the guide basin, thereby improving the aerodynamic performance and safety performance of the impeller machinery. Background Art

[0002] Limited by the system structure and the layout of the air path pipeline, the inlet air flow of impeller machinery such as axial flow turbines or centrifugal compressors usually enters through a radial air inlet chamber. The radial air inlet chamber and the internal guide basin form a chamber channel that turns the radially entering air flow and axially discharges it into the cascade. Such a sharp change in the flow path will inevitably cause the separation and reattachment of the air flow, thus forming a complex vortex structure in the air inlet chamber. Therefore, the design of this channel has an important impact on the overall performance of the impeller machinery.

[0003] However, in the prior art, there are many problems in the design of the radial air inlet chamber. First of all, there are usually many vortex structures in the air inlet chamber. Especially, after the air flow passes through the cylindrical guide basin, a shedding vortex similar to the Karman vortex street of cylinder flow will be formed. This vortex structure will not only generate large flow losses, reduce the air inlet efficiency, but also cause the circumferential distribution of the aerodynamic parameters at the outlet of the radial air inlet chamber to be uneven. This unevenness makes the flow field in the cascade channel disordered and reduces the turbine performance. At the same time, the formation of the shedding vortex will bring additional disturbance frequency signals to the machine. When these disturbance frequencies are close to the natural frequencies of the blades, it may induce the resonance of the blades, resulting in the problem of high cycle fatigue of the blades, shortening the blade life, and even may cause the blade to break, endangering the safe operation of the unit. In addition, the complex flow characteristics and the air flow turning process in the radial air inlet chamber will cause a series of other problems. For example, when the air flow flows around the surface of the cylindrical guide basin, local flow velocity changes and pressure fluctuations will occur, further intensifying the instability of the air flow. This instability not only affects the uniformity of the air flow, but also has an adverse impact on the air inlet angle and flow distribution of the air flow in the downstream cascade, reducing the working efficiency of the entire impeller machinery.

[0004] In the prior art, some improvement measures attempt to reduce the vortex and flow losses by optimizing the geometric shape of the air inlet chamber or the surface characteristics of the guide basin. However, these improvement measures have limited effects in practical applications, and often require major modifications to the overall structure of the impeller machinery, increasing the complexity and cost of design and manufacturing. Especially during the retrofit process of existing equipment, it is very difficult to make large-scale changes due to space and the original structure limitations.

[0005] Therefore, how to effectively suppress the shed vortices and flow losses in the intake chamber without significantly changing the existing structure, improve the uniformity and stability of the air flow, and enhance the aerodynamic performance and safety of the turbomachinery is a technical problem that urgently needs to be solved in the field of the intake structure design of turbomachinery. Summary of the Invention

[0006] In view of the above-mentioned defects and deficiencies in the prior art, where there are many vortex structures in the radial intake chamber, especially the shed vortices similar to the von Karman vortex street formed after passing through the cylindrical guide basin, resulting in flow losses, uneven circumferential distribution of the aerodynamic parameters at the outlet of the intake chamber, disordered flow field in the cascade passage, and possible high-cycle fatigue of the blades, etc., to solve at least one of the above-mentioned and other technical problems in the prior art, the present invention aims to provide a radial intake chamber structure for turbomachinery that can suppress shed vortices. By setting the lower half surface of the guide basin inside the intake chamber as a non-smooth cylindrical wall surface, the formation of shed vortices in the flow around the cylinder can be suppressed, the air flow organization form inside the intake chamber can be changed, and the aerodynamic performance and safety performance are better. At the same time, the groove-shaped or textured structure on the surface of the guide basin can play a better role in controlling and guiding the air flow. By designing groove-shaped or textured structures with different angles according to the circumferential position of the downstream cascade (generally the guide vane), the matching degree between the air flow angle at the outlet of the chamber and the air flow angle at the inlet of the downstream cascade can also be adjusted, and the non-uniformity of the aerodynamic parameters at the outlet of the intake chamber can be improved.

[0007] To achieve its technical purpose and solve its technical problems, the present invention adopts the following technical solutions:

[0008] A radial intake chamber structure for vortex suppression and flow diversion in turbomachinery, which is used to improve the intake air uniformity at the inlet of the turbomachinery and enhance the operation safety and reliability of the unit, at least includes a radial intake chamber and a cylindrical guide basin. Specifically:

[0009] The cylindrical guide basin is located inside the radial intake chamber. The wall surface of the intake chamber and the wall surface of the guide basin jointly form a radial air flow passage. The fluid enters the radial intake chamber radially and is axially discharged into the impeller inlet after being guided by the cylindrical guide basin.

[0010] The guide basin includes an upper part of the guide basin and a lower part of the guide basin. The wall surface of the lower part of the guide basin is set as a non-smooth circular ring wall surface, and a groove-shaped structure, a textured structure or a concave-convex hole structure is arranged on the non-smooth circular ring wall surface for suppressing the von Karman vortex street shed vortex structure formed behind the guide basin.

[0011] Preferably, the maximum depth of the non-smooth structure provided on the non-smooth circular ring wall surface is 0.001 - 0.05D, where D is the characteristic length of the cylindrical cross-section of the guide basin.

[0012] Furthermore, the non-smooth circular ring wall surface is composed of groove-shaped structures. The cross-section of the groove-shaped structure is arc-shaped, triangular, rectangular, trapezoidal, M-shaped or sinusoidal, and the geometric parameters of the cross-section of the groove-shaped structure are optimized according to the size of the flow guiding basin, operating conditions and processing difficulty.

[0013] Furthermore, the non-smooth circular ring wall surface is composed of groove-shaped structures. The cross-section of the groove-shaped structure is a composite groove shape with small grooves attached to both sides of the large groove. Among them, the structural depth of the small groove is 0.001 - 0.05D, and the structural depth of the large groove is 1.2 - 10 times that of the small groove.

[0014] Furthermore, there are at least two groove-shaped structures. The shape of each groove-shaped structure is the same and they are continuously distributed along the axis. The depth and width of each groove-shaped structure are consistent to ensure uniform distribution of the airflow on the lower surface of the entire flow guiding basin.

[0015] Furthermore, each groove-shaped structure is continuously distributed in an arc curve or a spiral shape at an angle deviating from the axis or the cylindrical busbar of the flow guiding basin by -30° to 30°. The deviation angle or spiral angle is the same as the inlet airflow angle of the cascade, and the groove-shaped structures are continuously distributed circumferentially or axially symmetrically on both sides of the radial center line of the flow guiding basin, so as to control the inlet airflow of the cascade within a better angle of attack range.

[0016] Furthermore, the groove-shaped structures can be set to be discontinuously distributed along the axis from the inlet to the outlet of the flow guiding basin, and can be evenly arrayed at different circumferential positions. The distribution quantity and spacing can be changed according to the number of blades and the pitch.

[0017] Furthermore, the non-smooth circular ring wall surface is set to be discontinuously distributed along the axis from the inlet to the outlet of the flow guiding basin. The non-smooth structures arranged on the non-smooth circular ring wall surface are composed of regular texture structures, and the non-smooth structures are evenly arrayed at different circumferential positions on the wall surface. The distribution quantity and spacing can be changed according to the number of blades and the pitch.

[0018] Furthermore, the non-smooth circular ring wall surface is set to be discontinuously distributed along the axis from the inlet to the outlet of the flow guiding basin. The non-smooth structures arranged on the non-smooth circular ring wall surface are composed of concave-convex hole structures, and the concave-convex hole structures are spherical, cylindrical or polyhedral shaped structures, and the non-smooth structures are evenly arrayed at different circumferential positions on the wall surface.

[0019] Preferably, the wall surface structure of the upper part of the flow guiding basin can be retained as a smooth circular ring wall surface, or set to be the same or different non-smooth circular ring wall surface structures as that of the lower part of the flow guiding basin, and the wall surface structure of the upper part of the flow guiding basin can be optimized according to specific flow characteristics and working conditions.

[0020] Compared with the prior art, the radial air inlet chamber structure applicable to vortex suppression and flow diversion of impeller machinery of the present utility model has the following beneficial and remarkable technical effects:

[0021] (1) The lower part of the flow guiding basin of the present utility model has a non-smooth cylindrical wall surface, which can effectively avoid the radial air flow at the inlet impacting the lower part of the flow guiding basin to form unstable shedding vortices similar to the Karman vortex street, thereby reducing the flow loss in the air inlet chamber and improving the overall efficiency of the system. In addition, this design also avoids the additional low-frequency disturbance brought by the vortex, which is beneficial to improving the efficiency and safety performance of the unit.

[0022] (2) The groove structure, texture structure or concave-convex hole structure on the non-smooth wall surface adopted by the present utility model can also be arranged according to the circumferential distribution characteristics of the downstream cascade, realizing better control and guidance of the air flow, reducing the non-uniformity of the inlet air flow in terms of air flow angle and mass flow rate, and the aerodynamic performance of the unit is better. The present utility model

[0023] (3) The structural design of the present utility model is simple and convenient to process. Only by appropriately non-smoothly treating the surface of the existing flow guiding basin without changing the main structure of the impeller machinery, the flow loss generated by the shedding vortex in the air inlet chamber can be effectively reduced and the uniformity of the inlet air flow of the impeller machinery can be improved. Therefore, it has high processing feasibility and economy. And this structure is not only easy to implement, but also can be widely applied to the radial air inlet structure of impeller machinery, with strong applicability and popularization value. Description of the Drawings

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0025] Figure 1 It is a side view of the prototype structure of the impeller machinery air inlet chamber of the present utility model;

[0026] Figure 2 It is a side view (a) and a front view (b) of the internal flow guiding basin of the air inlet chamber of the present utility model, in which continuous semicircular channels are uniformly distributed along the flow direction at the lower part of the flow guiding basin;

[0027] Figure 3 It is a side view (a) and a front view (b) of the internal flow guiding basin of the air inlet chamber of the present utility model, in which non-continuous triangular channels are uniformly distributed along the flow direction at the lower part of the flow guiding basin;

[0028] Figure 4This is the front view of the lower part of the flow guide basin inside the air intake chamber of the present utility model, which has groove-shaped structures with different cross-sectional types. Among them, semi-circular channels are arranged non-uniformly along the flow direction and along the generatrix direction at the lower part of the flow guide basin. Among them, (a) is circular, (b) is triangular, (c) is rectangular, and (d) is M-shaped.

[0029] Figure 5 This is a schematic diagram of the present utility model showing a quasi-parallelogram cross-section and an arc-shaped channel (a) with a certain angle deviation from the generatrix at the lower part of the flow guide basin inside the air intake chamber, and quasi-parallelogram cross-section and arc-shaped channels (b) symmetrically distributed on both sides of the lower part of the flow guide basin.

[0030] Explanation of reference numerals in the drawings:

[0031] Radial air intake chamber 1, air intake chamber inlet 1-1, air intake chamber outlet 1-2, flow guide basin 2, upper part of the flow guide basin 2-1, lower part of the flow guide basin 2-2, non-smooth structure 3. Specific implementation manners

[0032] The following details the embodiments of the present utility model. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present utility model and should not be construed as a limitation to the present utility model.

[0033] Aiming at the defects and deficiencies in the prior art that there are many vortex structures in the radial air intake chamber, especially the shedding vortices similar to the von Kármán vortex street formed after passing through the cylindrical flow guide basin, resulting in flow losses, uneven circumferential distribution of aerodynamic parameters at the air intake chamber outlet, disordered flow field in the cascade channel, and possible high-cycle fatigue of the blades, etc., in order to solve the above technical problems in the prior art, the present utility model aims to provide a radial air intake chamber structure applicable to turbomachinery that can suppress shedding vortices.

[0034] As a specific example, Figure 1 、 2Shows a preferred embodiment of the intake chamber structure of the present utility model that can suppress shedding vortices. Specifically, the radial intake chamber structure of the present utility model applicable to vortex suppression and flow guiding in turbomachinery includes a radial intake chamber 1 and a cylindrical guide basin 2. The cylindrical guide basin 2 is located inside the radial intake chamber 1. The wall surface of the radial intake chamber 1 and the wall surface of the guide basin 2 jointly form a radial air flow channel. The fluid enters the intake chamber inlet 1-1 radially, and after being guided by the cylindrical guide basin 2, it is axially discharged from the intake chamber outlet 1-2 into the impeller inlet. The guide basin 2 includes an upper part 2-1 and a lower part 2-2 of the guide basin. The wall surface of the lower part 2-2 of the guide basin is set as a non-smooth circular ring wall surface, and non-smooth structures 3 are arranged on the non-smooth circular ring wall surface. The non-smooth structures 3 can be groove-shaped structures, texture structures or concave-convex hole structures, which are used to destroy the shedding vortex structure of the Karman vortex street formed behind the guide basin 2.

[0035] In some preferred examples, for the non-smooth structures 3 arranged on the non-smooth circular ring wall surface of the lower part 2-2 of the guide basin, the maximum depth is 0.001 - 0.05D, where D is the characteristic length of the cylindrical cross-section of the guide basin. By controlling the depth of the non-smooth structures, the formation of the Karman vortex street can be effectively suppressed, and at the same time, the main flow direction of the air flow will not be significantly affected. The depth of the non-smooth structures can be optimized according to the specific dimensions and working conditions of the turbomachinery to achieve the best vortex suppression effect and the balance of flow losses.

[0036] In some preferred examples, the non-smooth circular ring wall surface of the lower part 2-2 of the guide basin is composed of groove-shaped structures. The cross-section of the groove-shaped structures can be arc-shaped, triangular, rectangular, trapezoidal, M-shaped or sinusoidal, and the geometric parameters of the cross-section of the groove-shaped structures are optimized and designed by comprehensively considering the guide basin size, operating conditions and processing difficulty. Groove-shaped structures with different cross-section shapes can produce different flow disturbance effects, so as to effectively suppress the Karman vortex street under different working conditions. In addition, the cross-section of the groove-shaped structures can also be a composite groove-shaped structure with small grooves on both sides of a large groove. Among them, the structural depth of the small grooves is 0.001 - 0.05D, and the depth of the large groove is 1.2 - 10 times that of the small grooves. The composite groove-shaped structure can produce flow disturbances at different scales and effectively suppress the formation of vortex structures at different scales. At the same time, the depth ratio of the large and small grooves can be optimized according to the fluid characteristics and working conditions to achieve the best vortex suppression effect.

[0037] In some preferred examples, there are at least two groove-shaped structures. The shape of each groove-shaped structure is the same and they are continuously distributed along the axial direction. The depth and width of each groove-shaped structure are consistent to ensure that the air flow is evenly distributed on the entire surface of the lower part of the guide basin. The setting of multiple groove-shaped structures can form continuous flow disturbances on the surface of the guide basin and effectively destroy the formation of large-scale vortex structures. The number and distribution of the groove-shaped structures can be optimized according to the size of the guide basin and the expected flow characteristics to achieve the best vortex suppression effect.

[0038] Figure 2 In the shown preferred examples, the non-smooth structure 3 at the lower part 2-2 of the flow guiding basin is a semi-circular groove. The structural shape of each semi-circular groove is the same, continuously distributed along the generatrix direction of the flow guiding basin, and evenly distributed at a certain angle along the circumferential direction. The cross-sectional radius of the semi-circular groove can be designed in combination with different impeller diameters, or can be arranged to be recessed inward along the surface of the flow guiding basin, so as to improve the uniformity of the air flow and the flow guiding efficiency without affecting the original flow area. In addition, the number and spacing of the semi-circular grooves can be optimized and adjusted according to specific operating conditions to achieve the best aerodynamic performance and operating effect.

[0039] In some preferred examples, the groove-shaped structure can be set to be discontinuously distributed along the axial direction from the inlet to the outlet of the flow guiding basin, and can be evenly arrayed and distributed at different circumferential positions. The distribution quantity and spacing can be changed according to the number of blades and the pitch to achieve the best vortex suppression effect. The discontinuously distributed groove-shaped structure can generate local flow disturbances at different axial positions, effectively suppressing the formation and development of the von Kármán vortex street.

[0040] As a specific example, such as Figure 3 shown, the non-smooth structure 3 at the lower part 2-2 of the flow guiding basin is a discontinuous triangular channel with evenly distributed along the flow direction. The structural shape of each discontinuous triangular channel is the same, evenly distributed at a certain angle along the circumferential direction, but spaced along the generatrix direction of the flow guiding basin. The angle and depth of each discontinuous triangular channel can be optimized according to the specific impeller diameter and operating conditions to ensure that the vortex structure can be effectively destroyed, the flow loss can be reduced, and the aerodynamic performance can be improved. The design of the discontinuous triangular channel helps to achieve the best air flow guiding and control effects under different working conditions, while ensuring that the flow area of the intake chamber is not significantly affected.

[0041] In further preferred examples, the non-smooth structure 3 arranged on the non-smooth circular ring wall surface can also be composed of regular texture structures. The non-smooth structure 3 is set to be discontinuously distributed along the axial direction from the inlet to the outlet of the flow guiding basin, and the non-smooth structure 3 is evenly arrayed and distributed at different circumferential positions on the wall surface. The distribution quantity and spacing can be changed according to the number of blades and the pitch. At the same time, the non-smooth structure 3 can also be composed of non-smooth structures or concave-convex hole structures. The concave-convex hole structures are spherical, cylindrical or polyhedral modeling structures, and the non-smooth structures are evenly arrayed and distributed at different circumferential positions on the wall surface.

[0042] As a specific example, such as Figure 4 shown, the cross-sections of the non-smooth structure 3 at the lower part 2-2 of the flow guiding basin are respectively set as Figure 4 the circle shown in (a), Figure 4 the triangle shown in (b), Figure 4 the rectangle shown in (c),Figure 4 (d) The M shape shown, the groove-shaped structures and texture structures with different cross-sectional shapes can be arranged continuously according to Figure 2 or can be arranged at intervals according to Figure 3 settings.

[0043] In some preferred examples, each groove-shaped structure is distributed in an arc curve or a spiral line continuously at an angle deviating from the axial direction or the cylindrical busbar of the flow guiding basin by -30° to 30°. The deviation angle or the spiral angle is the same as the inlet air flow angle of the cascade, and the groove-shaped structures are circumferentially continuously distributed or axially symmetrically distributed on both sides of the radial center line of the flow guiding basin, so as to control the inlet air flow of the cascade within a better angle of attack range.

[0044] As a specific example, as shown in Figure 5 , the non-smooth structure 3 at 2-2 of the lower part of the flow guiding basin is arranged along the surface curve of the flow guiding basin. As shown in Figure 5 (a), it is distributed in an arc line, or as shown in Figure 5 (b), the left side is distributed in an arc line, and the right side is axially symmetric with the left side along the radial direction, so as to deflect and guide the fluid, and can better adapt to the air flow angles at different circumferential positions at the inlet of the downstream cascade.

[0045] In some preferred examples, the wall structure of the upper part 2-1 of the flow guiding basin can be retained as a smooth circular ring wall, or can be set as a non-smooth circular ring wall structure the same as or different from that of the lower part 2-2 of the flow guiding basin, and the wall structure of the upper part 2-1 of the flow guiding basin can be optimized according to specific flow characteristics and working conditions to achieve the best flow control effect on the entire surface of the flow guiding basin 2. The choice of smooth or non-smooth structure is weighed according to the upstream air flow characteristics and the requirements of the downstream cascade inlet to achieve the best flow guiding and vortex suppression effects.

[0046] In summary, the air inlet chamber structure capable of suppressing shedding vortices in the present utility model can improve the non-uniformity of the air inlet at the inlet of the turbomachine, meet the requirements of the efficient operation of the turbomachine, enhance the safety and reliability of the unit operation, and at the same time has processing feasibility and broad application prospects.

[0047] The series of detailed descriptions listed above are only specific descriptions of the feasible embodiments of the present utility model, and they are not intended to limit the protection scope of the present utility model. Any equivalent embodiments or changes made without departing from the technical spirit of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A radial intake chamber structure suitable for suppressing vortex and guiding flow in turbomachinery, at least comprising a radial intake chamber and a cylindrical guide basin, characterized in that: The cylindrical guide basin is located inside the radial intake chamber. The wall surface of the intake chamber and the wall surface of the guide basin jointly form a radial air flow channel. The fluid enters the radial intake chamber radially and is axially discharged into the impeller inlet after being guided by the cylindrical guide basin. The guide basin comprises an upper part of the guide basin and a lower part of the guide basin. The wall surface of the lower part of the guide basin is set as a non-smooth circular ring wall surface, and a groove structure, a texture structure or a concave-convex hole structure is arranged on the non-smooth circular ring wall surface for suppressing the shedding vortex structure of the Karman vortex street formed behind the guide basin.

2. The radial intake chamber structure according to claim 1, characterized in that, The maximum depth of the non-smooth structure arranged on the non-smooth circular ring wall surface is 0.001 - 0.05D, where D is the characteristic length of the cylindrical cross-section of the guide basin.

3. The radial intake chamber structure according to claim 2, characterized in that, The non-smooth circular ring wall surface is composed of groove structures. The cross-section of the groove structure is arc-shaped, triangular, rectangular, trapezoidal, M-shaped or sinusoidal, and the geometric parameters of the cross-section of the groove structure are optimized according to the size of the guide basin, the operating conditions and the processing difficulty.

4. The radial intake chamber structure according to claim 2, characterized in that, The non-smooth circular ring wall surface is composed of groove structures. The cross-section of the groove structure is a composite groove shape with small grooves attached to both sides of a large groove. Among them, the structure depth of the small groove is 0.001 - 0.05D, and the structure depth of the large groove is 1.2 - 10 times that of the small groove structure depth.

5. The radial intake chamber structure according to claim 3 or 4, characterized in that, There are at least two groove structures. The shape of each groove structure is the same and they are all continuously distributed along the axis. The depth and width of each groove structure are consistent.

6. The radial intake chamber structure according to claim 3 or 4, characterized in that, Each groove structure is continuously distributed in an arc curve or a spiral shape at an angle deviating -30° to 30° from the axis or the cylindrical bus of the guide basin. The deviation angle or the spiral angle is the same as the inlet air flow angle of the cascade, and the groove structures are continuously distributed circumferentially or axially symmetrically on both sides of the radial center line of the guide basin.

7. The radial intake chamber structure according to claim 3 or 4, characterized in that The groove structures are arranged in a non-continuous distribution along the axis from the inlet to the outlet of the guide basin and are evenly arrayed at different circumferential positions. The distribution quantity and spacing are changed according to the number of blades and the pitch.

8. The radial intake chamber structure according to claim 2, wherein, The non-smooth circular ring wall surface is arranged in a non-continuous distribution along the axis from the inlet to the outlet of the guide basin. The arranged non-smooth structure is composed of regular texture structures. The non-smooth structures are evenly arrayed at different circumferential positions on the wall surface, and the distribution quantity and spacing are changed according to the number of blades and the pitch.

9. The radial intake chamber structure according to claim 2, characterized in that, The non-smooth circular ring wall surface is arranged in a non-continuous distribution along the axis from the inlet to the outlet of the guide basin. The arranged non-smooth structure is composed of concave-convex hole structures. The concave-convex hole structures are spherical, cylindrical or polyhedral modeling structures, and the non-smooth structures are evenly arrayed at different circumferential positions on the wall surface.

10. The radial intake chamber structure according to claim 1, characterized in that, The wall surface structure of the upper part of the guide basin is reserved as a smooth circular ring wall surface or set as a non-smooth circular ring wall surface structure same as or different from that of the lower part of the guide basin, and the wall surface structure of the upper part of the guide basin is optimized according to specific flow characteristics and working conditions.

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