CN112784370A - Design method of space guide vane of multistage centrifugal pump - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
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Abstract
The invention discloses a design method of a space guide vane of a multistage centrifugal pump, which comprises the steps of establishing an impeller model; determining a space guide vane initial parameter according to the impeller model and the single-stage performance parameter to obtain an initial model of the space guide vane; combining an impeller model and a preliminary model of the space guide vane into a first stage, optimizing preliminary parameters of the space guide vane, and performing fluid simulation on the stage; adjusting the preliminary model of the space guide vane according to the single-stage fluid simulation result until a preset single-stage condition is met; adjusting the preliminary model of the space guide vane according to the mutual influence between stages, and performing multi-stage fluid simulation; and adjusting the preliminary model of the space guide vane according to the multistage fluid simulation result until a preset multistage condition is met, and obtaining a final space guide vane model. Therefore, the space guide vane of the horizontal sectional type multistage centrifugal pump meeting the actual requirement can be obtained by the method.
Description
Technical Field
The invention relates to the technical field of multistage centrifugal pumps, in particular to a design method of a space guide vane of a multistage centrifugal pump.
Background
The main flow passage components of the vane pump are a water suction chamber, an impeller and a water pumping chamber. The pumping chamber is located at the periphery of the impeller and is used for collecting the liquid flowing out of the impeller and uniformly sending the liquid into a next stage or a discharge pipe, and most kinetic energy of the liquid at the outlet of the impeller is converted into pressure energy under the condition that the loss of the liquid is as small as possible in the process of collecting the liquid. The pumping chamber mainly comprises a vortex chamber (namely a spiral pumping chamber), a radial guide vane, a space guide vane, an axial flow pump guide vane and the like.
The space guide vane is a common water pressing chamber, and the front guide vane and the back guide vane are combined into a whole. Since the blades are spatially twisted, they are referred to as spatial vanes. Compared with the radial guide vane commonly used in the horizontal sectional type multistage pump, the space guide vane forms an independent flow passage from the inlet to the outlet, so that the hydraulic loss of fluid in the flow passage, including impact loss and mixing loss, is reduced. The efficiency of the horizontal sectional type multistage pump is improved. According to the CFD analysis result, the efficiency of the same centrifugal impeller (provided with the space guide vane is higher than that of the stage provided with the existing radial guide vane by more than 2 percent compared with that of a single stage (namely the combination of one impeller and one space guide vane) at the design working condition point.
However, the existing space guide vane is mainly used for various vertical pumps, and the existing space guide vane is provided with various well pumps, submersible pumps and condensate pumps in multiple stages, a single-stage guide vane mixed flow pump and the like. The space guide vanes used by these vertical pumps are mainly characterized by large axial length and small radial dimension. Because the axial length of the existing space guide vane is large, the existing space guide vane can not be used for a horizontal sectional type multistage centrifugal pump.
Disclosure of Invention
The invention aims to provide a design method of a space guide vane of a multistage centrifugal pump, which aims to solve the problem that the existing space guide vane has large axial length and cannot be used for a horizontal sectional multistage centrifugal pump.
According to an embodiment of the present invention, there is provided a method of designing a space guide vane of a multistage centrifugal pump, including:
establishing an impeller model;
determining a space guide vane initial parameter according to the impeller model and the single-stage performance parameter to obtain an initial model of the space guide vane;
combining the impeller model and the preliminary model of the space guide vane into a first stage, optimizing the preliminary parameters of the space guide vane, and performing fluid simulation on the stage;
adjusting the preliminary model of the space guide vane according to a single-stage fluid simulation result until a preset single-stage condition is met;
adjusting the preliminary model of the space guide vane according to the mutual influence between stages, and performing multi-stage fluid simulation;
and adjusting the preliminary model of the space guide vane according to the multi-stage fluid simulation result until a preset multi-stage condition is met, and obtaining a final space guide vane model.
Specifically, the determining a preliminary parameter of the spatial guide vane according to the impeller model and the single-stage performance parameter includes:
calculating to obtain the inlet width of the space guide vane according to the outlet width of the impeller model and the following formula;
b3＝b2+(0～2mm)；
wherein b2 is the outlet width of the impeller model, b3 is the inlet width of the space guide vane;
calculating to obtain the inlet radius of the space guide vane model according to the following formula;
R3＝(1.02～1.05)*R2；
wherein R2 is the exit radius of the impeller model and R3 is the inlet radius of the space guide vane;
according to the number of the blades of the impeller model, the number of the blades of the space guide vane is determined according to the following formula;
zi＝z-(1～3)；
wherein zi is the number of blades of the space guide vane, z is the number of blades of the impeller model, and zi and z are coprime;
determining the installation angle of the inlet blade of the space guide blade according to the installation angle of the blade outlet of the impeller model and the following formula,
βb3＝βb2-(1°～7°)；
wherein β b3 is the installation angle of the inlet blade of the space guide vane, β b2 is the blade outlet installation angle of the impeller model;
determining the maximum thickness of the blades of the space guide vane according to the following formula according to the minimum thickness of the blades of the space guide vane,
δmax＝(2～4)*δ1；
wherein δ max is the blade maximum thickness and δ 1 is the blade minimum thickness of the space vane.
Specifically, the minimum thickness of the blades of the space guide blade is 3-6mm, the security protection angle of the outlet blades of the space guide blade is 90 degrees, and the included angle between the tail edge line of the rear cover plate of the space guide blade and the axis is 20-45 degrees;
the blade outlet width, the blade outlet radius, the inlet width and the inlet radius of the space guide blade satisfy the following relations,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of the space guide vane, R4 is the blade outlet radius of the space guide vane, b3 is the inlet width of the space guide vane, R3 is the inlet radius of the space guide vane,
the cross section of overflowing among the blades of the space guide vane is a rectangular cross section.
The embodiment of the invention provides a design method of a space guide vane of a multistage centrifugal pump, which is used for respectively carrying out fluid simulation on a single stage and multiple stages and then carrying out parameter adjustment and optimization according to a simulation structure, so that the space guide vane of a horizontal sectional type multistage centrifugal pump meeting the actual requirements can be obtained.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart of a method for designing a space guide vane of a multistage centrifugal pump provided by the invention;
fig. 2 is a block diagram of an impeller and space vanes.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
According to an embodiment of the present invention, as shown in fig. 1 and 2, there is provided a method of designing a space guide vane of a multistage centrifugal pump, including:
step 11: and establishing an impeller 1 model.
According to the existing two-dimensional hydraulic diagram of the centrifugal impeller 1, drawing marking data is read or geometric parameters and information required by hydraulic design are measured by a ruler. Such as the inlet width b1 of the impeller 1, the outlet width b2 of the impeller 1, the inlet diameter D1 of the impeller 1, the outlet diameter D2 of the impeller 1, the radius R1H of the blade root at the inlet of the impeller 1, the inlet attack angle i at different radii from the blade root to the blade tip, the number z of blades, the thickness δ 1 of the blade inlet edge of the impeller 1, the actual thickness δ of the blade of the impeller 1, the blade inlet setting angle β b1 of the impeller 1, the blade outlet setting angle β b2 of the impeller 1, the line type of the meridian line, the coordinates of the connection point of each section of curve, the curvature of the line, and the like.
And (3) carrying out three-dimensional modeling on the blades of the impeller 1 according to the two-dimensional water map of the conventional centrifugal impeller 1 by using three-dimensional modeling software. First, points are taken on the hydraulic diagram according to axial and plane sectional lines of the pressure surface, and each axial and plane sectional line generates a multiple ibl file. Thereafter, the suction surface ibl file was extracted in the same manner. The ibl file is read in the three-dimensional modeling software, and the pressure surface and the suction surface curved surfaces of the blade of the impeller 1 are generated. Then leading in the molded lines of the front cover plate and the rear cover plate and the lines of the front edge and the tail edge, wherein the total number of the lines is 4, respectively making 4 curved surfaces around the rotating shaft, and extending the pressure surface and the suction surface of the blade. And then, combining and materializing the connecting curved surfaces to generate a three-dimensional impeller 1 blade, and rounding the front edge of the blade to obtain the impeller 1 blade which finally conforms to the hydraulic diagram.
And after the three-dimensional modeling is completed, deriving the x.igs file of the three-dimensional model of the blade of the impeller 1 from the three-dimensional modeling software. After the blades of the impeller 1 (piece 1) are read in by using three-dimensional design software, the impeller 1 is finely adjusted according to the obtained geometric parameters of the existing impeller 1, the length and the angle numerical value are rounded, and the model in the three-dimensional design software is completely consistent with the existing actual impeller 1.
Step 12: and determining the initial parameters of the space guide vane 2 according to the impeller 1 model and the single-stage performance parameters to obtain an initial model of the space guide vane 2.
Specifically, according to the impeller 1 model and the single-stage performance parameters, determining the preliminary parameters of the space guide vane 2, including:
according to the outlet width of the impeller 1 model, calculating to obtain the inlet width of the space guide vane 2 according to the following formula;
b3＝b2+(0～2mm)；
wherein b2 is the outlet width of the impeller 1 model, b3 is the inlet width of the space guide vane 2;
according to the following formula, calculating to obtain the inlet radius of the space guide vane 2 model;
R3＝(1.02～1.05)*R2；
wherein R2 is the exit radius of the impeller model, R3 is the entrance radius of the space guide vane 2;
according to the number of the blades of the impeller 1 model, the number of the blades of the space guide vane 2 is determined according to the following formula;
zi＝z-(1～3)；
wherein zi is the number of blades of the space guide vane 2, z is the number of blades of the impeller 1 model, and zi and z are coprime;
according to the blade outlet installation angle of the impeller 1 model, the installation angle of the inlet blade of the space guide blade 2 is determined according to the following formula,
βb3＝βb2-(1°～7°)；
wherein, β b3 is the installation angle of the inlet blade of the space guide vane 2, and β b2 is the installation angle of the blade outlet of the impeller 1 model;
according to the minimum thickness of the blades of the space guide vane 2, the maximum thickness of the blades of the space guide vane 2 is determined according to the following formula,
δmax＝(2～4)*δ1；
where δ max is the maximum thickness of the blade, and δ 1 is the minimum thickness of the blade of the space vane 2.
The minimum thickness of the blades of the space guide blade 2 is 3-6mm, the security protection angle of the outlet blades of the space guide blade 2 is 90 degrees, and the included angle between the tail edge line of the rear cover plate of the space guide blade 2 and the axis is 20-45 degrees.
The blade outlet width, the blade outlet radius, the inlet width and the inlet radius of the space guide blade 2 satisfy the following relations,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of space guide vane 2, R4 is the blade outlet radius of space guide vane 2, b3 is the inlet width of space guide vane 2, and R3 is the inlet radius of space guide vane 2.
Step 13: combining the impeller 1 model and the preliminary model of the space guide vane 2 into a first stage, optimizing the preliminary parameters of the space guide vane 2, and performing fluid simulation on the stage.
In the three-dimensional design software, the impeller 1 and the spatial guide vane 2 are combined into one stage and designed together. And after the design is finished with a single-stage preliminary scheme, performing single-stage CFD analysis, namely performing fluid simulation analysis. When calculated with CFD software, the mesh quality should satisfy: the orthogonality is more than or equal to 20 degrees, the length-width ratio is less than or equal to 1000, and the extension ratio is less than or equal to 3. In order to ensure that the physical quantity of the inlet of the calculation domain is closer to the actual value and the physical quantity of the outlet of the calculation domain is more stable, so that the calculation result is more accurate, the inlet and the outlet of the calculation domain need to extend upwards and downwards respectively. The y + value is changed by modifying the wall distance of the mesh until the y + value is within the range specified by the turbulence model selected for use in the CFD calculation. And adjusting the number of meshes of the whole computational domain by increasing and decreasing I, J, K the number of meshes in three directions, respectively performing CFD (computational fluid dynamics) calculation, and determining the optimal number of meshes and mesh topology. And processing the CFD analysis result after the calculation result, and checking the flow condition in the space guide vane 2 in detail to reduce the loss as a target and perform detailed three-dimensional optimization design on the space guide vane 2.
Wherein optimizing the preliminary parameters of the spatial guide vane 2 comprises adjusting the meridian profile, in particular determining the stage pitch according to the single-stage performance parameters and the axial-radial dimension control map. Within the range of the inter-stage distance, the meridian line is adjusted, the contour line with proper curvature is adjusted by using a Bessel curve, and then the circular arc straight line is fitted.
Adjusting the thickness distribution, specifically, adjusting the thickness distribution of the guide vane blades according to the strength requirement of the structural design on the guide vane blades and the requirements of a positioning spigot, a positioning pin installation space and the like during the structural design.
And adjusting the angle distribution of the guide vane blade, specifically, firstly determining the values of the guide vane inlet and outlet blade angles. And determining the inlet blade angle of the space guide vane 2 according to the outlet flow condition of the impeller 1. And determining the outlet blade angle of the guide blade with the aim of reducing the inlet prerotation of the next stage. The distribution rule of the blade angles is adjusted to obtain a better area distribution rule, and meanwhile, the blade inclination angle cannot be too small or too large, otherwise, the manufacturing difficulty is increased. In order to minimize hydraulic losses, the flow cross-section between the blades of the space guide vane 2 is rectangular or approximately rectangular.
And after the guide vane optimization design is completed, performing single-stage CFD analysis again.
Step 14: and adjusting the preliminary model of the space guide vane 2 according to the single-stage fluid simulation result until a preset single-stage condition is met.
And after the CFD calculation is finished, checking whether the single-stage performance meets the requirement. If not, continuing optimization; if so, a multi-stage study is conducted.
Step 15: and adjusting the preliminary model of the space guide vane 2 according to the mutual influence among stages, and performing multi-stage fluid simulation.
The change of the inlet speed distribution of the impeller 1 in one stage can change the work of the blades of the impeller 1, thereby influencing the performance of the stage. And the impeller 1 inlet velocity profile is dependent on the outlet flow of the upper stage spatial guide vane 2. To obtain a reasonable velocity distribution, improvements in the exit angle of the guide vane blades are required. By improving the design and CFD analysis, the best match value with the impeller 1 is obtained.
The interstage influence research comprises a barb type design, specifically, according to streamline distribution of two-stage calculation results, meridian lines of the space guide vane 2 are modified, an inclination angle theta of a rear cover plate of the space guide vane is determined, and the barb type space guide vane 2 is formed, so that the barb type space guide vane is more consistent with the fluid inertia motion rule.
And modifying the secondary curve, specifically modifying the profile of the secondary curve according to the meridian flow line obtained by the two-stage calculation.
And the matching of the space guide vane 2 and the primary impeller 1, and the space guide vane 2 which is well matched with the secondary impeller 1 and the primary impeller 1 are combined to calculate the primary performance.
Step 16: and adjusting the preliminary model of the space guide vane 2 according to the multistage fluid simulation result until a preset multistage condition is met, and obtaining a final space guide vane 2 model.
After the optimization design in terms of the inter-stage influence study is completed, the multi-stage CFD analysis is performed again. And after the CFD calculation is finished, checking whether the multilevel performance meets the requirements. If not, continuing optimization; and if so, outputting, namely outputting the three-dimensional model of the spatial guide vane 2 in the required format through an output interface of the three-dimensional design software.
The embodiment of the invention provides a design method of a space guide vane 2 of a multistage centrifugal pump, which is used for respectively carrying out fluid simulation on a single stage and multiple stages and then carrying out parameter adjustment and optimization according to a simulation structure, so that the space guide vane 2 of a horizontal sectional type multistage centrifugal pump meeting the actual requirements can be obtained.
Other embodiments of the invention will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the invention being indicated by the following claims.
It will be understood that the invention is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.
Claims (3)
1. A design method of a space guide vane of a multistage centrifugal pump is characterized by comprising the following steps:
establishing an impeller model;
determining a space guide vane initial parameter according to the impeller model and the single-stage performance parameter to obtain an initial model of the space guide vane;
combining the impeller model and the preliminary model of the space guide vane into a first stage, optimizing the preliminary parameters of the space guide vane, and performing fluid simulation on the stage;
adjusting the preliminary model of the space guide vane according to a single-stage fluid simulation result until a preset single-stage condition is met;
adjusting the preliminary model of the space guide vane according to the mutual influence between stages, and performing multi-stage fluid simulation;
and adjusting the preliminary model of the space guide vane according to the multi-stage fluid simulation result until a preset multi-stage condition is met, and obtaining a final space guide vane model.
2. The method of claim 1, wherein determining vane preliminary parameters from the wheel model and single stage performance parameters comprises:
calculating to obtain the inlet width of the space guide vane according to the outlet width of the impeller model and the following formula;
b3＝b2+(0～2mm)；
wherein b2 is the outlet width of the impeller model, b3 is the inlet width of the space guide vane;
calculating to obtain the inlet radius of the space guide vane model according to the following formula;
R3＝(1.02～1.05)*R2；
wherein R2 is the exit radius of the impeller model and R3 is the inlet radius of the space guide vane;
according to the number of the blades of the impeller model, the number of the blades of the space guide vane is determined according to the following formula;
zi＝z-(1～3)；
wherein zi is the number of blades of the space guide vane, z is the number of blades of the impeller model, and zi and z are coprime;
determining the installation angle of the inlet blade of the space guide blade according to the installation angle of the blade outlet of the impeller model and the following formula,
βb3＝βb2-(1°～7°)；
wherein β b3 is the installation angle of the inlet blade of the space guide vane, β b2 is the blade outlet installation angle of the impeller model;
determining the maximum thickness of the blades of the space guide vane according to the following formula according to the minimum thickness of the blades of the space guide vane,
δmax＝(2～4)*δ1；
wherein δ max is the blade maximum thickness and δ 1 is the blade minimum thickness of the space vane.
3. The method according to claim 2, wherein the minimum thickness of the blades of the space guide vane is 3-6mm, the security protection angle of the outlet blades of the space guide vane is 90 degrees, and the included angle between the tail edge line of the rear cover plate of the space guide vane and the axis is 20-45 degrees;
the blade outlet width, the blade outlet radius, the inlet width and the inlet radius of the space guide blade satisfy the following relations,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of the space guide vane, R4 is the blade outlet radius of the space guide vane, b3 is the inlet width of the space guide vane, R3 is the inlet radius of the space guide vane,
the cross section of overflowing among the blades of the space guide vane is a rectangular cross section.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113882971A (en) * | 2021-09-15 | 2022-01-04 | 浙江理工大学 | Stator guide vane structure of rocket engine turbopump |
| CN114294235A (en) * | 2021-12-22 | 2022-04-08 | 嘉利特荏原泵业有限公司 | Design method for interstage flow channel of guide vane type multistage centrifugal pump |
| CN116220913A (en) * | 2023-05-08 | 2023-06-06 | 中国航发四川燃气涡轮研究院 | Low-loss engine pre-rotation air supply system |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201916A (en) * | 2015-09-17 | 2015-12-30 | 浙江工业大学之江学院 | Designing method for hydraulic power of space guide-blade centrifugal pump |
-
2020
- 2020-12-31 CN CN202011637905.1A patent/CN112784370B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201916A (en) * | 2015-09-17 | 2015-12-30 | 浙江工业大学之江学院 | Designing method for hydraulic power of space guide-blade centrifugal pump |
Non-Patent Citations (2)
| Title |
|---|
| 单建华等: "多级离心泵的单级增效研究", 《安徽工业大学学报（自然科学版）》, vol. 33, no. 3, pages 251 - 255 * |
| 张雪莲: "第2章 数值计算方法及试验验证", 中国优秀硕士学位论文全文数据库 工程科技II辑, no. 2019, pages 10 - 19 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113882971A (en) * | 2021-09-15 | 2022-01-04 | 浙江理工大学 | Stator guide vane structure of rocket engine turbopump |
| CN113882971B (en) * | 2021-09-15 | 2023-02-03 | 浙江理工大学 | Stator guide vane structure of rocket engine turbopump |
| CN114294235A (en) * | 2021-12-22 | 2022-04-08 | 嘉利特荏原泵业有限公司 | Design method for interstage flow channel of guide vane type multistage centrifugal pump |
| CN116220913A (en) * | 2023-05-08 | 2023-06-06 | 中国航发四川燃气涡轮研究院 | Low-loss engine pre-rotation air supply system |
| CN116220913B (en) * | 2023-05-08 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Low-loss engine pre-rotation air supply system |
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