CN112784370B - Design method of space guide vane of multistage centrifugal pump - Google Patents
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- 230000003993 interaction Effects 0.000 claims abstract description 4
- 238000009434 installation Methods 0.000 claims description 11
- 238000004364 calculation method Methods 0.000 description 12
- 238000004458 analytical method Methods 0.000 description 7
- 238000009826 distribution Methods 0.000 description 6
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- 230000004323 axial length Effects 0.000 description 3
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
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- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
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Abstract
The application discloses a design method of space guide vanes of a multistage centrifugal pump, which comprises the steps of establishing an impeller model; determining a preliminary parameter of the space guide vane according to the impeller model and the single-stage performance parameter to obtain a preliminary model of the space guide vane; combining the impeller model and the preliminary model of the space guide vane into a stage, optimizing the preliminary parameters of the space guide vane, and carrying out fluid simulation on the stage; according to the single-stage fluid simulation result, the preliminary model of the space guide vane is adjusted until the preset single-stage condition is met; according to the interaction between the stages, the preliminary model of the space guide vane is adjusted, and multi-stage fluid simulation is carried out; and according to the multi-stage fluid simulation result, the preliminary model of the space guide vane is adjusted until the preset multi-stage condition is met, and a final space guide vane model is obtained. Therefore, the method can obtain the space guide vane of the horizontal sectional type multistage centrifugal pump which meets the actual demands.
Description
Technical Field
The application relates to the technical field of multistage centrifugal pumps, in particular to a design method of space guide vanes of a multistage centrifugal pump.
Background
The main flow-through components of the vane pump are a water suction chamber, an impeller and a water pressing chamber. The pumping chamber is located at the periphery of the impeller and serves to collect liquid flowing from the impeller and deliver it uniformly to the next stage or discharge pipe, where most of the kinetic energy of the liquid at the impeller outlet is converted into pressure energy with as little loss as possible during the collection of the liquid. The pumping chamber mainly comprises a volute chamber (namely a spiral pumping chamber), radial guide vanes, space guide vanes, axial flow pump guide vanes and the like.
The space guide vane is a common water pressing chamber, and the front guide vane and the back guide vane are integrated. Because the blades are spatially twisted, they are referred to as spatial vanes. Compared with the radial guide vane commonly used by the horizontal sectional type multistage pump, the space guide vane reduces hydraulic loss of fluid in the flow passage, including impact loss and blending loss due to the fact that the space guide vane forms an independent flow passage from the inlet to the outlet blades. And the efficiency of the horizontal sectional type multistage pump is improved. According to the CFD analysis result, the efficiency of the same centrifugal impeller (the space-distributing guide vane is higher than that of the radial guide vane, namely, the combination of one impeller and one space guide vane) at the design working point is higher by more than 2%.
However, the existing space guide vane is mostly used for various vertical pumps, and the existing space guide vane is multi-stage and comprises various well pumps, submersible pumps, condensate pumps, single-stage guide vane type mixed flow pumps and the like. The main characteristics of the space guide vanes used for the vertical pumps are large axial length and small radial size. The existing space guide vane has large axial length and cannot be used for a horizontal sectional type multistage centrifugal pump.
Disclosure of Invention
The application 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 is large in axial length and cannot be used for a horizontal sectional type multistage centrifugal pump.
According to an embodiment of the present application, there is provided a design method of a space vane of a multistage centrifugal pump, including:
establishing an impeller model;
determining a preliminary parameter of the space guide vane according to the impeller model and the single-stage performance parameter to obtain a preliminary 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 first stage;
according to a single-stage fluid simulation result, the preliminary model of the space guide vane is adjusted until a preset single-stage condition is met;
according to the interaction between stages, the preliminary model of the space guide vane is adjusted, and multistage fluid simulation is carried out;
and according to the multi-stage fluid simulation result, adjusting the preliminary model of the space guide vane until the preset multi-stage condition is met, and obtaining a final space guide vane model.
Specifically, the determining the preliminary parameters of the space guide vane according to the impeller model and the single-stage performance parameters comprises the following steps:
according to the outlet width of the impeller model, calculating to obtain the inlet width of the space guide vane according to the following formula;
b3＝b2+(0～2mm)；
wherein b2 is the outlet width of the impeller model, and b3 is the inlet width of the space guide vane;
according to the following formula, calculating to obtain the inlet radius of the space guide vane model;
R3＝(1.02～1.05)*R2；
wherein R2 is the outlet radius of the impeller model, and R3 is the inlet radius of the space guide vane;
according to the number of blades of the impeller model, determining the number of blades of the space guide vane 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 z are mutually equal;
according to the blade outlet installation angle of the impeller model, determining the installation angle of the inlet blade of the space guide blade according to the following formula,
βb3＝βb2-(1°～7°)；
wherein βb3 is the installation angle of the inlet blade of the space guide vane, and βb2 is the blade outlet installation angle of the impeller model;
according to the minimum thickness of the blades of the space guide vanes, determining the maximum thickness of the blades of the space guide vanes according to the following formula,
δmax＝(2～4)*δ1；
wherein δmax is the maximum thickness of the blade, and δ1 is the minimum thickness of the blade of the space vane.
Specifically, the minimum thickness of the blades of the space guide vane is 3-6mm, the security 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 relation,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of the space vane, R4 is the blade outlet radius of the space vane, b3 is the inlet width of the space vane, R3 is the inlet radius of the space vane,
the inter-blade flow section of the space guide vane is a rectangular section.
The embodiment of the application 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 optimization according to a simulation structure, so that the space guide vane of the horizontal sectional type multistage centrifugal pump meeting actual requirements can be obtained.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are 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 application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for designing a space vane of a multistage centrifugal pump provided by the application;
FIG. 2 is a block diagram of an impeller and space vane.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
According to an embodiment of the present application, as shown in fig. 1 and 2, there is provided a method for designing a space vane of a multistage centrifugal pump, including:
step 11: and (5) establishing a model of the impeller 1.
According to the existing two-dimensional water map of the centrifugal impeller 1, drawing annotation data are read or geometric parameters and information required by water force design are measured by using 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 root radius R1H at the inlet of the impeller 1, the inlet attack angle i at different radii from the root to the tip, the number of blades z, the thickness delta 1 of the blade inlet side of the impeller 1, the actual thickness delta of the blade of the impeller 1, the blade inlet setting angle betab 1 of the impeller 1, the blade outlet setting angle betab 2 of the impeller 1, the line shape of the meridian line, the coordinates of the curve connection points of each section, the curvature of the line, and the like.
Three-dimensional modeling of the blades of the impeller 1 is performed according to the existing two-dimensional water map of the centrifugal impeller 1 by using three-dimensional modeling software. First, the pressure surface axis-plane cross-section is pressed to take a point on the hydrograph, and each axis-plane cross-section generates a file ibl. Suction side ibl is then extracted in the same way. And (5) reading in a ibl file in three-dimensional modeling software to generate a pressure surface and a suction surface curved surface of the blade of the impeller 1. And then leading in the molded lines of the front cover plate and the rear cover plate, the leading edge and the trailing edge, and making 4 curved surfaces around the rotating shaft respectively to extend the pressure surface and the suction surface of the blade. Then, the respective curved surfaces are combined and solidified to generate a three-dimensional impeller 1 blade, and the leading edge of the blade is rounded to obtain the impeller 1 blade which finally conforms to the hydrodynamic map.
After the three-dimensional modeling is completed, deriving an igs file of the three-dimensional model of the impeller 1 blade from three-dimensional modeling software. After the three-dimensional design software is used for reading the blades of the impeller 1 (the piece 1), the impeller 1 is finely adjusted according to the obtained geometric parameters of the existing impeller 1, and the values of the length and the angle are rounded, so that the model in the three-dimensional design software is completely consistent with the existing actual impeller 1.
Step 12: and determining the preliminary parameters of the space guide vane 2 according to the impeller 1 model and the single-stage performance parameters to obtain a preliminary model of the space guide vane 2.
Specifically, determining preliminary parameters of the space vane 2 according to the impeller 1 model and the single-stage performance parameters comprises:
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, and b3 is the inlet width of the space 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 outlet radius of the impeller model, and R3 is the inlet radius of the space 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 the zi and z are mutually equal;
according to the blade outlet mounting angle of the impeller 1 model, the mounting angle of the inlet blade of the space vane 2 is determined according to the following formula,
βb3＝βb2-(1°～7°)；
wherein, beta b3 is the installation angle of the inlet blade of the space vane 2, and beta 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 vane 2, the maximum thickness of the blades of the space vane 2 is determined according to the following formula,
δmax＝(2～4)*δ1；
wherein δmax is the maximum thickness of the blade, and δ1 is the minimum thickness of the blade of the space vane 2.
The minimum thickness of the blades of the space guide vane 2 is 3-6mm, the security angle of the outlet blades of the space guide vane 2 is 90 degrees, and the included angle between the tail edge line of the rear cover plate of the space guide vane 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 vane 2 satisfy the following relation,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of the space vane 2, R4 is the blade outlet radius of the space vane 2, b3 is the inlet width of the space vane 2, and R3 is the inlet radius of the space vane 2.
Step 13: the impeller 1 model and the preliminary model of the space vane 2 are combined into a stage, the preliminary parameters of the space vane 2 are optimized, and the stage is subjected to fluid simulation.
In the three-dimensional design software, the impeller 1 and the space vane 2 are combined into one stage to be designed together. After the design is completed in a single-stage preliminary scheme, single-stage CFD analysis is carried out, namely fluid simulation analysis is carried out. 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 expansion 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, the physical quantity of the outlet of the calculation domain is more stable, so that the calculation result is more accurate, and the inlet and the outlet of the calculation domain are required 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 the CFD calculation. The grid number of the whole calculation domain is adjusted by increasing and decreasing the grid number of the I, J, K directions, CFD calculation is carried out respectively, and the optimal grid number and the grid topological structure are determined. And (3) according to the calculation result, the CFD analysis result is processed, the flow condition in the space guide vane 2 is checked in detail, the loss is reduced, and the space guide vane 2 is subjected to detailed three-dimensional optimization design.
Wherein optimizing the preliminary parameters of the space vane 2 comprises adjusting a meridian line, in particular determining a stage spacing from the single stage performance parameters and the axial radial dimension control map. And in the range of limiting the inter-stage distances, adjusting a meridian line, firstly adjusting a contour line with proper curvature by using a Bezier curve, and then fitting by using an arc straight line.
The thickness distribution is adjusted, specifically, the thickness distribution of the guide vane blade is adjusted according to the strength requirement of the structural design on the guide vane blade and the requirements of a positioning spigot, a positioning pin installation space and the like in the structural design.
The vane blade angle distribution is adjusted, in particular, the value of the vane inlet and outlet blade angle is first determined. The inlet blade angle of the space vane 2 is determined according to the outlet flow condition of the impeller 1. The vane outlet blade angle is determined with the aim of reducing the next stage inlet pre-rotation. And the distribution rule of the blade angles is adjusted to obtain a good area distribution rule, and meanwhile, the inclination angle of the blade cannot be too small or too large, or the manufacturing difficulty is increased. In order to minimize hydraulic losses, the flow cross section between the blades of the space vane 2 is rectangular or nearly rectangular.
After the guide vane optimization design is completed, single-stage CFD analysis is performed again.
Step 14: and according to the single-stage fluid simulation result, the preliminary model of the space vane 2 is adjusted until the preset single-stage condition is met.
After the CFD calculation is completed, it is checked whether the single-stage performance meets the requirements. If not, continuing to optimize; if so, a multi-stage study is performed.
Step 15: based on the inter-stage interactions, a preliminary model of the space vane 2 is adjusted and a multi-stage fluid simulation is performed.
The variation of the inlet speed profile of the impeller 1 in one stage will change the work done by the blades of the impeller 1 and thus affect the performance of the stage. While the impeller 1 inlet velocity profile depends on the outlet flow of the upper stage space vanes 2. In order to obtain a reasonable speed profile, an improvement in the vane blade exit angle is required. By improved design and CFD analysis, an optimal matching value with the impeller 1 is obtained.
The inter-stage influence research comprises a barb type design, specifically, the meridian line of the space guide vane 2 is modified according to the streamline distribution of the two-stage calculation result, the inclined angle theta of the rear cover plate of the space guide vane is determined, and the barb type space guide vane 2 is formed, so that the fluid inertia motion law is more met.
And modifying the secondary curve, specifically, modifying the profile of the secondary curve according to the meridian line obtained by two-stage calculation.
Matching the space guide vane 2 with the first-stage impeller 1, and combining the space guide vane 2 which is well matched with the secondary impeller 1 with the first-stage impeller 1 to calculate the first-stage performance.
Step 16: and according to the multi-stage fluid simulation result, the preliminary model of the space guide vane 2 is adjusted until the preset multi-stage condition is met, and a final model of the space guide vane 2 is obtained.
After the optimization design in the aspect of the inter-stage influence study is completed, multi-stage CFD analysis is performed again. After the CFD calculation is completed, whether the multi-stage performance meets the requirement is checked. If not, continuing to optimize; and if the space guide vane 2 three-dimensional model meets the requirement, outputting, namely outputting the space guide vane 2 three-dimensional model in a required format through an output interface of three-dimensional design software.
The embodiment of the application 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 optimization according to a simulation structure, so that the space guide vane 2 of the horizontal sectional type multistage centrifugal pump meeting actual requirements can be obtained.
Other embodiments of the application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses, or adaptations of the application following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the application pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the application being indicated by the following claims.
It is to be understood that the application is not limited to the precise arrangements and instrumentalities shown in the drawings, which have been described above, and that various modifications and changes may be effected without departing from the scope thereof. The scope of the application is limited only by the appended claims.
Claims (3)
1. A method of designing a space vane of a multistage centrifugal pump, comprising:
establishing an impeller model;
determining a preliminary parameter of the space guide vane according to the impeller model and the single-stage performance parameter to obtain a preliminary 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 first stage; the method comprises the steps of optimizing preliminary parameters of a space guide vane, namely adjusting a meridian line, determining a stage distance according to a single-stage performance parameter and an axial radial dimension control chart, adjusting the meridian line in a stage distance limiting range, firstly adjusting a contour line with proper curvature by using a Bezier curve, and then fitting by using an arc straight line;
according to a single-stage fluid simulation result, the preliminary model of the space guide vane is adjusted until a preset single-stage condition is met;
according to the interaction between stages, the preliminary model of the space guide vane is adjusted, and multistage fluid simulation is carried out;
and according to the multi-stage fluid simulation result, adjusting the preliminary model of the space guide vane until the preset multi-stage condition is met, and obtaining a final space guide vane model.
2. The method of claim 1, wherein the determining vane preliminary parameters from the impeller model and single stage performance parameters comprises:
according to the outlet width of the impeller model, calculating to obtain the inlet width of the space guide vane according to the following formula;
b3＝b2+(0～2mm)；
wherein b2 is the outlet width of the impeller model, and b3 is the inlet width of the space guide vane;
according to the following formula, calculating to obtain the inlet radius of the space guide vane model;
R3＝(1.02～1.05)*R2；
wherein R2 is the outlet radius of the impeller model, and R3 is the inlet radius of the space guide vane;
according to the number of blades of the impeller model, determining the number of blades of the space guide vane 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 z are mutually equal;
according to the blade outlet installation angle of the impeller model, determining the installation angle of the inlet blade of the space guide blade according to the following formula,
βb3＝βb2-(1°～7°)；
wherein βb3 is the installation angle of the inlet blade of the space guide vane, and βb2 is the blade outlet installation angle of the impeller model;
according to the minimum thickness of the blades of the space guide vanes, determining the maximum thickness of the blades of the space guide vanes according to the following formula,
δmax＝(2～4)*δ1；
wherein δmax is the maximum thickness of the blade, and δ1 is the minimum thickness of the blade of the space vane.
3. The method of claim 2, wherein the minimum thickness of the blades of the space vane is 3-6mm, the exit blade placement angle of the space vane is 90 °, and the trailing edge line of the trailing cover plate of the space vane is 20 ° to 45 ° from the axis;
the blade outlet width, the blade outlet radius, the inlet width and the inlet radius of the space guide blade satisfy the following relation,
R4*b4＝(0.65～0.85)*R3*b3；
wherein b4 is the blade outlet width of the space vane, R4 is the blade outlet radius of the space vane, b3 is the inlet width of the space vane, R3 is the inlet radius of the space vane,
the inter-blade flow section of the space guide vane is a rectangular section.
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