CN-121997837-A - Compressor configuration method and system based on shell flow characteristic simulation analysis

CN121997837ACN 121997837 ACN121997837 ACN 121997837ACN-121997837-A

Abstract

The invention discloses a compressor configuration method and a system based on shell internal flow characteristic simulation analysis, and relates to the technical field of compressor optimization, wherein the method comprises the steps of generating a numerical simulation calculation result according to a plurality of preset discrete compressor shell internal fluid flow models and a plurality of grid division nodes of a compressor; and performing iterative operation, wherein the iterative operation comprises the steps of judging the convergence of a numerical simulation calculation result according to the fluid flow state in the compressor shell, if the convergence is not carried out, carrying out numerical simulation on a fluid flow model in the compressor shell under a random working condition again, replacing the current numerical simulation calculation result with the recalculated numerical simulation calculation result until the convergence is carried out, and configuring the internal structure of the compressor according to the numerical simulation calculation result. According to the invention, through simulation analysis of the fluid flow characteristics in the compressor shell, the internal structure of the compressor is configured by using the simulation calculation result, so that the calculation efficiency and accuracy can be improved, and the internal structure of the compressor can be effectively optimized.

Inventors

YIN JUN
YANG FAN

Assignees

重庆大学

Dates

Publication Date: 20260508
Application Date: 20260209

Claims (10)

1. The compressor configuration method based on the simulation analysis of the flow characteristics in the shell is characterized by comprising the following steps of: generating a numerical simulation calculation result according to a plurality of preset fluid flow models in the discrete compressor shell and a plurality of grid division nodes of the compressor, wherein the fluid flow models in the discrete compressor shell correspond to the grid division nodes one by one; dividing different calculation domains according to the geometric shape change conditions of different areas in the compressor, and obtaining corresponding grid dividing points by adopting tetrahedral grid division or hexahedral grid division; the hexahedral mesh dividing process comprises the steps of analyzing the change of the geometric shape of a pump cavity according to a time step, reconstructing a mesh, and interpolating the flow field attribute of the last time step mesh to the updated mesh; Performing iterative operation, wherein the iterative operation comprises the steps of judging the convergence of a numerical simulation calculation result according to the fluid flow state in the compressor shell, if the convergence is not carried out, carrying out numerical simulation on a discrete compressor shell fluid flow model under a random working condition again, and replacing the current numerical simulation calculation result with the recalculated numerical simulation calculation result until the convergence is carried out; and configuring the internal structure of the compressor according to the numerical simulation calculation result.
2. The method for configuring a compressor based on simulation analysis of flow characteristics in a shell according to claim 1, wherein the generating a numerical simulation calculation result according to a plurality of preset fluid flow models in a discrete compressor shell and a plurality of grid division nodes of the compressor, wherein the fluid flow models in the discrete compressor shell correspond to the grid division nodes one by one comprises: Dividing calculation domains according to geometric features of different areas of the compressor, and respectively carrying out grid division on the different calculation domains by using a dynamic grid division method to obtain a plurality of grid division nodes, wherein the calculation domains comprise an air inlet, a pump cavity and an air exhaust hole; respectively establishing a corresponding discrete compressor shell fluid flow model for each grid division node according to a preset compressor shell fluid flow model; And respectively carrying out numerical simulation calculation on the fluid flow model in the discrete compressor shell according to the compressor parameters under the given working conditions to obtain a numerical simulation calculation result.
3. The compressor configuration method based on flow characteristic simulation analysis in shell according to claim 2, wherein the dividing the calculation domains according to the geometric characteristics of different areas of the compressor, and performing grid division on the different calculation domains by using a dynamic grid division method to obtain grid division nodes respectively, comprises: Dividing three calculation domains of an air inlet, a pump cavity and an air exhaust hole according to the geometric shape change conditions of different areas in the compressor; adopting tetrahedral mesh division for the air inlet and the air outlet; Adopting hexahedral grid division for the pump cavity, and utilizing a dynamic Lagrangian grid method to enable grid nodes in the pump cavity to change along with the change of the geometric shape of the pump cavity; And connecting the calculation domains by adopting an interface technology, so that grid nodes of the calculation domains are corresponding to each other, generating a grid file, and obtaining grid division nodes.
4. The compressor configuration method based on flow characteristic simulation analysis in a shell according to claim 3, wherein the pump chamber is divided into hexahedral meshes, and mesh nodes in the pump chamber are changed along with the change of the geometry of the pump chamber by using a dynamic lagrangian mesh method, comprising: Generating a hexahedral initial grid by using an O-shaped grid technology; Setting time steps in the simulation time, dynamically updating the node positions of the hexahedral mesh according to the change of the geometric shape of the pump cavity in each time step, and reconstructing the mesh; interpolating flow field attributes of the previous time step grid to the updated grid by using a Lagrangian interpolation method; And stopping reconstructing the grid when the set simulation time is over.
5. The compressor configuration method based on flow characteristics simulation analysis in a shell according to claim 2, wherein the establishing a corresponding discrete in-shell fluid flow model for each meshing node according to a preset in-shell fluid flow model includes: obtaining a fluid flow model in the compressor shell according to the flow characteristics of the refrigerant in the compressor; Substituting the grid division nodes into the fluid flow model in the compressor shell to obtain a discrete fluid flow model in the compressor shell.
6. The method for configuring a compressor based on simulation analysis of flow characteristics in a shell according to claim 5, wherein the obtaining a fluid flow model in the shell of the compressor based on flow characteristics of refrigerant in the compressor comprises: Constructing a compressor control equation according to the flow characteristic of the refrigerant in the compressor, wherein the refrigerant in the compressor flows into a non-steady compressible turbulent flow in a three-dimensional space; by RNG The turbulence model simulates the flow process of the refrigerant in the compressor and constructs a compressor turbulence model; combining the compressor control equation with the compressor turbulence model to obtain a fluid flow model in a compressor shell; the initial conditions and boundary conditions are set according to the initially given parameters and the fluid flow characteristics of the compressor shell.
7. The method for configuring a compressor based on simulation analysis of flow characteristics of a shell according to claim 6, wherein the setting of initial conditions and boundary conditions according to the initially given parameters and flow characteristics of the fluid in the shell of the compressor comprises: Setting inlet pressure, fluid velocity and temperature in the compressor according to the initial given parameters, and determining initial conditions; the boundary conditions are determined based on inlet and outlet boundary conditions and object plane boundary conditions of the compressor.
8. The method of claim 1, wherein the performing an iterative operation includes determining convergence of the numerical simulation calculation based on the fluid flow conditions in the compressor shell, and if not, re-modeling the fluid flow model in the discrete compressor shell under a random operating condition and replacing the current numerical simulation calculation with the re-calculated numerical simulation calculation until convergence, comprising: Judging whether the current numerical simulation calculation result is converged or not by using a residual error value analysis method; and when the current numerical simulation calculation result is not converged, carrying out numerical simulation again on the fluid flow model in the discrete compressor shell under a random working condition, and replacing the current numerical simulation calculation result with the recalculated numerical simulation calculation result until the numerical simulation calculation result is converged.
9. The compressor configuration method based on in-shell flow characteristic simulation analysis according to claim 8, wherein the determining whether the current numerical simulation calculation result converges by using a residual value analysis method comprises: Obtaining the residual value of each node and the root mean square residual value of all nodes by calculating the difference between the numerical simulation calculation result and the real result; Setting a convergence standard value J, and converging corresponding numerical simulation calculation results when the residual value of each node and the root mean square residual value of all nodes are smaller than the convergence standard value J.
10. A compressor configuration system based on in-shell flow characteristic simulation analysis for implementing a compressor configuration method based on in-shell flow characteristic simulation analysis according to any one of claims 1 to 9, the system comprising: The compressor model simulation calculation module generates a numerical simulation calculation result according to a plurality of preset discrete compressor shell fluid flow models and a plurality of grid division nodes of the compressor, wherein the discrete compressor shell fluid flow models are in one-to-one correspondence with the grid division nodes; The simulation result iteration module is used for executing iteration operation, wherein the iteration operation comprises the steps of judging the convergence of a numerical simulation calculation result according to the fluid flow state in the compressor shell, if the convergence is not carried out, carrying out numerical simulation on a discrete compressor shell fluid flow model under a random working condition again, and replacing the current numerical simulation calculation result with the recalculated numerical simulation calculation result until the convergence is carried out; And the compressor internal structure configuration module configures the internal structure of the compressor according to the numerical simulation calculation result.

Description

Compressor configuration method and system based on shell flow characteristic simulation analysis Technical Field The invention relates to the technical field of compressor optimization, in particular to a compressor configuration method and system based on simulation analysis of flow characteristics in a shell. Background In modern engineering applications, compressors are widely used in aerodynamic systems, such as air conditioning, refrigeration and gas turbines, whose performance optimization affects the efficiency and reliability of the overall system. To enhance compressor design and performance assessment, numerical modeling techniques, particularly computational fluid dynamics, may be employed to analyze flow characteristics within the compressor shell. These simulations can provide detailed flow field information, including velocity profiles, pressure variations, and turbulence characteristics, to aid in understanding the behavior of the fluid within the compressor shell and the impact on compressor performance. For example, chinese patent application publication No. CN115017843a discloses a method for optimizing the aerodynamic performance of a centrifugal compressor, which improves the design concept of conventional design-modification, describes the linearity of meridian flow channels, the linearity of blade installation angle distribution and the linearity of blade thickness distribution by using a small amount of parameters to control straight lines or curves, so as to form a three-dimensional geometry represented by a small amount of parameters, and then obtains a centrifugal compressor model with optimal aerodynamic performance in accordance with the design parameter range by using an optimization method combining experimental design, an artificial neural network, a genetic algorithm and CFD. The design method can further optimize the design scheme without the improvement direction from the beginning on one hand, and can also optimize the design aiming at specific parameters when the improvement direction is clear on the other hand. Under the condition of ensuring the unchanged size, the pneumatic performance of the centrifugal compressor is better. The prior art has the following problems that in the optimization process of the compressor, a discretized compressor shell internal fluid flow model is utilized according to the internal fluid flow characteristics of the compressor shell, simulation calculation is carried out on compressor parameters under different working conditions, and a method for configuring the internal structure of the compressor by utilizing simulation calculation results is not available, and in order to solve the problems, the invention provides a compressor configuration method and a system based on shell internal fluid flow characteristic simulation analysis. Disclosure of Invention Aiming at the defects of the prior art, the invention mainly aims to provide a compressor configuration method and a system based on shell flow characteristic simulation analysis, which can effectively solve the problems in the background art. The specific technical scheme of the invention is as follows: a compressor configuration method based on simulation analysis of flow characteristics in a shell, the compressor configuration method comprising: generating a numerical simulation calculation result according to a plurality of preset fluid flow models in the discrete compressor shell and a plurality of grid division nodes of the compressor, wherein the fluid flow models in the discrete compressor shell correspond to the grid division nodes one by one; Performing iterative operation, wherein the iterative operation comprises the steps of judging the convergence of a numerical simulation calculation result according to the fluid flow state in the compressor shell, if the convergence is not carried out, carrying out numerical simulation on a discrete compressor shell fluid flow model under a random working condition again, and replacing the current numerical simulation calculation result with the recalculated numerical simulation calculation result until the convergence is carried out; and configuring the internal structure of the compressor according to the numerical simulation calculation result. Specifically, the generating a numerical simulation calculation result according to a plurality of preset fluid flow models in a discrete compressor shell and a plurality of grid division nodes of the compressor, wherein the fluid flow models in the discrete compressor shell correspond to the grid division nodes one by one includes: Dividing calculation domains according to geometric features of different areas of the compressor, and respectively carrying out grid division on the different calculation domains by using a dynamic grid division method to obtain a plurality of grid division nodes; respectively establishing a corresponding discrete compressor shell fluid flow model for each grid divi