CN110489832B - Simulation test method for pneumatic performance of turbulence control screen unit body - Google Patents
Simulation test method for pneumatic performance of turbulence control screen unit body Download PDFInfo
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Abstract
The application relates to a simulation test method for the pneumatic performance of a turbulence control screen unit body, which comprises the following steps: constructing a unit body model or a turbulence control screen model with a unit body, dividing a calculation area of the unit body model into an upstream fluid area, a honeycomb porous medium area and a downstream fluid area according to the airflow direction, and connecting the adjacent two areas by using an interface; setting boundary conditions of numerical simulation; determining a face porosity, a bulk porosity and a loss model of the honeycomb porous media region; and carrying out a numerical simulation test on the unit body or the turbulence control screen model to obtain a simulation result. According to the simulation test method, the honeycomb structure is used as a porous medium model, and the integral area of the honeycomb structure is directly subjected to grid division, so that the grid division step is greatly simplified, the number of grids is reduced, the interface and the honeycomb solid wall surface problem do not exist in the grids, the calculation efficiency is improved, the interface connection is adopted between different areas, and the calculation precision is improved.
Description
Technical Field
The application belongs to the technical field of aeroengine acoustic tests, and particularly relates to a simulation test method for pneumatic performance of a turbulence control screen unit body.
Background
As shown in fig. 1, the turbulence control screen 1 is an apparatus for researching acoustic performance of an aeroengine, which is generally formed by splicing hundreds of unit bodies 2 to form a spherical shell, wherein the unit bodies 2 are composed of a perforated plate 3 and a honeycomb structure 4, the perforated plate 3 is provided with a plurality of honeycomb holes 31 matched with the honeycomb structure 4, and the honeycomb structure 4 has a decisive effect on the aerodynamic performance of the turbulence screen in the unit bodies 2.
Currently, there are two main approaches to the study of the aerodynamic properties of honeycomb structural units:
one is a test that uses a total pressure probe to obtain the total pressure loss characteristics between the upstream and downstream of the honeycomb cell, followed by a particle image velocimetry (Particle Image Velocimetry, PIV) to obtain the cell outlet flow field distribution. However, when the incoming flow speed is smaller, for example, the incoming flow speed is less than 5m/s, the total pressure loss passing through the honeycomb structural unit body is smaller, and the error of the test result is larger. According to the flow range of the current scaled fan/booster stage test, the incoming flow speed of the turbulence control screen unit body is mostly lower than 5m/s, so that the error is larger; the PIV has the problems that the tracer particles are difficult to add and the distribution of the tracer particles is uneven when measuring a flow field; if the aerodynamic characteristics of the whole turbulence control screen are analyzed and researched, the test method is difficult and high in cost, and particularly, the PIV is used for measuring the rear flow field of the turbulence control screen.
The other is a simulation test, namely, modeling a honeycomb structure unit body or an entire turbulence control screen, then carrying out grid division on a honeycomb structure, and obtaining grids of the entire honeycomb structure unit body in an array mode. In this method, the entire calculation region is treated as a fluid region and a numerical simulation is performed, which also includes a honeycomb structure region. However, the method of meshing a honeycomb structure and then modeling the array and the corresponding simulation test method have the following disadvantages: 1) The number of grids is huge, the calculation cost is high, and the efficiency is low; 2) The grid interfaces and the periodic boundary conditions are too many, so that the grids are unevenly distributed at the interfaces, and the calculated flow field results are discontinuous; 3) The honeycomb has a large number of solid wall surfaces inside, and the solid wall surfaces have a certain thickness, so that the solid wall surfaces are difficult to process when modeling, namely grid dividing; 4) The single honeycomb structure boundary layer grid division and calculation setting have larger influence on the calculation result; 5) The results and test values obtained by the modeling method and the simulation test method have larger differences.
Thus, a new approach is needed to obtain the aerodynamic properties of the turbulence control screen unit body.
Disclosure of Invention
The invention aims to provide a simulation test method for the pneumatic performance of a turbulence control screen unit body, which solves or reduces at least one problem in the background technology.
The technical scheme of the application is as follows: a simulation test method for pneumatic performance of a turbulence control screen unit body, the simulation test method comprising:
constructing a unit body model or a turbulence control screen model with a unit body, dividing a calculation area of the unit body model into an upstream fluid area, a honeycomb porous medium area and a downstream fluid area according to the airflow direction, and connecting adjacent two areas by using an interface;
setting boundary conditions of numerical simulation;
determining a face porosity, a bulk porosity and a loss model of the cellular porous media region;
and carrying out a numerical simulation test on the unit body or the turbulence control screen model to obtain a simulation result.
In this application, before the setting of the boundary condition of the numerical simulation, the method further includes: and carrying out grid division on the unit body model.
In this application, the setting a boundary condition of the numerical simulation includes:
setting a computer medium in numerical simulation calculation, wherein the computer medium is ideal gas;
setting a reference pressure of a predetermined value in the upstream fluid region, the cellular porous medium region, and the downstream fluid region;
an inlet total pressure is set at the inlet of the upstream fluid zone, the inlet total pressure is zero, and an outlet boundary condition is set at the outlet of the downstream fluid zone, the outlet boundary condition being a mass flow outlet.
In this application, the loss model is a tangential loss, which includes flow direction, flow direction loss, and lateral loss.
In this application, the flow direction loss includes permeability and drag loss coefficient, or linear/square drag coefficient.
In the present application, the permeability K is
Wherein: a is the coefficient, Q is the volumetric flow through the porous medium, μ is the aerodynamic viscosity of the air, L is the thickness of the porous medium, a is the cross-sectional area of the honeycomb structure, Δp is the pressure differential.
In the present application, the drag loss coefficient K loss Is that
Wherein: b is the coefficient, v is the apparent velocity, ρ is the density of the fluid passing through the honeycomb structure, ΔP is the pressure differential, and L is the thickness of the porous medium.
In the present application, the linear drag coefficient C R1 Is that
The square drag coefficient C R2 Is that
In the present application, the lateral loss is determined according to a lateral resistance loss coefficient determined according to a multiplier of a flow direction resistance coefficient and a flow direction coefficient multiplying factor, and a lateral permeability determined according to a division of the flow direction permeability and the flow direction coefficient multiplying factor.
In the present application, the typical value of the flow direction coefficient magnification is 10 to 100.
According to the simulation test method for the aerodynamic performance of the turbulence control screen unit body, the honeycomb structure is taken as a porous medium model, and the grid division is directly carried out aiming at the integral area of the honeycomb structure, so that the grid division step is greatly simplified, the number of grids is reduced, the interface and the wall surface problem of the honeycomb solid body do not exist in the grids, and the calculation efficiency is improved; in addition, the calculation area is divided into three parts, the upstream and the downstream are fluid areas, the middle is a porous medium area, and the different areas are connected by adopting interfaces, so that the calculation accuracy is improved. The method has obvious advantages in grid division and calculation efficiency. The result obtained by the simulation test method of the application is well matched with the test value, and the research cost and risk can be reduced.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic view of a prior art turbulence control screen and unit cell.
Fig. 2 is a flow field schematic of the method of the present application.
Fig. 3 is a schematic diagram of a calculation grid division of a honeycomb structural unit body simulation test in the present application.
FIG. 4 is a graph of flow permeability curves for a honeycomb porous media structure according to one embodiment of the present application.
FIG. 5 is a graph of the flow-to-drag loss coefficient of a honeycomb porous media structure according to one embodiment of the present application.
FIG. 6 is a graph showing a comparison of a simulation test method and a test measurement method according to an embodiment of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to solve the problems of long grid division time, long calculation time, low calculation precision and the like in the simulation method in the prior art, the application provides a simulation test method of a turbulence control screen unit body based on a porous medium model, which mainly comprises the following steps: and constructing a model, namely dividing the unit body grids of the turbulence control screen, setting numerical simulation boundary conditions, and calculating a honeycomb porous medium flow loss model. Specifically, the method comprises the following steps:
1. construction of test model-turbulence control screen unit division based on porous medium model
In constructing the test model, the honeycomb structural body was treated as a porous medium. The type of region in which the unit cell is located is porous medium, and the type of region upstream and downstream thereof is fluid, thus dividing the entire calculation region into three parts, an upstream fluid region, a honeycomb porous medium region, and a downstream fluid region. Adjacent two computing regions are connected by an Interface.
The cellular structure unit body of the turbulence control screen is subjected to grid division, namely the rectangular area is subjected to direct grid division. In the grid division process, the grid division is simple and convenient, and the number of grids is small. The built test model does not need to consider the internal honeycomb solid wall surface problem and the internal interface problem, and the mesh dividing step is greatly simplified.
2. Numerical simulation boundary condition setting
For numerical simulation of honeycomb unit bodies, the region type of the upstream and downstream regions is a Fluid region (Fluid Domain), and the region type of the honeycomb region is a Porous medium region (Porous Domain). The computational medium is an ideal gas and the turbulence model is a k-Epsilon model. The calculation type is a constant calculation.
The three-part calculation region reference pressure was set to 1 atm, and the total inlet pressure of the upstream fluid region was set to 0Pa. Since the flow velocity of the upstream fluid region in the calculation region is low, particularly at a flow velocity of 5m/s, the dynamic pressure is relatively small, and in solving the equation pressure term, in order to avoid the influence of the truncation error on the small pressure variation, the reference pressure is set to 1 atmosphere in order to improve the calculation accuracy.
The outlet boundary condition of the downstream fluid zone is set as the mass flow outlet.
3. Honeycomb porous media flow loss model calculation
In CFX numerical simulation of porous media, it is necessary to determine the Area porosity (Area porosity), the Volume porosity (Volume porosity) and the Loss model (Loss models).
The plane porosity refers to the area a '(a' =k·a) over an infinitely small control plane a through which fluid is allowed to flow, K being a symmetrical second order tensor. Currently in CFX analysis, only the Isotropic (isotopic) plane porosity tensor K is allowed.
Bulk porosity refers to the ratio of the volume through which a fluid is allowed to flow to the physical volume. The size of the honeycomb structure is an important index for designing the unit body of the turbulence control screen.
The Loss model has an Isotropic Loss (Isotropic Loss) and a Directional Loss (Directional Loss), the Loss model of the honeycomb belonging to the latter. The study of the loss in the direction is divided into three aspects: a: a flow direction; b: flow direction loss; c: lateral losses. Loss model corresponding loss speed type (Loss Velocity Type): the apparent Velocity (Superficial), or the True Velocity (True Velocity) may be selected. The superficial velocity is a flow velocity calculated in terms of physical area, i.e., calculated from the flow rate through the porous medium and the physical area. The true velocity is the flow rate within the honeycomb medium. The method selects an apparent velocity.
a: flow direction (Stream Wise Direction):
the flow direction may alternatively be expressed in a cartesian or cylindrical coordinate system. The embodiments of the present application choose to represent the direction of fluid flow in a Cartesian coordinate system. Numerical simulation was performed on cellular structure porous media units. If the flow direction is along the Z axis, the Z direction velocity component is 1 (representing the presence or absence) and the X and Y direction velocity components are 0.
b: stream Wise Loss:
the flow loss can be selected from the permeability K and the resistance loss coefficient K loss (Permeability and Resistance Loss Coefficient), or a linear and square coefficient of resistance (Linear and Quadratic Resistance Coefficients).
The method for calculating the permeability K comprises the following steps:
wherein: q-the volumetric flow through the porous medium;
μ—dynamic viscosity of air;
l—thickness of porous medium;
a-the cross-sectional area of the honeycomb structure;
ΔP-pressure differential, pressure drop after flowing through the honeycomb structure, was tested.
a-coefficients in this calculation method;
coefficient of resistance loss K loss The calculation method comprises the following steps:
v-apparent velocity;
ρ—the density of the fluid passing through the honeycomb structure;
b-coefficients in this calculation method;
in the calculation process of the formula, the coefficient a and the coefficient b are a conclusion obtained by comparing a plurality of numerical simulation results with the unit body blowing test results.
Linear drag coefficient C R1 And squared drag coefficient C R2 With permeability K and coefficient of resistance loss K loss The relationship is as follows:
in the simulation test method of an embodiment of the present application, when determining the flow loss, a method of permeability and a coefficient of resistance loss is adopted.
c: lateral Loss (transition Loss):
in a honeycomb structure, only flow in the honeycomb direction is allowed, while lateral flow is prevented. The lateral loss should be chosen to be flow coefficient multiplying factor (Streamwise Coefficients Multiplier), i.e. the permeability and drag loss coefficient of the lateral loss are determined by both flow loss and flow coefficient multiplying factor:
1) The transverse resistance loss coefficient is obtained by multiplying the flow direction resistance loss coefficient by the multiple;
2) The transverse permeability is obtained by dividing the permeability of the flow direction by this multiple.
Wherein, the typical value of the flow direction coefficient multiplying power is 10-100. For the honeycomb structure shown in fig. 2 in the present application, the multiplying power should be 100, which means that the resistance loss in the transverse direction is extremely large, the permeability is extremely low, and the flow in the transverse direction is almost completely blocked, so that the practical flow condition is met.
As shown in fig. 3 and fig. 4, the pressure drop and the incoming flow velocity after passing through the honeycomb structural body of the turbulence control screen are obtained according to the test, and then the flow direction permeability and the flow direction loss coefficient can be obtained according to the calculation method of the flow direction permeability and the flow direction loss coefficient provided in the simulation test method of the application.
As shown in fig. 5, by testing and simulating the data obtained in fig. 3 and 4, it can be seen that: the numerical simulation result (pressure drop and incoming flow speed function) curve obtained by the simulation test method of the porous medium-based turbulence control screen unit structure almost completely coincides with the result curve obtained by the test measurement method, so that the correctness of the simulation test of the porous medium-based turbulence control screen unit structure is verified.
According to the simulation test method for the aerodynamic performance of the turbulence control screen unit body, the honeycomb structure is taken as a porous medium model, and the grid division is directly carried out aiming at the integral area of the honeycomb structure, so that the grid division step is greatly simplified, the number of grids is reduced, the interface and the wall surface problem of the honeycomb solid body do not exist in the grids, and the calculation efficiency is improved; in addition, the calculation area is divided into three parts, the upstream and the downstream are fluid areas, the middle is a porous medium area, and the different areas are connected by adopting interfaces, so that the calculation accuracy is improved. The method has obvious advantages in grid division and calculation efficiency. The result obtained by the simulation test method of the application is well matched with the test value, and the research cost and risk can be reduced.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A simulation test method for pneumatic performance of a turbulence control screen unit body, the simulation test method comprising:
constructing a unit body model or a turbulence control screen model with a unit body, dividing a calculation area of the unit body model into an upstream fluid area, a honeycomb porous medium area and a downstream fluid area according to the airflow direction, and connecting adjacent two areas by using an interface;
setting boundary conditions of numerical simulation;
determining a face porosity, a bulk porosity, and a loss model of the honeycomb porous media region, wherein the loss model comprises three aspects of flow direction, flow direction loss, and lateral loss:
the flow direction is expressed in a cartesian coordinate system or a cylindrical coordinate system;
the flow direction loss is a coefficient set consisting of permeability and drag loss coefficient, or a coefficient set consisting of linear drag coefficient and square drag coefficient, wherein:
the permeability K satisfies:
wherein: q-the volumetric flow through the porous medium;
μ—dynamic viscosity of air;
l—thickness of porous medium;
a-the cross-sectional area of the honeycomb structure;
ΔP—pressure differential, i.e., the pressure drop across the honeycomb;
a-coefficients in this calculation method;
coefficient of resistance loss K loss The method meets the following conditions:
in the formula, v is apparent speed;
ρ—the density of the fluid passing through the honeycomb structure;
b-coefficients in this calculation method;
linear drag coefficient C R1 And squared drag coefficient C R2 With permeability K and coefficient of resistance loss K loss The following relationship is satisfied:
the lateral loss is represented by permeability and drag loss coefficient, wherein the permeability and drag loss coefficient of the lateral loss are determined by two factors of flow direction loss and flow direction coefficient multiplying power;
and carrying out a numerical simulation test on the unit body or the turbulence control screen model to obtain a simulation result.
2. The method of claim 1, further comprising, prior to said setting the boundary conditions of the numerical simulation: and carrying out grid division on the unit body model.
3. The method of claim 1, wherein setting boundary conditions for numerical simulation comprises:
setting a computing medium in numerical simulation computation, wherein the computing medium is ideal gas;
setting a reference pressure of a predetermined value in the upstream fluid region, the cellular porous medium region, and the downstream fluid region;
an inlet total pressure is set at the inlet of the upstream fluid zone, the inlet total pressure is zero, and an outlet boundary condition is set at the outlet of the downstream fluid zone, wherein the outlet boundary condition is a mass flow outlet.
4. The method of claim 1, wherein the drag loss coefficient of the lateral loss is obtained by multiplying the flow direction drag loss coefficient by the flow direction coefficient magnification, and the permeability of the lateral loss is obtained by dividing the flow direction permeability by the flow direction coefficient magnification.
5. The method of claim 4, wherein the flow direction coefficient magnification has a typical value of 10 to 100.
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