CN114004115A - Novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades - Google Patents
Novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades Download PDFInfo
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Abstract
本发明公开了一种新的复杂冷却叶片快速三维管网半气热耦合评估方法，包括以下步骤：S1、预设叶片外壁的温度Twg＝Tw0，Tw0为估计的壁面温度；冷气出口设定流量为Q，温度边界为Tc，迭代起始步计算出流量和温度为估计值，对叶片外流进行三维气动计算；得到叶片外表面温度T0、压力P以及换热系数WT。本发明中，三维数值计算的计算模型相比一维管网计算更接近真实的物理模型，精度更高，耗费的计算资源小，计算周期更短，在气动设计阶段考虑冷气及冷却结构对流场的影响，同时评估气动外型变化对已有冷却结构冷却效果的影响，可以得到整个流场的详实信息，因而可以进行更加细致的气动传热分析。The present invention discloses a novel method for evaluating the semi -gas-thermal coupling of a new complex cooling blade rapid three-dimensional pipe network. Set the flow rate as Q and the temperature boundary as T c , calculate the flow rate and temperature as estimated values in the initial iterative step, and perform a three-dimensional aerodynamic calculation on the outflow of the blade; obtain the blade outer surface temperature T 0 , pressure P and heat transfer coefficient W T . In the present invention, the calculation model of the three-dimensional numerical calculation is closer to the real physical model than the one-dimensional pipe network calculation, with higher precision, less computational resource consumption, and shorter calculation cycle. At the same time, the influence of aerodynamic shape changes on the cooling effect of the existing cooling structure can be evaluated, and detailed information of the entire flow field can be obtained, so that a more detailed aerodynamic heat transfer analysis can be carried out.
Description
Technical Field
The invention relates to the technical field of evaluation methods, in particular to a novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades.
Background
In the traditional turbine design process, pneumatic design and heat transfer design are carried out separately, so that although the design difficulty is reduced, the pneumatic calculation precision is reduced, and the heat transfer design is difficult; secondly, on one hand, the influence of a cooling structure on the aerodynamic efficiency is difficult to consider in the blade profile design and optimization stage, and the existence of the cooling structure can cause the surface temperature boundary layer and the speed boundary layer of the blade to be greatly changed, and finally, the influence on the efficiency of the turbine and the temperature field of the blade is generated; finally, the aerodynamic boundary of the blade is the basis of the cooling structure design, the change of the blade profile changes the pressure distribution on the surface of the blade, if the blade directly inherits the original cooling structure, the area of a cooling channel and the pressure boundary of an outlet are changed, so the cold air flow and flow distribution of the original cooling structure can be changed, and the difference of the pressure distribution can change the development of a boundary layer, thereby changing the outer heat exchange boundary of the cooling structure design.
The cooling effect is difficult to predict due to molded line change, in blade modification or optimization design, the original cooling structure and the blade profile combination obtained through optimization are subjected to accounting after pneumatic design is finished, the fact that both the pneumatic efficiency and the cooling effect cannot reach ideal design values is often found, and the traditional turbine design thought may cause the design effect to be unsatisfactory and the design work to be repeated.
Therefore, the influence of the cold air and the cooling structure on the flow field needs to be considered in the pneumatic design stage, and the influence of the change of the pneumatic appearance on the cooling effect of the existing cooling structure is evaluated at the same time, so that a novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for the complex cooling blades is provided.
Disclosure of Invention
In order to solve the technical problems mentioned in the background art, a novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades is provided.
In order to achieve the purpose, the invention adopts the following technical scheme:
a novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades comprises the following steps:
s1, presetting the temperature T of the outer wall of the bladewg＝Tw0，Tw0Is the estimated wall temperature; the cold air outlet is set to have a flow rate Q and a temperature margin TcCalculating the flow and the temperature as estimated values at the initial iteration step, and performing three-dimensional pneumatic calculation on the outflow of the blades; obtaining the temperature of the outer surface of the bladeT0Pressure P and heat transfer coefficient WTThe method is used as boundary conditions for calculation of an internal flow production one-dimensional pipe network and calculation of solid domain three-dimensional heat conduction;
s2, rapidly carrying out parametric modeling on the cooling structure by adopting a Hadamard development unit design method, and providing a geometric boundary for a Hadamard pipe network calculation program and a Hadamard turbine solid domain automatic structured grid program; the one-dimensional pipe network program is adopted to calculate the internal flow field,
the geometric boundary of the pipe network calculation is provided by a parameterized modeling program of a cooling structure of the Hadamard turbine, and the gas temperature T of the outer surface of the blade required by the pipe network calculation0The gas pressure P and the outer wall surface heat exchange coefficient WT are provided by three-dimensional calculation of an outer flow field;
s3, performing three-dimensional heat conduction calculation on the solid domain of the blade by adopting a third type of boundary conditions (wall temperature and heat exchange coefficient) on the inner wall surface and the outer wall surface, wherein the solid domain grid is provided by a solid domain automatic structured grid program of the Kazakh big turbine, the boundary of the outer wall surface is calculated from the outer flow in a three-dimensional mode, and the boundary of the inner wall surface is calculated from the inner flow one-dimensional pipe network;
s4, performing three-dimensional pneumatic calculation of blade outflow in the next process, and updating the temperature boundary T of the blade outer wall surfacewg＝Tw1，Tw1Updating the given flow and temperature boundary of the cold air outlet for the temperature of the outer wall surface of the blade obtained by the three-dimensional heat conduction calculation in the last step, wherein the flow and the temperature can be obtained in the step S2;
s5, comparing the aerodynamic efficiency of the blade and the temperature boundary of the outer wall surface obtained by the last two times of outflow three-dimensional calculation, if the aerodynamic efficiency and the temperature of the outer wall surface are converged, ending the three-dimensional pipe network half-gas thermal coupling calculation, and otherwise, repeating the steps S2-S5.
As a further description of the above technical solution:
the T is0The calculation formula of (a) is as follows:
T0＝Q*(C+int(atstep/1000)*B)R0
wherein R is0The rotating speed is C, the proportion of the initial rotating speed to the reference rotating speed is ATstep, the accumulative iteration step number calculated by CFX solving is ATstep, and the proportion of the rotating speed stepping value to the reference rotating speed is B;
the pressure P is calculated as follows:
P＝P0+int((atstep-int(atstep/1000)*1000)/100)*H，
wherein, P0For the initial value of the outlet pressure, atstep is the cumulative iteration step number calculated by solving CFX, and H is the pressure step value;
WT＝Sin(1/T0)*Cos(P0)。
as a further description of the above technical solution:
the cooling structure rapid parametric modeling comprises the following steps:
a1, selecting the inner and outer surfaces of the cold air outlet as a parameterization object, and storing X, Y coordinates of the extracted points in an array form to form four arrays; the four arrays are X, Y coordinates of the inner surface and the outer surface of the front edge laminate respectively, and the accurate positioning of the position of the cooling structure is realized through the operation of the array pointers;
b1, establishing a local coordinate system for the cooling structure positioned in the step A1, selecting a starting point and Pi of the cooling structure in the array in the step A, and determining a two-dimensional vector by adopting a local two-dimensional angular coordinate system;
c1, completing modeling according to the starting point of the cooling structure obtained in the step B1 and the vector with Pi perpendicular to the blade profile, and obtaining a three-dimensional solid model.
As a further description of the above technical solution:
in step B1, the specific steps for determining the two-dimensional vector are as follows: taking a vector vertical to the blade profile as a reference axis of a local two-dimensional angular coordinate system, taking the anticlockwise direction as the positive direction and the clockwise direction as the negative direction, taking a cooling structure starting point Pi, taking two points Pi-1 and Pi +1 adjacent to the starting point in the same array, and taking a vertical bisector of a connecting line of the two points Pi-1 and Pi +1 to obtain a vector of which the Pi is vertical to the blade profile as a two-dimensional vector.
As a further description of the above technical solution:
in step S2, the calculation of the internal flow field is as follows:
a2, introducing the established three-dimensional entity model into a finite element analysis tool ANSYS, carrying out finite element division on the three-dimensional entity model, defining material and element properties, and adding load and constraint conditions;
b2, obtaining the inherent mode of the blade by utilizing the dynamic mode analysis in the finite element analysis tool ANSYS, extracting the frequency and the mode required by the flow field analysis, and deriving the CSD finite element mesh node information of the computational structure dynamics of the blade surface to obtain a CSD node;
c2 establishes a flow field model of the blade, introduces the established three-dimensional entity model of the fan blade of the engine into a fluid dynamics simulation tool CFX, establishes a single-channel flow field model of the blade of the engine, divides fluid grids, and exports fluid grid nodes and unit information on the surface of the blade to obtain computational fluid dynamics CFD nodes.
As a further description of the above technical solution:
further comprising the steps of:
d2, obtaining the vibration displacement of the linear interpolation blade; interpolating a P-th order vibration mode on a CSD node on the surface of the blade onto a CFD node on the surface of the blade by adopting a three-dimensional linear interpolation method, wherein P is a positive integer and belongs to [1, 10], and the P serves as vibration displacement of all CFD nodes on the surface of the blade in a flow field; the small-range point selection interpolation can ensure the processing speed, and an area control factor is introduced to ensure the interpolation precision;
e2: generating a grid file required by flow field analysis through multi-layer dynamic grid processing;
distributing the vibration displacement of each CFD node on the surface of the blade to nodes corresponding to M layers of O-shaped grid areas around the blade according to the initial distance proportion of each layer by adopting a multilayer moving grid method, decreasing the vibration displacement from the surface of the blade to the outside in the normal direction, and finally generating grid files of all nodes of a flow field at each moment, wherein the displacement of the M layer is zero; the multilayer dynamic grid method is suitable for 1-M layers, wherein M is the number of layers of O-shaped grids in the flow field model;
f2: and calling a dynamic grid module to obtain each parameter in the flow field.
As a further description of the above technical solution:
the flow field analysis is realized by a fluid dynamics simulation tool CFX, and comprises the following steps: loading boundary conditions and initial conditions in the flow field model established in the step C2; the static temperature and total pressure are given to the inlet of the channel, the static pressure is given to the outlet, the interface boundary condition is given to the circulation symmetry plane, and the motion grid boundary condition is given to the surface of the blade; taking a steady field without adding a motion grid as an initial condition; the blade vibrates according to a P-th order natural mode, the motion period of the blade is the reciprocal of the frequency, the interval of each time step is the same, and an N-S equation is solved on each time step; finally, setting the output result to be that aerodynamic force and corresponding node displacement information are output at each time step; the time step is one N times of one movement period of the blade, N is the time step number of one period movement of the blade set by a user, and in order to ensure the simulation efficiency in practical application, N is taken as a positive integer and belongs to [30, 80 ].
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
in the invention, compared with a one-dimensional pipe network calculation, a calculation model of three-dimensional numerical calculation is closer to a real physical model, the precision is higher, the consumed calculation resource is small, the calculation period is shorter, the influence of cold air and a cooling structure on a flow field is considered in a pneumatic design stage, meanwhile, the influence of the change of the pneumatic appearance on the cooling effect of the existing cooling structure is evaluated, and the detailed information of the whole flow field can be obtained, so that more detailed pneumatic heat transfer analysis can be carried out.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to 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.
Examples
The invention provides a technical scheme that: a novel rapid three-dimensional pipe network half-gas thermal coupling evaluation method for complex cooling blades comprises the following steps:
s1, presetting blade outer wallTemperature T ofwg＝Tw0，Tw0Is the estimated wall temperature; the cold air outlet is set to have a flow rate Q and a temperature margin TcCalculating the flow and the temperature as estimated values at the initial iteration step, and performing three-dimensional pneumatic calculation on the outflow of the blades; obtaining the temperature T of the outer surface of the blade0Pressure P and heat transfer coefficient WTThe method is used as boundary conditions for calculation of an internal flow production one-dimensional pipe network and calculation of solid domain three-dimensional heat conduction;
s2, rapidly carrying out parametric modeling on the cooling structure by adopting a Hadamard development unit design method, and providing a geometric boundary for a Hadamard pipe network calculation program and a Hadamard turbine solid domain automatic structured grid program; the one-dimensional pipe network program is adopted to calculate the internal flow field,
the geometric boundary of the pipe network calculation is provided by a parameterized modeling program of a cooling structure of the Hadamard turbine, and the gas temperature T of the outer surface of the blade required by the pipe network calculation0The gas pressure P and the outer wall surface heat exchange coefficient WT are provided by three-dimensional calculation of an outer flow field;
s3, performing three-dimensional heat conduction calculation on the solid domain of the blade by adopting a third type of boundary conditions (wall temperature and heat exchange coefficient) on the inner wall surface and the outer wall surface, wherein the solid domain grid is provided by a solid domain automatic structured grid program of the Kazakh big turbine, the boundary of the outer wall surface is calculated from the outer flow in a three-dimensional mode, and the boundary of the inner wall surface is calculated from the inner flow one-dimensional pipe network;
s4, performing three-dimensional pneumatic calculation of blade outflow in the next process, and updating the temperature boundary T of the blade outer wall surfacewg＝Tw1，Tw1Updating the given flow and temperature boundary of the cold air outlet for the temperature of the outer wall surface of the blade obtained by the three-dimensional heat conduction calculation in the last step, wherein the flow and the temperature can be obtained in the step S2;
s5, comparing the aerodynamic efficiency of the blade and the temperature boundary of the outer wall surface obtained by the last two times of outflow three-dimensional calculation, if the aerodynamic efficiency and the temperature of the outer wall surface are converged, ending the three-dimensional pipe network half-gas thermal coupling calculation, and otherwise, repeating the steps S2-S5.
T0The calculation formula of (a) is as follows:
T0＝Q*(C+int(atstep/1000)*B)R0
wherein R is0The rotating speed is C, the proportion of the initial rotating speed to the reference rotating speed is ATstep, the accumulative iteration step number calculated by CFX solving is ATstep, and the proportion of the rotating speed stepping value to the reference rotating speed is B;
the pressure P is calculated as follows:
P＝P0+int((atstep-int(atstep/1000)*1000)/100)*H，
wherein, P0For the initial value of the outlet pressure, atstep is the cumulative iteration step number calculated by solving CFX, and H is the pressure step value;
WT＝Sin(1/T0)*Cos(P0)。
the cooling structure rapid parametric modeling comprises the following steps:
a1, selecting the inner and outer surfaces of the cold air outlet as a parameterization object, and storing X, Y coordinates of the extracted points in an array form to form four arrays; the four arrays are X, Y coordinates of the inner surface and the outer surface of the front edge laminate respectively, and the accurate positioning of the position of the cooling structure is realized through the operation of the array pointers;
b1, establishing a local coordinate system for the cooling structure positioned in the step A1, selecting a starting point and Pi of the cooling structure in the array in the step A, and determining a two-dimensional vector by adopting a local two-dimensional angular coordinate system;
c1, completing modeling according to the starting point of the cooling structure obtained in the step B1 and the vector with Pi perpendicular to the blade profile, and obtaining a three-dimensional solid model.
In step B1, the specific steps for determining the two-dimensional vector are as follows: and taking a vector vertical to the blade profile as a reference axis of a local two-dimensional angular coordinate system, taking the anticlockwise direction as the positive direction and the clockwise direction as the negative direction, taking a cooling structure starting point Pi, taking two points Pi-1 and Pi +1 adjacent to the starting point in the same array, and taking a vertical bisector of a connecting line of the two points Pi-1 and Pi +1 to obtain a vector of which the Pi is vertical to the blade profile as a two-dimensional vector.
In step S2, the calculation of the internal flow field is as follows:
a2, introducing the established three-dimensional entity model into a finite element analysis tool ANSYS, carrying out finite element division on the three-dimensional entity model, defining material and element properties, and adding load and constraint conditions;
b2, obtaining the inherent mode of the blade by utilizing the dynamic mode analysis in the finite element analysis tool ANSYS, extracting the frequency and the mode required by the flow field analysis, and deriving the CSD finite element mesh node information of the computational structure dynamics of the blade surface to obtain a CSD node;
c2 establishes a flow field model of the blade, introduces the established three-dimensional entity model of the fan blade of the engine into a fluid dynamics simulation tool CFX, establishes a single-channel flow field model of the blade of the engine, divides fluid grids, and exports fluid grid nodes and unit information on the surface of the blade to obtain computational fluid dynamics CFD nodes.
Further comprising the steps of:
d2, obtaining the vibration displacement of the linear interpolation blade; interpolating a P-th order vibration mode on a CSD node on the surface of the blade onto a CFD node on the surface of the blade by adopting a three-dimensional linear interpolation method, wherein P is a positive integer and belongs to [1, 10], and the P serves as vibration displacement of all CFD nodes on the surface of the blade in a flow field; the small-range point selection interpolation can ensure the processing speed, and an area control factor is introduced to ensure the interpolation precision;
e2: generating a grid file required by flow field analysis through multi-layer dynamic grid processing;
distributing the vibration displacement of each CFD node on the surface of the blade to nodes corresponding to M layers of O-shaped grid areas around the blade according to the initial distance proportion of each layer by adopting a multilayer moving grid method, decreasing the vibration displacement from the surface of the blade to the outside in the normal direction, and finally generating grid files of all nodes of a flow field at each moment, wherein the displacement of the M layer is zero; the multilayer moving grid method is suitable for 1-M layers, wherein M is the number of layers of O-shaped grids in the flow field model;
f2: and calling a dynamic grid module to obtain each parameter in the flow field.
The flow field analysis is realized by a fluid dynamics simulation tool CFX, and comprises the following steps: loading boundary conditions and initial conditions in the flow field model established in the step C2; the static temperature and total pressure are given to the inlet of the channel, the static pressure is given to the outlet, the interface boundary condition is given to the circulation symmetry plane, and the motion grid boundary condition is given to the surface of the blade; taking a steady field without adding a motion grid as an initial condition; the blade vibrates according to a P-th order natural mode, the motion period of the blade is the reciprocal of the frequency, the interval of each time step is the same, and an N-S equation is solved on each time step; finally, setting the output result to be that aerodynamic force and corresponding node displacement information are output at each time step; the time step is one N times of one movement period of the blade, N is the time step number of one period movement of the blade set by a user, and in order to ensure the simulation efficiency in practical application, N is taken as a positive integer and belongs to [30, 80 ].
The working principle is as follows: compared with a one-dimensional pipe network calculation, the calculation model of the three-dimensional numerical calculation is closer to a real physical model, the precision is higher, the consumed calculation resources are small, the calculation period is shorter, the influence of cold air and a cooling structure on a flow field is considered in the pneumatic design stage, meanwhile, the influence of the pneumatic appearance change on the cooling effect of the existing cooling structure is evaluated, and the detailed information of the whole flow field can be obtained, so that more detailed pneumatic heat transfer analysis can be carried out.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
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