CN112507586A - Rapid assessment method for two-dimensional temperature and strength of turbine air cooling blade - Google Patents
Rapid assessment method for two-dimensional temperature and strength of turbine air cooling blade Download PDFInfo
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Abstract
The application belongs to the field of aircraft engines, and particularly relates to a quick evaluation method for two-dimensional temperature and strength of a turbine air-cooled blade. The method comprises the following steps: the method comprises the following steps: acquiring a two-dimensional section of the turbine air-cooling blade; step two: constructing a finite element model of a two-dimensional section, and carrying out mesh division on the finite element model to obtain node data of a mesh; step three: acquiring material parameters and temperature field calculation boundary conditions of the turbine air cooling blades, and calculating temperature values of all nodes of a grid to obtain temperature fields of the turbine air cooling blades; step four: the temperature field of the turbine air-cooled blade is equivalent to a thermal load, the thermal load and a preset pressure load are simultaneously applied to a finite element model, and the displacement value and the stress value of each node of the grid are calculated to obtain the displacement field and the stress field of the turbine air-cooled blade; the same set of grids are adopted in the calculation of the temperature field, the displacement field and the stress field. According to the method and the device, the calculation efficiency and the calculation convenience can be improved on the basis of ensuring the calculation accuracy.
Description
Technical Field
The application belongs to the field of aircraft engines, and particularly relates to a quick evaluation method for two-dimensional temperature and strength of a turbine air-cooled blade.
Background
At present, commercial software is mostly adopted for calculating the temperature and strength of the turbine cooling blade, and the unified thought is that a two-dimensional geometric model of the blade is input for grid division, and calculation is carried out by establishing a surface effect unit and inputting a heat exchange boundary through a gas-heat coupling algorithm or a distribution algorithm. However, both the gas-thermal coupling algorithm and the method for establishing the input boundary of the surface effect unit require the input of a two-dimensional geometric model of the blade, and due to the fact that different grids are adopted for temperature and strength, calculation operation is complex, calculation time is long due to the fact that intermediate manual operation, a plurality of calculation steps and the like, and a long period is consumed when the blade is subjected to scheme design.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a method for rapidly evaluating two-dimensional temperature and strength of a turbine air cooling blade, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a method for rapidly evaluating two-dimensional temperature and strength of a turbine air cooling blade comprises the following steps:
the method comprises the following steps: acquiring a two-dimensional section of the turbine air-cooling blade;
step two: constructing a finite element model of the two-dimensional section, and carrying out mesh division on the finite element model to obtain node data of a mesh;
step three: acquiring material parameters and temperature field calculation boundary conditions of the turbine air cooling blades, and calculating temperature values of all nodes of the grids to obtain temperature fields of the turbine air cooling blades;
step four: the temperature field of the turbine air cooling blade is equivalent to a heat load, the heat load and a preset pressure load are simultaneously applied to the finite element model, and the displacement value and the stress value of each node of the grid are calculated to obtain the displacement field and the stress field of the turbine air cooling blade;
wherein, the same set of grids are adopted in the calculation of the temperature field, the displacement field and the stress field.
Optionally, in the second step, the constructing a finite element model of the two-dimensional cross section includes:
s201, dividing the blade section into an outer molded surface and an inner molded surface, selecting an outer molded line on the outer molded surface, and selecting an inner molded line on the inner molded surface;
s202, selecting nodes on the outer molded line and the inner molded line, and sequencing the nodes according to a clockwise or anticlockwise sequence;
and S203, drawing a closed finite element model according to each node.
Optionally, in S201, when an outer mold line is selected on the outer mold surface, and an inner mold line is selected on the inner mold surface, the following principle is satisfied:
the external line segments cannot be selfed;
the inner line segment cannot be selfed;
the inner profile is not allowed to exceed the outer profile.
Optionally, in S202, when nodes are selected on the outer profile and the inner profile, if the distance between two adjacent nodes exceeds the preset maximum segment length limit, linear interpolation is performed according to the maximum segment length limit, so that the selected nodes meet the limit condition.
Optionally, in S203, the drawing a closed finite element model according to each node includes:
dividing the internal contour node into a closed graph node and a non-closed graph node;
connecting the closed graph nodes into a plurality of closed graphs;
and connecting the non-closed graph nodes of the inner profile nodes and the outer profile nodes into a closed graph.
Optionally, in the second step, the meshing the finite element model, and acquiring node data of a mesh includes:
s204, judging whether the inner type wire nodes and the outer type wire nodes need to be encrypted or deleted, if so, encrypting or deleting the inner type wire nodes and the outer type wire nodes in one of the following modes;
predetermined multiple encryption or deletion: if encryption or deletion is selected to be N times, adding or deleting N nodes between two adjacent nodes in the selected area in a linear interpolation mode;
predetermined interval encryption or puncturing: if the control node distance L is selected, adding or deleting nodes in the selected area to enable the distance between two adjacent nodes to be L;
s205, carrying out grid division on the finite element model based on the encrypted or deleted molded line node pair to generate a plurality of grid units;
and S206, acquiring node data of each grid unit.
Alternatively,
in S204, encrypting the grid by 1 time, and increasing 1 node between two adjacent nodes by adopting a linear interpolation mode;
in S205, the finite element model is subjected to mesh division by using a Delaunay point-by-point insertion algorithm for fast centroid insertion based on the Watson algorithm, so as to generate a plurality of triangular mesh units with 3 nodes, and the triangular mesh units with 3 nodes are converted into triangular mesh units with 6 nodes;
in S206, node data of each triangle mesh unit of 6 nodes is acquired.
Optionally, in step three, the obtaining material parameters and temperature field calculation boundary conditions of the turbine air-cooled blade, and calculating temperature values of each node of the grid, to obtain the temperature field of the turbine air-cooled blade includes:
s301, obtaining material parameters and temperature field calculation boundary conditions of the turbine air cooling blade;
s302, calculating boundary conditions according to the material parameters and the temperature field of the turbine air cooling blade, and acquiring a series of discrete points on a material heat conductivity coefficient-temperature curve of the turbine air cooling blade, wherein each discrete point corresponds to a temperature value and a material heat conductivity coefficient under the temperature value;
s303, constructing an initial temperature field;
s304, acquiring a series of material heat conductivity coefficients under a temperature field through piecewise linear interpolation;
s305, calculating by adopting a finite element method according to the heat conductivity coefficient of the material in the S304 to obtain a new temperature field;
and S306, calculating the maximum difference value of the temperature fields obtained twice before and after, if the maximum difference value is smaller than a preset threshold value, judging that the calculation is converged, and otherwise, repeating S304-S306 until the calculation is converged.
Optionally, in S301, the temperature field calculation boundary condition includes a gas side boundary condition and a cold gas side boundary condition, which is in the form of one of a constant temperature boundary condition, a constant thermal current density boundary condition, and a convective heat transfer boundary condition, the gas side boundary is input through nodes on a plurality of outer contours, and the cold gas measurement boundary is given by segments to the cold gas boundary on the node where the inner contours of different areas are located, and is interpolated linearly to the mesh nodes of the entire outer contours and the entire inner contours, respectively.
Alternatively,
if the evaluated blade is a guide blade and the input boundary condition of the gas side is a convective heat transfer boundary condition, correcting the nonuniformity of the outlet temperature of the combustion chamber:
Tpeak＝(1+OTDF)×T4+OTDF×T3
Tg＝Tpeak×Tg/Tmax
wherein OTDF is the combustion chamber outlet temperature non-uniformity, T4Is the average total temperature, T, of the blade inlet3Is the average total temperature, T, of the combustion chamber inlet gas flowgFor gas heat exchange temperature, TmaxThe highest total temperature of the gas at the inlet of the blade;
if the surface of the turbine air-cooled blade is provided with an air film hole and the input boundary condition of the gas side is a convective heat transfer boundary condition, performing air film correction on the convective heat transfer boundary condition of the gas side:
and (3) correcting the air film at the front edge of the blade:
η1＝-0.028(X/MS)0.577+0.45
Tfilm＝(1-η1)×Tg+η1×Tc
and (3) correcting the air film of the blade except the front edge:
η2＝-0.014(X/MS)0.654+0.5
Tfilm＝(1-η2)×Tg+η2×Tc
wherein eta is1、η2For the air film cooling effect, M is the density flow ratio of cold fluid and hot fluid, S is the height of the jet nozzle of the two-dimensional slot, X is the downstream length of the air film, and T isgFor gas heat exchange temperature, TcFor the film discharge of the cold gas temperature, TfilmCorrected temperature for air film.
The invention has at least the following beneficial technical effects:
the quick evaluation method for the two-dimensional temperature and the strength of the turbine air cooling blade can improve the calculation efficiency and the calculation convenience on the basis of ensuring the calculation accuracy.
Drawings
FIG. 1 is a flow chart of a method for rapid two-dimensional temperature and strength assessment of a turbine air-cooled blade according to an embodiment of the present application;
FIG. 2 is a schematic cross-sectional view of a turbine air cooling blade according to an embodiment of the present application;
FIG. 3 is a schematic view of a finite element model of a turbine air cooling blade according to an embodiment of the present application;
FIG. 4 is a schematic illustration of temperature boundary conditions for a turbine air cooling blade according to an embodiment of the present application;
FIG. 5 is a schematic graph comparing the temperature field of a turbine air cooled blade obtained in accordance with an embodiment of the present application with results from ANSYS;
fig. 6 is a graph showing the comparison of the x-direction displacement of the turbine air-cooled blade obtained in the embodiment of the present application with the results of ANSYS;
fig. 7 is a schematic diagram comparing the results of y-direction displacement of the turbine air-cooled blade obtained in one embodiment of the present application with ANSYS;
fig. 8 is a graph illustrating the comparison of x-direction stress of a turbine air-cooled blade obtained according to an embodiment of the present application with the results of ANSYS;
fig. 9 is a graph showing a comparison of the y-direction stress of the turbine air-cooled blade obtained in the embodiment of the present application with the result of ANSYS.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application will be described in further detail with reference to fig. 1 to 9.
The application provides a method for rapidly evaluating two-dimensional temperature and strength of a turbine air cooling blade, as shown in fig. 1, comprising the following steps:
the method comprises the following steps: acquiring a two-dimensional section of the turbine air-cooling blade;
step two: constructing a finite element model of a two-dimensional section, and carrying out mesh division on the finite element model to obtain node data of a mesh;
step three: acquiring material parameters and temperature field calculation boundary conditions of the turbine air cooling blades, and calculating temperature values of all nodes of a grid to obtain temperature fields of the turbine air cooling blades;
step four: the temperature field of the turbine air-cooled blade is equivalent to a thermal load, the thermal load and a preset pressure load are simultaneously applied to a finite element model, and the displacement value and the stress value of each node of the grid are calculated to obtain the displacement field and the stress field of the turbine air-cooled blade;
wherein, the same set of grids are adopted in the calculation of the temperature field, the displacement field and the stress field.
In the rapid evaluation method for the two-dimensional temperature and the strength of the turbine air-cooled blade, when the temperature field, the displacement field and the stress field of the turbine air-cooled blade are calculated, a two-dimensional steady-state thermal-structure uncoupled statics finite element calculation method based on linear elasticity and one-way influence is adopted to analyze the heat conduction process and the deformation of the blade section, and the adopted basic assumptions comprise:
1) the thermal analysis and the stress analysis are linear elasticity;
2) the coupling between heat and structural deformation is not considered, i.e. it is assumed that the influence between temperature field, thermal load, displacement field is unidirectional.
Specifically, in the second step, constructing the finite element model of the two-dimensional cross section includes:
s201, dividing the section of the blade into an outer molded surface and an inner molded surface, selecting an outer molded line on the outer molded surface, and selecting an inner molded line on the inner molded surface;
in this embodiment, leaf data input supporting multiple data formats: data files such as TXT, DAT and the like; DXF formatted metafile: the DXF file drawn by CAD software such as AutoCAD and the like can support the loading of entities such as circles, arcs, two-dimensional ambiguous lines, three-dimensional ambiguous lines, sample lines, straight lines, ellipses and the like; UG software outputs a point set format file, and a linear simulation method is adopted to draw a molded line by loading a plurality of nodes on the boundary.
S202, selecting nodes on the outer molded line and the inner molded line, and sequencing the nodes according to a clockwise or anticlockwise sequence;
and S203, drawing a closed finite element model according to each node.
In this embodiment, in S201, when an outer molded line is selected on the outer molded surface and an inner molded line is selected on the inner molded surface, the following principle is satisfied:
the external line segments cannot be selfed;
the inner line segment cannot be selfed;
the inner profile is not allowed to exceed the outer profile.
In S202, when selecting nodes on the outer profile and the inner profile, if the distance between two adjacent nodes exceeds the preset maximum segment length limit, linear interpolation is performed according to the maximum segment length limit, so that the selected nodes meet the limit condition.
In S203, drawing a closed finite element model from the respective nodes includes:
dividing the internal contour node into a closed graph node and a non-closed graph node;
connecting the closed graph nodes into a plurality of closed graphs;
and connecting the non-closed graph nodes of the inner profile nodes and the outer profile nodes into a closed graph.
In an embodiment of the present application, in the second step, the mesh division is performed on the finite element model, and the obtaining node data of the mesh includes:
s204, judging whether the inner profile line node and the outer profile line node need to be encrypted or deleted, if so, encrypting or deleting by one of the following modes;
predetermined multiple encryption or deletion: if encryption or deletion by N times is selected, adding or deleting N nodes (the air film hole is not encrypted) between two adjacent nodes in the selected area in a linear interpolation mode;
predetermined interval encryption or puncturing: if the control node distance L is selected, adding or deleting nodes in the selected area to enable the distance between two adjacent nodes to be L (the air film hole opening is not encrypted);
in this embodiment, the mesh size is designed by a method of locally adding or deleting nodes or controlling the overall division size, for example, if the mesh is encrypted by 1 time, 1 node is added between two adjacent nodes by adopting a linear interpolation method;
s205, carrying out grid division on the finite element model based on the encrypted or deleted molded line node pair to generate a plurality of grid units;
in this embodiment, a Delaunay point-by-point insertion algorithm for fast inserting a centroid based on a Watson algorithm is adopted to perform mesh division on a finite element model to generate a plurality of triangular mesh units with 3 nodes, and the triangular mesh units with 3 nodes are converted into triangular mesh units with 6 nodes;
s206, acquiring node data of each grid unit; in this embodiment, the node data of each triangular mesh unit with 6 nodes is obtained, and the output node data may include node coordinates, the number of units, the numbers of nodes on the inner and outer boundaries, and the like.
According to the method for rapidly evaluating the two-dimensional temperature and the strength of the turbine air cooling blade, the grid used for calculation is divided based on the input geometric nodes, and local geometric points are encrypted or deleted at the positions where boundary points are sparse or dense through graphic display to form a proper size, so that grid division is performed. Meanwhile, the mesh control is performed by setting the total division size, and the maximum division size is generally defined at about 1% of the image size. The method avoids that the set boundary nodes are too sparse, so that the grid unit possibly penetrates through the inner and outer molded lines to cause unreasonable temperature stress calculation results, the given boundary points are too compact, or the density uniformity is unreasonable, so that the grid division is possibly subjected to accuracy overflow errors.
The application adopts a rapid automatic division method to carry out two-dimensional structured grid division, and specifically comprises the following steps: firstly, boundary data of a finite element model is obtained, triangular mesh division is carried out, and discretized triangular mesh node data and unit data of 3 nodes are output, wherein the node data comprises node coordinates, node numbers of units and the like; and then converting the node and unit data of the triangular mesh with 3 nodes into triangular units with 6 nodes according to the node and unit data of the triangular mesh with 3 nodes, and outputting the converted units, node data and boundary point numbers. The mesh division adopts a Delaunay point-by-point insertion algorithm for quickly inserting centroids based on a Watson algorithm, has the advantages of simple and reliable method, simultaneous generation of nodes and units and easy realization of smooth transition between density meshes, and effectively improves the speed and efficiency of finite element mesh generation.
In one embodiment of the present application, in step three, obtaining material parameters and temperature field calculation boundary conditions of the turbine air-cooled blade, and calculating a temperature value of each node of the grid, to obtain the temperature field of the turbine air-cooled blade includes:
s301, obtaining material parameters and temperature field calculation boundary conditions of the turbine air cooling blade;
s302, calculating boundary conditions according to material parameters and a temperature field of the turbine air-cooled blade, and acquiring a series of discrete points on a material heat conductivity coefficient-temperature curve of the turbine air-cooled blade, wherein each discrete point corresponds to a temperature value and a material heat conductivity coefficient under the temperature value;
s303, constructing an initial temperature field;
s304, acquiring a series of material heat conductivity coefficients under a temperature field through piecewise linear interpolation;
s305, calculating by adopting a finite element method according to the heat conductivity coefficient of the material in the S304 to obtain a new temperature field;
and S306, calculating the maximum difference value of the temperature fields obtained twice before and after, if the maximum difference value is smaller than a preset threshold value, judging that the calculation is converged, and otherwise, repeating S304-S306 until the calculation is converged.
In the calculation of the temperature field of the turbine air cooling blade, a curve of the heat conductivity value required by temperature calculation along with the temperature change is obtained, the material parameters can change along with the temperature change, the material of the unit in the actual calculation process is the material parameters under the average temperature of the unit nodes, and each calculation boundary is linearly interpolated to each grid boundary of the inner surface and the outer surface of the blade.
In S301, the temperature field calculation boundary condition includes a gas side boundary condition and a cold side boundary condition, which may be one of a constant temperature boundary condition, a constant heat flow density boundary condition, and a convective heat transfer boundary condition. The constant temperature boundary represents the temperature of a given node, the constant heat flow density boundary represents the given heat flow density, and the convection heat transfer boundary represents the heat transfer temperature and the heat transfer coefficient of the given node. The gas side boundary is input through nodes on a plurality of outer lines, and the cold air measuring boundary is given to the cold air boundary on the node where the inner lines of different areas are located in a segmented mode and is respectively interpolated to grid nodes of the whole outer lines and the whole inner lines through linear interpolation.
Advantageously, in this embodiment, if the evaluated vanes are guide vanes and the input gas side boundary condition is a convective heat transfer boundary condition, then the combustor exit temperature non-uniformity correction is performed on them:
Tpeak＝(1+OTDF)×T4+OTDF×T3
Tg＝Tpeak×Tg/Tmax
wherein OTDF is the combustion chamber outlet temperature non-uniformity, T4Is the average total temperature, T, of the blade inlet3Is the average total temperature, T, of the combustion chamber inlet gas flowgFor gas heat exchange temperature, TmaxThe highest total temperature of the gas at the inlet of the blade;
advantageously, in this embodiment, if the surface of the turbine air-cooled blade is provided with a gas film hole, and the input gas-side boundary condition is a convective heat transfer boundary condition, the gas film correction is performed on the gas-side convective heat transfer boundary condition:
and (3) correcting the air film at the front edge of the blade:
η1＝-0.028(X/MS)0.577+0.45
Tfilm＝(1-η1)×Tg+η1×Tc
and (3) correcting the air film of the blade except the front edge:
η2＝-0.014(X/MS)0.654+0.5
Tfilm＝(1-η2)×Tg+η2×Tc
wherein eta is1、η2For air film cooling effect, M is the density flow ratio of cold fluid and hot fluid, and S isThe height of the jet nozzle of the two-dimensional seam, X is the downstream length of the air film, TgFor gas heat exchange temperature, TcFor the film discharge of the cold gas temperature, TfilmCorrected temperature for air film.
In the fourth step, the calculating of the displacement field and the stress field of the turbine air-cooled blade specifically includes:
firstly, the displacement field, the stress field calculation and the temperature field calculation adopt the same set of grids;
then, acquiring the temperature field calculated in the third step, and material parameters and stress boundary conditions of the turbine air-cooled blade required by stress calculation, wherein the material parameters comprise curves of material density, elastic modulus, Poisson's ratio, thermal expansion coefficient and the like which change along with the temperature, and setting pressure values on boundary nodes according to actual conditions;
and finally, equating the temperature field of the turbine air cooling blade to be a heat load, simultaneously applying the heat load and a preset pressure load on the finite element model, and calculating the displacement value and the stress value of each node of the grid by a finite element method to obtain the displacement field and the stress field of the turbine air cooling blade.
In the application, the same set of grids are adopted for the calculation of the two-dimensional temperature field, the displacement field and the stress field of the blade, the calculation steps of data interpolation and transmission brought by the calculation of the temperature field and the strength of the blade by adopting different grids are omitted, the error caused by the calculation is avoided, and the calculation speed is increased.
In one embodiment of the application, a two-dimensional temperature and intensity calculation process for an engine guide vane with a film hole is provided. Firstly, a finite element model of a blade section is established after the section of the turbine air cooling blade is obtained, the inner and outer molded lines of the molded line of the turbine air cooling blade are shown in fig. 2, the curve 0 represents the outer molded line, and the curves 1 and 2 represent the inner molded line. Given the size of the mesh partition, a triangular finite element mesh is generated, as shown in fig. 3, the size of the mesh partition is 0.4, and the mesh partition is converted into a 6-node triangular unit, in this embodiment, there are 9002 nodes and 4100 units. Given convective heat transfer boundary conditions, i.e. given vanesThe convection heat transfer coefficient and the ambient temperature of the gas side and the cold side of the blade gas side are 798W/(m)2And DEG C), the ambient temperature is 1145 ℃, and as shown in figure 4, the front cavity and the rear cavity in the inner cavity are divided into 10 sections, and boundaries are respectively given. As shown in fig. 5, when the temperature field calculation result (left) obtained by the present application is compared with the result (right) of ANSYS, it can be seen that the result is substantially consistent with ANSYS, and the reliability of the method is also verified.
Further, as shown in fig. 6 to 9, the finite element model and the thermal analysis model of the static analysis employ the same set of meshes. The static analysis needs to exert constraint on the structure, a spring unit is added to each boundary point in the model of the embodiment, and the rigidity of the unit is 1/1e of the minimum value of diagonal elements of the structural rigidity matrix5And applying distributed load to the inner and outer boundaries, wherein the load direction is vertical to the boundaries, the pressure intensity of the gas side is approximately 200000Pa, the pressure intensity of the front cavity is 591651Pa, and the pressure intensity of the rear cavity is 202250Pa, so that the calculation results of the displacement field and the stress field are obtained. Comparing the calculation result of the application with the result of ANSYS, it can be seen that the result of the application is basically consistent with the result of ANSYS.
The quick evaluation method for the two-dimensional temperature and the strength of the turbine air cooling blade is high in calculation efficiency and accuracy and suitable for various types of turbine cooling blades.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within 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 (10)
1. A method for rapidly evaluating two-dimensional temperature and strength of a turbine air cooling blade is characterized by comprising the following steps:
the method comprises the following steps: acquiring a two-dimensional section of the turbine air-cooling blade;
step two: constructing a finite element model of the two-dimensional section, and carrying out mesh division on the finite element model to obtain node data of a mesh;
step three: acquiring material parameters and temperature field calculation boundary conditions of the turbine air cooling blades, and calculating temperature values of all nodes of the grids to obtain temperature fields of the turbine air cooling blades;
step four: the temperature field of the turbine air cooling blade is equivalent to a heat load, the heat load and a preset pressure load are simultaneously applied to the finite element model, and the displacement value and the stress value of each node of the grid are calculated to obtain the displacement field and the stress field of the turbine air cooling blade;
wherein, the same set of grids are adopted in the calculation of the temperature field, the displacement field and the stress field.
2. The method of claim 1, wherein in the second step, the constructing the finite element model of the two-dimensional cross section includes:
s201, dividing the blade section into an outer molded surface and an inner molded surface, selecting an outer molded line on the outer molded surface, and selecting an inner molded line on the inner molded surface;
s202, selecting nodes on the outer molded line and the inner molded line, and sequencing the nodes according to a clockwise or anticlockwise sequence;
and S203, drawing a closed finite element model according to each node.
3. The method of claim 2, wherein in step S201, when an outer profile is selected on the outer profile and an inner profile is selected on the inner profile, the following principles are satisfied:
the external line segments cannot be selfed;
the inner line segment cannot be selfed;
the inner profile is not allowed to exceed the outer profile.
4. The method according to claim 3, wherein in step S202, when the nodes are selected on the outer profile and the inner profile, if the distance between two adjacent nodes exceeds a preset maximum segment length limit, linear interpolation is performed according to the maximum segment length limit, so that the selected nodes meet the limit condition.
5. The method for rapidly estimating the two-dimensional temperature and strength of the turbine air-cooled blade according to claim 4, wherein the step S203 of drawing a closed finite element model according to each node includes:
dividing the internal contour node into a closed graph node and a non-closed graph node;
connecting the closed graph nodes into a plurality of closed graphs;
and connecting the non-closed graph nodes of the inner profile nodes and the outer profile nodes into a closed graph.
6. The method of claim 2, wherein the step two of meshing the finite element model to obtain node data of a mesh comprises:
s204, judging whether the inner type wire nodes and the outer type wire nodes need to be encrypted or deleted, if so, encrypting or deleting the inner type wire nodes and the outer type wire nodes in one of the following modes;
predetermined multiple encryption or deletion: if encryption or deletion is selected to be N times, adding or deleting N nodes between two adjacent nodes in the selected area in a linear interpolation mode;
predetermined interval encryption or puncturing: if the control node distance L is selected, adding or deleting nodes in the selected area to enable the distance between two adjacent nodes to be L;
s205, carrying out grid division on the finite element model based on the encrypted or deleted molded line nodes to generate a plurality of grid units;
and S206, acquiring node data of each grid unit.
7. The method for rapid evaluation of two-dimensional temperature and strength of turbine air-cooled blades according to claim 6,
in S204, encrypting the grid by 1 time, and increasing 1 node between two adjacent nodes by adopting a linear interpolation mode;
in S205, the finite element model is subjected to mesh division by using a Delaunay point-by-point insertion algorithm for fast centroid insertion based on the Watson algorithm, so as to generate a plurality of triangular mesh units with 3 nodes, and the triangular mesh units with 3 nodes are converted into triangular mesh units with 6 nodes;
in S206, node data of each triangle mesh unit of 6 nodes is acquired.
8. The method according to claim 1, wherein in step three, the obtaining of material parameters of the turbine air-cooled blades and boundary conditions of temperature field calculation, and the calculating of temperature values at each node of the grid, the obtaining of the temperature field of the turbine air-cooled blades includes:
s301, obtaining material parameters and temperature field calculation boundary conditions of the turbine air cooling blade;
s302, calculating boundary conditions according to the material parameters and the temperature field of the turbine air cooling blade, and acquiring a series of discrete points on a material heat conductivity coefficient-temperature curve of the turbine air cooling blade, wherein each discrete point corresponds to a temperature value and a material heat conductivity coefficient under the temperature value;
s303, constructing an initial temperature field;
s304, acquiring a series of material heat conductivity coefficients under a temperature field through piecewise linear interpolation;
s305, calculating by adopting a finite element method according to the heat conductivity coefficient of the material in the S304 to obtain a new temperature field;
and S306, calculating the maximum difference value of the temperature fields obtained twice before and after, if the maximum difference value is smaller than a preset threshold value, judging that the calculation is converged, and otherwise, repeating S304-S306 until the calculation is converged.
9. The method for rapidly evaluating two-dimensional temperature and strength of turbine air-cooled blades according to claim 8, wherein in S301, the temperature field calculation boundary conditions include a gas side boundary condition and a cold side boundary condition, which is in the form of one of a constant temperature boundary condition, a constant heat flow density boundary condition and a convective heat transfer boundary condition, the gas side boundary is input through nodes on a plurality of outer contours, and the cold gas side boundary is segmented to give cold gas boundaries on nodes where the inner contours are located in different areas, and is linearly interpolated to grid nodes of the entire outer contours and the entire inner contours, respectively.
10. The method for rapid evaluation of two-dimensional temperature and strength of turbine air-cooled blades according to claim 9,
if the evaluated blade is a guide blade and the input boundary condition of the gas side is a convective heat transfer boundary condition, correcting the nonuniformity of the outlet temperature of the combustion chamber:
Tpeak＝(1+OTDF)×T4+OTDF×T3
Tg＝Tpeak×Tg/Tmax
wherein OTDF is the combustion chamber outlet temperature non-uniformity, T4Is the average total temperature, T, of the blade inlet3Is the average total temperature, T, of the combustion chamber inlet gas flowgFor gas heat exchange temperature, TmaxThe highest total temperature of the gas at the inlet of the blade;
if the surface of the turbine air-cooled blade is provided with an air film hole and the input boundary condition of the gas side is a convective heat transfer boundary condition, performing air film correction on the convective heat transfer boundary condition of the gas side:
and (3) correcting the air film at the front edge of the blade:
η1＝-0.028(X/MS)0.577+0.45
Tfilm＝(1-η1)×Tg+η1×Tc
and (3) correcting the air film of the blade except the front edge:
η2＝-0.014(X/MS)0.654+0.5
Tfilm＝(1-η2)×Tg+η2×Tc
wherein eta is1、η2For the air film cooling effect, M is the density flow ratio of cold fluid and hot fluid, S is the height of the jet nozzle of the two-dimensional slot, X is the downstream length of the air film, and T isgFor gas heat exchange temperature, TcFor the film discharge of the cold gas temperature, TfilmCorrected temperature for air film.
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