CN115994991A - Method for rapidly converting cold state and hot state of turbine blade model - Google Patents
Method for rapidly converting cold state and hot state of turbine blade model Download PDFInfo
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- CN115994991A CN115994991A CN202310036722.1A CN202310036722A CN115994991A CN 115994991 A CN115994991 A CN 115994991A CN 202310036722 A CN202310036722 A CN 202310036722A CN 115994991 A CN115994991 A CN 115994991A
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Abstract
The invention provides a method for rapidly converting cold and hot states of a turbine blade model, which comprises the following steps: based on the existing thermal state blade, performing high-precision finite element grid division on the thermal state blade to obtain grid node coordinates S. At the 1 st iteration, the initial value G of the cold state blade iterative solution is obtained 1 Taken as S and at G 1 Applying conditions such as pneumatic load, temperature field, centrifugal load and the like, and obtaining a thermal state blade iterative solution S through finite element calculation 1 And grid node displacement U 1 Will S 1 Comparing the coordinates of each node with S, and calculating residual errors E of each node 1 . If E 1 The maximum value is greater than 0.01mm, the iteration is not converged, and the iteration is performed through S and U 1 Construction of updated cold state blade iterative solution G 2 And the iterative process is repeated. After the nth iteration converges, the cold state in this iterationBlade iterative solution G n The cold state blade is obtained by converting the hot state blade S under the conditions of aerodynamic load, temperature field and centrifugal load. The invention not only ensures the conversion precision, but also solves the problem of large calculation amount.
Description
Technical Field
The invention belongs to the technical field of turbine blades of engines, and particularly relates to a method for rapidly converting cold and hot states of a turbine blade model.
Background
Turbine rotor blades of an aeroengine are one of the most important parts of the engine. The cold state blade has no load and no stress, and can be directly produced and manufactured; the thermal state blade is a working blade under the conditions of pneumatic load, temperature field, centrifugal load and the like, and stress concentration occurs locally at the moment. Since the stress condition of the hot blade cannot be known, the hot blade is unloaded, and the cold blade cannot be directly obtained. Through repeated iteration, the cold-hot state conversion of the blade can be realized.
After the pneumatic design of the centrifugal impeller compressor or turbine of the engine is completed, the given flow channels and blade profiles are the thermal dimensions of the design points, and the parts processed according to the design model are cold models. If the centrifugal impeller compressor or the turbine rotor is directly processed according to a thermal state model, deformation can occur under the working state of the centrifugal impeller compressor or the turbine rotor, particularly the turbine rotor can be obviously deformed under the pneumatic load, the high temperature and the centrifugal load, and the deformation can influence the pneumatic performance of the component and deviate from the performance of the design point.
The conventional cold-hot state conversion method with higher accuracy comprises the following steps:
firstly, taking a temperature field and centrifugal load into consideration, taking the center of gravity of each modeling section of a blade profile as a deformation output point, establishing a Cartesian coordinate system, carrying out coordinate conversion in three directions on each section control point, and then iterating to obtain a cold state model meeting the precision;
the other method with higher precision but larger calculation amount is to consider the pneumatic load, the temperature field and the centrifugal load, project the finite element grid nodes which are arranged in disorder to the modeling section, output the deformation by the projection points, perform three-dimensional interpolation to obtain the deformation of each control point, and then iterate to obtain the cold state model meeting the precision.
The two methods can obtain a cold state model with higher precision. The first conversion method can basically ensure the precision of axial flow blades, but can hardly ensure the precision of centrifugal impellers and centripetal turbine blades; the second method has high precision, but has large calculation amount and time consumption, and is difficult to meet the requirement of quick conversion in engineering practice
In order to achieve both calculation accuracy and calculation speed, a method for rapidly converting the cold state and the hot state of a turbine blade model is provided.
Disclosure of Invention
The invention aims to solve the technical problems of the prior art, and provides a method for rapidly converting the cold state and the hot state of a turbine blade model to solve the problems in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme: a method for rapidly converting cold and hot states of a turbine blade model comprises the following steps:
step 1, on the basis of the existing thermal state blade, carrying out high-precision finite element grid division on the thermal state blade to obtain grid node coordinates S;
step 2, the initial value G of the cold state blade iterative solution 1 Taking S as the raw material;
step 3, iterating solution G on cold state blade 1 Applying conditions such as pneumatic load, temperature field, centrifugal load and the like, and obtaining a thermal state blade iterative solution S through finite element calculation 1 And grid node displacement U 1 ；
Step 4, S is 1 Comparing the coordinates of each node with S, and calculating residual errors E of each node 1 ；
Step 5, if E 1 If the maximum value is greater than 0.01mm, the iteration is not converged, and the displacement U of each node is calculated by S 1 Construction of a new cold blade iteration solution G 2 The construction method comprises the following steps:
G 2 ＝S-U 1 ；
wherein:
G 2 representing a cold state blade iteration solution at the 2 nd iteration;
s represents a thermal state blade;
U 1 representing the grid node displacement at the 1 st iteration;
repeatedly executing the step 3 and the step 4, and performing iterative calculation;
step 6, after the nth iteration, residual error E n When the maximum value is less than or equal to 0.01mm, the iteration is considered to be converged, and the cold state blade iteration solution G in the iteration is considered to be converged n The cold state blade is obtained by converting the hot state blade S under the conditions of aerodynamic load, temperature field and centrifugal load.
Further, in the nth iteration of step 5, the mathematical model for solving the cold state blade iteration solution is as follows:
G n ＝S-U n-1
wherein:
G n representing an iterative solution of the cold state blade at the nth iteration;
s represents a thermal state blade;
U n representing the grid node displacement at the nth iteration;
U n obtained by finite element calculation, residual E n Is defined as
E n ＝S-(G n +U n )
Convergence criteria: and stopping calculation when the maximum residual error is smaller than 0.01 mm.
Further, when the finite element dispersion is performed, the blade at the nth calculation step is dispersed into a dot array
k is the number of nodes after the blades are separated from the network,
S i is the coordinates of the nodes of the thermal state blade,
Further, in the initial calculation, G is taken 1 ＝S。
Compared with the prior art, the invention has the following advantages:
according to the invention, by considering the pneumatic load, the temperature field and the centrifugal load, iterative calculation can be rapidly performed and the maximum residual error and the point coordinate calculated each time can be output; when iterative calculation is repeated, each step of calculation can output a corresponding maximum residual error, so that the convergence result can be intuitively obtained by performing several steps of calculation; after iteration convergence, the model obtained by the calculation is a cold state blade obtained by converting a hot state blade S; the invention accelerates the cold-hot state conversion process of the turbine blade on the premise of ensuring the conversion precision, and effectively improves the working efficiency.
Drawings
FIG. 1 is a flow chart of a method for converting cold and hot states of a turbine blade according to the present invention;
FIG. 2 is a schematic diagram of a finite element computing grid in an embodiment of the invention;
FIG. 3 is a diagram showing a comparison of a cold state model and an original model obtained after a hot state to cold state conversion of a blade according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1-3, the present invention provides a technical solution: a method for rapidly converting cold and hot states of a turbine blade model comprises the following steps:
the mathematical model for solving the geometric position before cold deformation is as follows:
G n ＝S-U n-1
wherein:
G n represents the nth iterationIterative solution of the cold state blade in generation;
s represents a thermal state blade;
U n representing the grid node displacement at the nth iteration;
U n obtained by finite element calculation, residual E n Is defined as
E n ＝S-(G n +U n )
Convergence criteria: and stopping calculation when the maximum residual error is smaller than 0.01 mm.
After finite element dispersion, the blade at the nth step is dispersed into a point array
k is the number of nodes after the blades are separated from the network,
S i is the coordinates of the nodes of the thermal state blade,
In the initial calculation, G is taken 1 ＝S；
Step 1, on the basis of the existing thermal state blade, carrying out high-precision finite element grid division on the thermal state blade to obtain grid node coordinates S;
step 2, the initial value G of the cold state blade iterative solution 1 Taking S as the raw material;
step 3, iterating solution G on cold state blade 1 Applying conditions such as pneumatic load, temperature field, centrifugal load and the like, and obtaining a thermal state blade iterative solution S through finite element calculation 1 And grid node displacement U 1 ；
Step 4, S is 1 Comparing the coordinates of each node with S, and calculating residual errors E of each node 1 ；
Step 5, if E 1 If the maximum value is greater than 0.01mm, the iteration is not converged, and the displacement U is generated through S and each point 1 Construction of a new cold blade iteration solution G 2 The construction method comprises the following steps:
G 2 ＝S-U 1 ；
wherein:
G 2 representing an iterative solution of the cold state blade at the 2 nd iteration;
s represents a thermal state blade;
U 1 representing the grid node displacement at the 1 st iteration;
repeatedly executing the step 3 and the step 4, and performing iterative calculation;
step 6, after the nth iteration, residual error E n When the maximum value is less than or equal to 0.01mm, the iteration is considered to be converged, and the cold state blade iteration solution G in the iteration is considered to be converged n The cold state blade is obtained by converting the hot state blade S under the conditions of aerodynamic load, temperature field and centrifugal load.
FIG. 3 shows a comparison of a cold state model with an original model after a hot state to cold state transition of a blade;
since the deformation of the turbine blade is generally smaller, the deformation is reflected in the figure, namely, the models are mostly overlapped before and after deformation; the non-overlapped part is a larger deformed part, so that the inspection and subsequent study are facilitated.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The method for rapidly converting the cold state and the hot state of the turbine blade model is characterized by comprising the following steps of:
step 1, based on the existing thermal state blade, carrying out high-precision finite element grid division on the thermal state blade;
step 2, acquiring grid node coordinates S;
step 3, the initial value G of the cold state blade iterative solution 1 Taken as S and at G 1 Applying conditions such as pneumatic load, temperature field, centrifugal load and the like, and obtaining a thermal state blade iterative solution S through finite element calculation 1 And grid node displacement U 1 ；
Step 4, S is 1 Comparing the coordinates of each node with S, and calculating residual errors E of each node 1 ；
Step 5, if E 1 The maximum value is greater than 0.01mm, and the displacement U of each point is obtained through S 1 Construction of a New Cold blade G 2 The construction method comprises the following steps:
G 2 ＝S-U 1 ；
wherein:
G 2 representing an iterative solution of the cold state blade at the 2 nd iteration;
s represents a thermal state blade;
U 1 representing the grid node displacement at the 1 st iteration;
repeatedly executing the step 3 and the step 4, and performing iterative calculation;
step 6, after the nth iteration, residual error E n When the maximum value is less than or equal to 0.01mm, the iteration is considered to be converged, and the cold state blade iteration solution G in the iteration is considered to be converged n Namely the thermal state blade S rotates under the conditions of pneumatic load, temperature field and centrifugal loadAnd changing to obtain the cold state blade.
2. The method for rapidly converting cold and hot states of a turbine blade model according to claim 1, wherein in the nth iteration of step 5, a mathematical model for solving an iterative solution of a cold state blade is as follows:
G n ＝S-U n-1
wherein:
G n representing an iterative solution of the cold state blade at the nth iteration;
s represents a thermal state blade;
U n representing the grid node displacement at the nth iteration;
U n obtained by finite element calculation, residual E n Is defined as
E n ＝S-(G n +U n )
Convergence criteria: and stopping calculation when the maximum residual error is smaller than 0.01 mm.
3. The method for rapidly converting cold and hot states of a turbine blade model according to claim 2, wherein the blades at the nth step of calculation are discretized into a point array after the finite element discretization is performed
k is the number of nodes after the blades are separated from the network,
S i is the coordinates of the nodes of the thermal state blade,
4. A method for rapidly converting cold and hot states of a turbine blade model according to claim 3, wherein G is taken during initial calculation 1 ＝S。
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117688698A (en) * | 2024-02-04 | 2024-03-12 | 西安流固动力科技有限公司 | Multi-disciplinary design method and device for turbine blade cooling structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117688698A (en) * | 2024-02-04 | 2024-03-12 | 西安流固动力科技有限公司 | Multi-disciplinary design method and device for turbine blade cooling structure |
| CN117688698B (en) * | 2024-02-04 | 2024-06-07 | 西安流固动力科技有限公司 | Multi-disciplinary design method and device for turbine blade cooling structure |
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