CN114139298B - Multi-disciplinary coupling analysis method for gas, heat and solid - Google Patents
Multi-disciplinary coupling analysis method for gas, heat and solid Download PDFInfo
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- CN114139298B CN114139298B CN202111223598.7A CN202111223598A CN114139298B CN 114139298 B CN114139298 B CN 114139298B CN 202111223598 A CN202111223598 A CN 202111223598A CN 114139298 B CN114139298 B CN 114139298B
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Abstract
The invention discloses a multi-disciplinary coupling analysis method for gas, heat and solid, belongs to the technical field of turbine blade service life calculation methods, and solves the technical problem that the method in the prior art does not comprehensively consider gas, heat and solid and only singly considers the gas, heat and solid. S101, generating a model of the turbine blade based on CAM software according to preset geometric shapes and cooling structure parameters of the turbine blade; s102, acquiring the aerodynamic boundary of the turbine blade and determining the actual temperature and/or pressure of each point of the blade; s103, determining the static strength of all points of the blade according to the actual temperature and pressure boundaries of all points; s104, determining the actual service life of the blade according to the static intensity distribution of all points. The method of the invention comprehensively considers and evaluates the service life of the blade.
Description
Technical Field
The invention belongs to the technical field of turbine blade life calculation methods, and particularly relates to a method for multi-disciplinary coupling analysis of gas, heat and solid.
Background
The turbine is used as a hot end component of the aeroengine, has the characteristics of high inlet flow temperature, high pressure, severe and complex working environment and the like, and is a subject of deep cross fusion of multiple subjects of high-integration pneumatic, heat transfer and strength. Based on the traditional engineering evaluation analysis method of the turbine component at present: the decoupling design method of pneumatic design, cooling design, structure and strength design mutually independent and cyclic iteration is characterized in that one-dimensional, two-dimensional and three-dimensional design stages exist in the design iteration process among various disciplines and professions, so that the data transmission dimension and precision among various disciplines in the whole turbine component design period can not be ensured, and the inherent limitation of the traditional design evaluation method of the turbine is brought:
1) The iteration efficiency of the design between professions is low;
2) The dimension and the precision of data transmission between disciplines are low;
3) The estimated deviation of the service life of the turbine blade is large.
Therefore, the traditional turbine component design evaluation analysis method cannot meet the design requirements of high efficiency, high precision, long service life, low stress and multiple physical fields of the turbine blade.
In view of this, the present invention has been made.
Disclosure of Invention
The invention aims to provide a multi-disciplinary coupling analysis method for gas, heat and solid, which solves the technical problem that the method in the prior art lacks comprehensive consideration of gas, heat and solid and only singly considers. The technical scheme of the scheme has a plurality of technical advantages, and the following description is provided:
a method of multi-disciplinary coupling analysis of gas, heat and solids is provided for use in the assessment of aircraft engine turbine blade life, the method comprising:
s101, generating a model of the turbine blade based on CAM software according to preset geometric shapes and cooling structure parameters of the turbine blade;
s102, acquiring the aerodynamic boundary of the turbine blade and determining the actual temperature and/or pressure of each point of the blade;
s103, determining static strength of all points of the blade according to the actual temperature and the actual pressure of all points;
s104, determining the actual service life of the blade according to the static strength of all points.
The method is an analysis method which is put forward for the first time in China under the condition of considering multi-disciplinary coupling of the blades, considers that each point of the blades is influenced by gas temperature or pressure, and the solid strength, couples the parameters, and finally determines the actual service life of the blades, so that the problem of multi-physical field coupling of gas, heat, solid and the like of the turbine blades is truly solved, high-dimensional and high-precision data transmission among disciplines is realized, the design iteration period of the turbine blades is greatly reduced, and the design precision is improved.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
the method is firstly put forward in China under the condition of considering multi-disciplinary coupling of the blades, considers that each point of the blade is influenced by gas temperature or pressure, and the solid strength, couples the parameters, and finally determines the actual service life of the blade, so that the problem of multi-physical field coupling of gas, heat, solid and the like of the turbine blade is truly solved, high-dimensional and high-precision data transmission among disciplines is realized, the design iteration period of the turbine blade is greatly reduced, and the design precision is improved.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from them without inventive effort for a person skilled in the art.
FIG. 1 is a general flow chart of the present invention;
Detailed Description
Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. 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.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order to better understand the aspects of the present invention, the present invention will be described in further detail with reference to the accompanying drawings and detailed description. The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The method of gas, heat and solid multidisciplinary coupling analysis of fig. 1, suitable for use in the assessment of aircraft engine turbine blade life, comprises:
s101, generating a model of the turbine blade based on CAM software according to preset geometric shapes and cooling structure parameters of the turbine blade;
s102, acquiring the aerodynamic boundary of the turbine blade and determining the actual temperature and/or pressure of each point of the blade, wherein the method comprises the following steps:
and obtaining physical parameters of fuel gas in the turbine and the heat conductivity coefficient of the turbine blade material. Physical parameters of the fuel gas, such as gas density, isobaric specific heat capacity, gas constant, and the like. Based on the gas physical parameters and the thermal conductivity of the blade material, the actual temperature and pressure of each point of the turbine blade are determined by combining the aerodynamic boundaries of the turbine blade through a finite volume and finite element analysis method.
S103, determining static strength of all points of the blade according to actual temperature and pressure of all points, and specifically:
and (3) carrying out region division on all points through a temperature field, judging whether the temperature point of each region exceeds a preset value, wherein the preset value is the allowable temperature of the material for a long time, if so, optimizing the preset geometric shape and cooling structure parameters of the turbine blade until the preset value is met, namely, the temperature reaches the standard, if not, determining the boundary conditions of the actual temperature and the actual pressure of each point of the turbine blade for the static strength of the turbine blade, wherein the boundary conditions are the boundary conditions of the temperature and the actual pressure, namely, the change rule of the variable or the derivative thereof solved on the boundary of the solving region along with time and places is a range value. For example, aerodynamic loads on the surface of the turbine blade, preset installation mode constraint parameters of the blade and material properties of the blade, such as material durability, are obtained, and the static strength of each point of the turbine blade is determined by a finite element analysis method in combination with the actual temperature of each point.
S104, determining the actual service life of the blade according to the distribution of the static intensity of all points, and specifically:
it is determined whether the static strength exceeds a preset permanent strength, such as a stress requirement. If so, optimizing the preset geometric shape and cooling structure parameters of the turbine blade until each point meets the preset lasting strength, namely, the static strength reaches the standard, if not, determining the actual service life of the blade, if so, acquiring the preset installation mode constraint parameters of the blade, and determining the vibration and modal parameters of the blade by combining the static strength of each point through a finite element analysis method so as to determine the actual service life of the blade.
Further, the method for determining the actual service life of the blade comprises the following steps:
judging whether the actual service life of the blade exceeds a preset service life value, designing the turbine according to a specification, wherein turbines of different models and sizes have a standard range, if so, optimizing the preset geometric shape and cooling structure parameters of the turbine blade until the preset service life value is met, and if not, using the turbine blade as the actual parameters of the blade.
The method is an analysis method which is put forward for the first time in China under the condition of considering multi-disciplinary coupling of the blades, considers that each point of the blade is influenced by gas temperature or pressure, and the solid strength, couples the parameters, and finally determines the actual service life of the blade, so that the problem of multi-physical field coupling of gas, heat, solid and the like of the turbine blade is truly solved, high-dimensional and high-precision data transmission among disciplines is realized, the design iteration period of the turbine blade is greatly reduced, and the design precision is improved.
And through setting up turbine blade gas heat set multidisciplinary coupling analysis flow, realized turbine blade aerodynamic performance, temperature field, thermal stress and life-span rapid evaluation, the data between the different departments can realize automatic transmission at the flow frame bottom simultaneously, has solved turbine blade gas, heat, solid etc. multidisciplinary physical field coupling problem in the true sense, realizes data high dimension, high accuracy transmission between the disciplinary, greatly reduces turbine blade design iteration cycle, promotes the design precision.
Design principle:
principle of operation
1. The method has the main principle that the flow solidification of the turbine blade in each design evaluation stage can be realized under the existing ANSYS WORKBENCH platform. The blade aerodynamic load, the blade flow field and the blade grid performance can be evaluated in the turbine blade aerodynamic evaluation analysis stage;
in the stage of turbine blade heat transfer evaluation analysis, aerodynamic parameter design boundaries can be automatically obtained and blade temperature field evaluation analysis can be carried out;
in the turbine blade static strength evaluation stage, the static strength calculation boundary condition is automatically loaded according to the pneumatic load boundary and the temperature field boundary obtained through gas-heat coupling calculation, so that the blade surface static strength evaluation analysis is realized;
in the stage of turbine blade mode evaluation analysis, load data and constraint boundaries from upstream static strength calculation can be automatically inherited, static frequency and dynamic frequency calculation of the blade is realized, and finally the service life of the turbine blade is evaluated through the obtained blade surface stress distribution and blade deformation.
2. Analytical method flow
A gas-heat-set multidisciplinary coupling analysis method for turbine blades of an aeroengine is shown in fig. 1, and comprises the following steps:
2.1 turbine blade geometry model processing and meshing
After the turbine blade completes the early pneumatic structure design, carrying out the turbine blade geometric model processing based on the real geometry, reducing the real geometry to the greatest extent while simplifying the geometric model, and improving the simulation evaluation precision; and then, carrying out grid division based on the simplified geometric model, and providing initial geometric and grid input for a turbine blade gas-heat-set multidisciplinary coupling analysis platform.
2.2 turbine blade gas-thermal coupling calculation
After the division of the turbine blade grids is completed, the pneumatic load and the blade temperature field evaluation of the turbine blade are realized under a CFX gas thermal coupling module under an ANSYS WORKBENCH platform
2.3 turbine blade static Strength calculation
Taking a turbine blade pneumatic load boundary and a temperature field boundary obtained under the CFX gas thermal coupling module as a static strength calculation module input boundary, automatically realizing turbine blade load boundary loading, realizing turbine blade static strength evaluation, and obtaining blade surface stress distribution and blade deformation
2.4 turbine blade static and dynamic frequency calculation
The blade surface pneumatic load distribution and the solid surface temperature field which are obtained under the CFX gas thermal coupling module are used as the input boundary of the blade static frequency and dynamic frequency calculation module, so that the turbine blade static frequency and dynamic frequency calculation is realized, the blade campbell diagram can be obtained, and the turbine blade vibration analysis is realized.
2.5 turbine blade Life assessment
And the service life of the blade can be evaluated according to the material parameters of the turbine blade by a static strength calculation module and a result obtained by blade vibration analysis.
2.6 determining whether the turbine blade temperature field, stress distribution, and lifetime meet the requirements
Judging and analyzing whether the temperature field, the stress distribution and the service life of the turbine blade meet the requirements according to the turbine blade gas heat-setting multidisciplinary coupling evaluation result, if abnormal problems such as local overtemperature, local overstress, short service life and the like of the turbine blade exist, feeding back in time, optimizing a blade geometric model, iterating again, and finally obtaining the turbine blade design result meeting the index requirements of all aspects of the turbine blade.
The product provided by the invention is described in detail above. The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the core concepts of the invention. It should be noted that it will be apparent to those skilled in the art that several improvements and modifications can be made to the invention without departing from the inventive concept, and these improvements and modifications fall within the scope of the appended claims.
Claims (2)
1. A method of multi-disciplinary coupling analysis of gas, heat and solids for use in the assessment of aircraft engine turbine blade life, the method comprising:
s101, generating a model of the turbine blade based on CAM software according to preset geometric shapes and cooling structure parameters of the turbine blade;
s102, acquiring the aerodynamic boundaries of the turbine blade and determining the actual temperature and/or pressure of each point of the blade, wherein the method comprises the following steps:
acquiring physical parameters of fuel gas in a turbine and a heat conductivity coefficient of a turbine blade material; determining the actual temperature and pressure of each point of the turbine blade by combining the gas physical parameters and the heat conductivity coefficient of the gas in the turbine through a finite volume and finite element analysis method and combining the pneumatic boundary of the turbine blade, wherein all points are divided into areas through a temperature field, judging whether the temperature point of each area exceeds a preset value, if so, optimizing the preset geometric shape and the cooling structure parameters of the turbine blade until the preset value is met, and if not, determining the static strength of the turbine blade by using the boundary conditions of the actual temperature and the pressure of each point of the turbine blade;
s103, determining the static intensity of all points of the blade according to the actual temperature and the actual pressure of all points, wherein the method for determining the static intensity of each point comprises the following steps: acquiring aerodynamic load on the surface of a turbine blade, constraint parameters of a preset mounting mode of the blade and material properties of the blade, determining static strength of each point by combining the actual temperature of each point of the turbine blade through a finite element analysis method, judging whether the static strength exceeds preset lasting strength, if so, optimizing preset geometric shape and cooling structure parameters of the turbine blade until each point meets the preset lasting strength, and if not, determining the actual service life of the blade;
s104, determining the actual service life of the blade according to the static strength of all points, wherein the method comprises the following steps: and acquiring preset installation mode constraint parameters of the blade, and determining vibration and modal parameters of the blade by combining the static strength of each point through a finite element analysis method so as to determine the actual service life of the blade.
2. The method of claim 1, wherein determining the actual life of the blade comprises:
judging whether the actual service life of the blade exceeds a preset service life value, if so, optimizing the preset geometric shape and cooling structure parameters of the turbine blade, and if not, using the optimized geometric shape and cooling structure parameters as the actual parameters of the blade.
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| CN112507586A (en) * | 2020-12-02 | 2021-03-16 | 中国航发沈阳发动机研究所 | Rapid assessment method for two-dimensional temperature and strength of turbine air cooling blade |
| CN112380794A (en) * | 2020-12-08 | 2021-02-19 | 中北大学 | Multi-disciplinary parallel cooperation optimization design method for aviation turbine engine blade |
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