CN117932984A - Rapid analysis method and device for transition state radial deformation of aero-engine wheel disc - Google Patents
Rapid analysis method and device for transition state radial deformation of aero-engine wheel disc Download PDFInfo
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Abstract
The invention relates to the technical field of aero-engines, and discloses a method and a device for rapidly analyzing transition state radial deformation of a wheel disc of an aero-engine, wherein a wheel disc transition state temperature rapid calculation model based on engine performance parameters is established by selecting rotating speed and gas compressor outlet section temperature, and the gas compressor outlet section temperature at the working rotating speed of the engine is obtained through calculation; and finally, respectively obtaining radial deformation of the wheel disc caused by the rotating speed and radial deformation of the wheel disc caused by the temperature through the structural characteristics of the wheel disc, the working rotating speed of the engine and the temperature of the outlet section of the air compressor, and carrying out linear superposition on the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation quantity of the wheel disc. Under the condition that the materials and the structures of the engine wheel disc are determined, the radial deformation of the wheel disc under different engine usage can be rapidly obtained based on the engine performance parameters, the calculation efficiency is high, the precision is high, and the gap optimization design in the full envelope range is convenient to develop.
Description
Technical Field
The invention relates to the technical field of aero-engines, and discloses a method and a device for rapidly analyzing transition state radial deformation of an aero-engine wheel disc.
Background
The blade tip clearance of the aero-engine is closely related to the performance of the engine, the wheel disc is used as a key piece of the aero-engine, and the radial deformation in the working process influences the blade tip clearance of the engine, so that the performance and the working safety of the engine are influenced. The traditional finite element analysis method cannot directly obtain the rule of influence of engine performance parameters on radial deformation of the wheel disc, a large number of transition processes exist in the actual test run process of the engine, time and labor are wasted when the deformation of the wheel disc is calculated by relying on finite elements, and the requirements of rapid evaluation and iterative optimization design of gaps cannot be met.
In the prior art, a multi-parameter fitting method is often adopted to establish the relation between the overall performance parameters and the radial deformation of the wheel disc, but the method excessively depends on the number of samples, the number of samples is enough, the analysis result can be accurate, and the accuracy of the wheel disc deformation calculation beyond the sample usage is greatly reduced.
Disclosure of Invention
The invention aims to provide a rapid analysis method and device for transition state radial deformation of an aeroengine wheel disc, which can rapidly obtain the radial deformation of the wheel disc under different engine usage based on engine performance parameters, has high calculation efficiency and high precision, and is convenient for developing gap optimization design in a full envelope range.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a rapid analysis method for transition state radial deformation of an aeroengine wheel disk comprises the following steps:
According to an engine test run test, acquiring performance data of an engine test run process, wherein the performance data comprises a rotating speed and a temperature of an outlet section of a gas compressor; taking the rotating speed in the test run process as an independent variable, and the corresponding temperature of the outlet section of the air compressor as a dependent variable, and fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed;
Substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the air compressor, analyzing and obtaining temperature values of the wheel disc at all moments, and according to the temperature of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, analyzing and obtaining radial deformation of the wheel disc caused by the temperature;
analyzing and obtaining radial deformation of the wheel disc caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc and the performance parameters of the material of the wheel disc;
and linearly superposing the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation of the wheel disc.
Further, when the function model is fitted, the rotation speed in the test run process and the corresponding temperature of the outlet section of the air compressor are substituted into a fitted functionWherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、/>、/>、/>Fitting coefficients are respectively used.
Further, the method for analyzing and obtaining the radial deformation of the wheel disc caused by the temperature comprises the following steps:
according to the temperature of the outlet section of the gas compressor, adopting a calculation model Temperature values/>, at each moment, of the disk edge and the disk center of the disk are respectively obtainedWherein/>，/>Representing the heart,/>Representing the edges; /(I)Is the temperature of the outlet section of the compressor,/>For/>, at hub or rim relative to the current momentTemperature before time,/>Is the time constant at the rim or center,/>Is a natural constant;
According to the disk edge temperature, the disk core temperature and the disk structure parameters, adopts Obtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
Further, adoptAnalysis to obtain radial deformation/>, caused by rotation speed, of wheel discWherein/>For the density of the wheel disc material,/>Is the elastic modulus of the wheel disc material,/>For engine operating speed/>Corresponding angular velocity.
In order to achieve the technical effects, the invention also provides a rapid analysis device for the transition state radial deformation of the aero-engine wheel disc, which is used for implementing the rapid analysis method for the transition state radial deformation of the aero-engine wheel disc, and comprises the following steps:
The data fitting module is used for fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed by taking the rotating speed in the test run process as an independent variable and the temperature of the outlet section of the corresponding air compressor as a dependent variable according to the performance data of the test run process of the engine;
The first analysis module is used for substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the air compressor, analyzing and obtaining temperature values of the wheel disc at all moments, and according to the temperature of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, analyzing and obtaining radial deformation of the wheel disc caused by the temperature;
The second analysis module is used for analyzing and obtaining radial deformation of the wheel disc caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc and the performance parameters of the wheel disc materials;
And an output module. The method is used for linearly superposing the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation of the wheel disc.
Further, when the function model is fitted in the data fitting module, the rotation speed and the corresponding temperature of the outlet section of the air compressor in the test run process are substituted into a fitting functionWherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、/>、、/>Fitting coefficients are respectively used.
Further, the first analysis module adopts a calculation model according to the temperature of the outlet section of the compressorTemperature values/>, at each moment, of the disk edge and the disk center of the disk are respectively obtainedWherein/>，Representing the heart,/>Representing the edges; /(I)Is the temperature of the outlet section of the compressor,/>For/>, at hub or rim relative to the current momentTemperature before time,/>Is the time constant at the rim or center,/>Is a natural constant;
According to the disk edge temperature, the disk core temperature and the disk structure parameters, adopts Obtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
Further, the second analysis module adoptsAnalysis to obtain radial deformation/>, caused by rotation speed, of wheel discWherein/>For the density of the wheel disc material,/>Is the elastic modulus of the wheel disc material,/>For engine operating speed/>Corresponding angular velocity,/>Is the radial dimension of the center of the wheel disc,/>Is the radial dimension of the rim of the wheel disc.
Compared with the prior art, the invention has the following beneficial effects: according to the invention, a rapid calculation model of the transition state temperature of the wheel disc based on the engine performance parameters is established by selecting the rotating speed and the temperature of the outlet section of the air compressor, and the temperature of the outlet section of the air compressor under the working rotating speed of the engine is obtained through calculation; and finally, respectively obtaining radial deformation of the wheel disc caused by the rotating speed and radial deformation of the wheel disc caused by the temperature through the structural characteristics of the wheel disc, the working rotating speed of the engine and the temperature of the outlet section of the air compressor, and carrying out linear superposition on the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation quantity of the wheel disc. The method can rapidly obtain radial deformation of the wheel disc under different engine usage based on the engine performance parameters under the condition that the materials and the structure of the wheel disc of the engine are determined, has high calculation efficiency and high precision, and is convenient for developing gap optimization design within the full envelope.
Drawings
FIG. 1 is a flow chart of a method for rapid analysis of transition state radial deformation of an aircraft engine disk in examples 1 or 2;
FIG. 2 is a block diagram of a device for rapidly analyzing transition state radial deformation of an aero-engine disk in example 1;
FIG. 3 is a schematic view showing the structural dimensions of the rim and the hub of the wheel disc of embodiment 1 or 2;
1, a wheel disc; 2. a data fitting module; 3. a first analysis module; 4. a second analysis module; 5. and an output module.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1-3, a method for rapidly analyzing transition state radial deformation of an aeroengine wheel disc comprises the following steps:
According to an engine test run test, acquiring performance data of an engine test run process, wherein the performance data comprises a rotating speed and a temperature of an outlet section of a gas compressor; taking the rotating speed in the test run process as an independent variable, and the corresponding temperature of the outlet section of the air compressor as a dependent variable, and fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed;
Substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the gas compressor, analyzing and obtaining temperature values of the wheel disc 1 at all times, and according to the temperature of the wheel disc 1, the material performance of the wheel disc 1 and the structural parameters of the wheel disc 1, analyzing and obtaining radial deformation of the wheel disc 1 caused by the temperature;
And linearly superposing the radial deformation of the wheel disc 1 caused by the rotating speed and the radial deformation of the wheel disc 1 caused by the temperature to obtain the transitional radial deformation of the wheel disc 1.
In the embodiment, through screening engine performance parameters, selecting the rotating speed affecting radial deformation of the wheel disc 1 and the temperature of the outlet section of the air compressor in the engine performance parameters, then establishing a wheel disc 1 transition state temperature rapid calculation model based on the engine performance parameters by combining with the thermal response rule of the wheel disc 1 in a transition state, and calculating the temperature of the outlet section of the air compressor under the working rotating speed of the engine through the wheel disc 1 transition state temperature rapid calculation model; and finally, respectively obtaining radial deformation of the wheel disc 1 caused by the rotating speed and radial deformation of the wheel disc 1 caused by the temperature through the structural characteristics of the wheel disc 1, the working rotating speed of the engine and the temperature of an outlet section of the air compressor, and linearly superposing the radial deformation of the wheel disc 1 caused by the rotating speed and the radial deformation of the wheel disc 1 caused by the temperature to obtain the transition state radial deformation of the wheel disc 1. According to the invention, under the condition that the materials and the structures of the engine wheel disc 1 are determined, the radial deformation of the wheel disc 1 under different engine usage can be rapidly obtained based on the engine performance parameters, the calculation efficiency is high, the calculation precision is high, and the gap optimization design in the full envelope range is convenient to develop.
Based on the same inventive concept, the embodiment also provides a rapid analysis device for transition state radial deformation of an aero-engine wheel disc, which is used for implementing the rapid analysis method for transition state radial deformation of the aero-engine wheel disc 1, and comprises the following steps:
the data fitting module 2 is used for fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed by taking the rotating speed in the test run process as an independent variable and the temperature of the outlet section of the corresponding air compressor as a dependent variable according to the performance data of the test run process of the engine;
the first analysis module 3 is used for substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the gas compressor, analyzing and obtaining temperature values of the wheel disc 1 at all times, and according to the temperature of the wheel disc 1, the material performance of the wheel disc 1 and the structural parameters of the wheel disc 1, analyzing and obtaining radial deformation of the wheel disc 1 caused by the temperature;
The second analysis module 4 is used for analyzing and obtaining radial deformation of the wheel disc 1 caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc 1 and the material performance parameters of the wheel disc 1;
And an output module 5. The method is used for linearly superposing radial deformation of the wheel disc 1 caused by rotating speed and radial deformation of the wheel disc 1 caused by temperature to obtain transition state radial deformation of the wheel disc 1.
In this embodiment, when the data fitting module 2 performs the function model fitting, the rotation speed and the corresponding compressor outlet section temperature in the test run process are substituted into the fitting functionWherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、、/>、/>Fitting coefficients are respectively used.
The first analysis module 3 adopts a calculation model according to the temperature of the outlet section of the compressorTemperature values/>, at each moment, of the edge and the center of the wheel disc 1 are obtained respectivelyWherein/>，Representing the heart,/>Representing the edges; /(I)Is the temperature of the outlet section of the compressor,/>For/>, at hub or rim relative to the current momentTemperature before time,/>Is a time constant,/>Is a natural constant;
According to the temperature of the rim of the wheel disc 1, the temperature of the center of the wheel disc and the structural parameters of the wheel disc 1, adopts Obtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
The second analysis module 4 adoptsAnalysis to obtain radial deformation/>, caused by rotational speed, of wheel disc 1Wherein/>For the material density of the wheel disc 1,/>Is the elastic modulus of the material of the wheel disc 1,/>For engine operating speed/>Corresponding angular velocity.
Example 2
Referring to fig. 1 and 3, in this embodiment, an analysis method of transition state radial deformation of a certain aero-engine wheel disc is taken as an example, and the method specifically includes the following steps:
Step 1, according to an engine test run test, acquiring performance data of an engine test run process, wherein the performance data comprises a rotating speed and a temperature of an outlet section of a gas compressor; taking the rotating speed in the test run process as an independent variable, and the corresponding temperature of the outlet section of the air compressor as a dependent variable, and fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed;
in this embodiment, when the function model is fitted, the rotation speed and the corresponding compressor outlet section temperature in the test run course are substituted into the fitted function Wherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、/>、/>、/>Fitting coefficients are respectively used.
Step 2, substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the gas compressor, analyzing and obtaining temperature values of the wheel disc 1 at all times, and according to the temperature of the wheel disc 1, the material performance of the wheel disc 1 and the structural parameters of the wheel disc 1, analyzing and obtaining radial deformation of the wheel disc 1 caused by the temperature;
In this embodiment, a calculation model is first used according to the temperature of the outlet section of the compressor Temperature values/>, at each moment, of the edge and the center of the wheel disc 1 are obtained respectivelyWherein/>，/>Representing the heart,/>Representing the edges; /(I)Is the temperature of the outlet section of the compressor,/>For/>, at hub or rim relative to the current momentTemperature before time,/>Is a natural constant; /(I)Is the time constant at the rim or center,/>，/>For radial dimension of rim or hub,/>Is the thickness of the disk edge or the disk center (i.e./>For the thickness of the disk center,/>Thickness of rim)/>For/>Engine speed variation before and after a time period,/>For/>Temperature variation of outlet section of compressor before and after time period,/>To take the following measuresTime constant expression as independent variable, in case of material and structure determination of wheel disc 1,/>Fitting according to finite element analysis.
According to the temperature of the rim of the wheel disc 1, the temperature of the center of the wheel disc and the structural parameters of the wheel disc 1, adoptsObtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
Step 3, analyzing and obtaining radial deformation of the wheel disc 1 caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc 1 and the material performance parameters of the wheel disc 1;
In the present embodiment, use is made of Analysis to obtain radial deformation/>, caused by rotational speed, of wheel disc 1Wherein/>For the material density of the wheel disc 1,/>Is the elastic modulus of the material of the wheel disc 1,/>For engine operating speed/>Corresponding angular velocity.
Step 4, linearly superposing radial deformation of the wheel disc 1 caused by the rotating speed and radial deformation of the wheel disc 1 caused by the temperature to obtain the transitional radial deformation of the wheel disc 1。
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (8)
1. The rapid analysis method for the transition state radial deformation of the aeroengine wheel disc is characterized by comprising the following steps of:
According to an engine test run test, acquiring performance data of an engine test run process, wherein the performance data comprises a rotating speed and a temperature of an outlet section of a gas compressor; taking the rotating speed in the test run process as an independent variable, and the corresponding temperature of the outlet section of the air compressor as a dependent variable, and fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed;
Substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the air compressor, analyzing and obtaining temperature values of the wheel disc at all moments, and according to the temperature of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, analyzing and obtaining radial deformation of the wheel disc caused by the temperature;
analyzing and obtaining radial deformation of the wheel disc caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc and the performance parameters of the material of the wheel disc;
and linearly superposing the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation of the wheel disc.
2. The rapid analysis method for transition state radial deformation of aeroengine disk according to claim 1, wherein the function model fitting is performed by substituting the rotational speed in the test run course and the corresponding compressor outlet section temperature into a fitting functionWherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、/>、/>、/>Fitting coefficients are respectively used.
3. The rapid analysis method for transition state radial deformation of an aircraft engine disk according to claim 1, wherein the method for analyzing and obtaining the temperature-induced radial deformation of the disk comprises:
according to the temperature of the outlet section of the gas compressor, adopting a calculation model Temperature values/>, at each moment, of the disk edge and the disk center of the disk are respectively obtainedWherein/>，/>Representing the heart,/>Representing the edges; /(I)Is the temperature of the outlet section of the compressor,/>For/>, at hub or rim relative to the current momentTemperature before time,/>Is the time constant at the rim or center,/>Is a natural constant;
According to the disk edge temperature, the disk core temperature and the disk structure parameters, adopts Obtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
4. A method for rapid analysis of transition state radial deformation of an aeroengine disk according to claim 3, wherein the method comprises the steps ofAnalysis to obtain radial deformation/>, caused by rotation speed, of wheel discWherein/>For the density of the wheel disc material,/>Is the elastic modulus of the wheel disc material,/>For engine operating speed/>Corresponding angular velocity.
5. An aeroengine wheel disc transition state radial deformation rapid analysis device for implementing the aeroengine wheel disc transition state radial deformation rapid analysis method according to claim 1, comprising:
The data fitting module is used for fitting to obtain a function model between the temperature of the outlet section of the air compressor and the rotating speed by taking the rotating speed in the test run process as an independent variable and the temperature of the outlet section of the corresponding air compressor as a dependent variable according to the performance data of the test run process of the engine;
The first analysis module is used for substituting the working rotation speed of the working state of the aero-engine into the function model to obtain the temperature of the outlet section of the air compressor; according to the temperature of the outlet section of the air compressor, analyzing and obtaining temperature values of the wheel disc at all moments, and according to the temperature of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, analyzing and obtaining radial deformation of the wheel disc caused by the temperature;
The second analysis module is used for analyzing and obtaining radial deformation of the wheel disc caused by the rotating speed according to the working rotating speed of the engine, the structural parameters of the wheel disc and the performance parameters of the wheel disc materials;
and the output module is used for linearly superposing the radial deformation of the wheel disc caused by the rotating speed and the radial deformation of the wheel disc caused by the temperature to obtain the transition state radial deformation quantity of the wheel disc.
6. The rapid analysis device for transition state radial deformation of an aeroengine disk according to claim 5, wherein when the function model fitting is performed in the data fitting module, the rotation speed in the test run course and the corresponding compressor outlet section temperature are substituted into a fitting functionWherein/>Is the temperature of the outlet section of the compressor,/>For engine operating speed,/>Engine speed for slow engine state,/>、/>、/>、/>、/>Fitting coefficients are respectively used.
7. The rapid analysis device for transition state radial deformation of an aeroengine disk according to claim 5, wherein the first analysis module adopts a calculation model according to the temperature of the outlet section of the compressorTemperature values/>, at each moment, of the disk edge and the disk center of the disk are respectively obtainedWherein/>，/>Representing the heart,/>Representing the edges; Is the temperature of the outlet section of the compressor,/> For/>, at hub or rim relative to the current momentTemperature before time,/>Is the time constant at the rim or center,/>Is a natural constant;
According to the disk edge temperature, the disk core temperature and the disk structure parameters, adopts Obtaining the rim radius/>Wherein/>For the radius/>Temperature at/(I)Is the temperature of the center of the wheel disc,/>For the rim temperature of the wheel disc,/>Is the radial dimension of the center of the wheel disc,/>The radial dimension of the rim of the wheel disc;
According to the temperature distribution of the wheel disc, the material performance of the wheel disc and the structural parameters of the wheel disc, adopts Integral acquisition of temperature induced radial deformation of disk/>Wherein/>Is the linear expansion coefficient of the wheel disc material,/>Poisson ratio of wheel material,/>Is a differential sign.
8. The rapid analysis device for transition state radial deformation of an aircraft engine disk according to claim 5, wherein the second analysis module adoptsAnalysis to obtain radial deformation/>, caused by rotation speed, of wheel discWhereinFor the density of the wheel disc material,/>Is the elastic modulus of the wheel disc material,/>For engine operating speed/>Corresponding angular velocity.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101718227A (en) * | 2009-11-01 | 2010-06-02 | 韩凤琳 | Heat flow turbine |
| DE102014008556A1 (en) * | 2014-06-09 | 2015-12-17 | Manfred Stute | Turbo air-conditioning |
| CN109342053A (en) * | 2018-11-16 | 2019-02-15 | 东北大学 | Dish axle coupled rotor system thermal analysis test platform and its measurement method of thermal deformation |
| WO2020000248A1 (en) * | 2018-06-27 | 2020-01-02 | 大连理工大学 | Space reconstruction based method for predicting key performance parameters of transition state acceleration process of aircraft engine |
| CN113188781A (en) * | 2021-04-25 | 2021-07-30 | 中国航发湖南动力机械研究所 | Method for correcting rotor temperature field in fatigue test of blade of aircraft engine |
| CN116542114A (en) * | 2023-07-04 | 2023-08-04 | 中国航发四川燃气涡轮研究院 | Method and device for analyzing temperature stress deformation of compressor rotor based on overall parameters |
-
2024
- 2024-03-25 CN CN202410338716.6A patent/CN117932984B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101718227A (en) * | 2009-11-01 | 2010-06-02 | 韩凤琳 | Heat flow turbine |
| DE102014008556A1 (en) * | 2014-06-09 | 2015-12-17 | Manfred Stute | Turbo air-conditioning |
| WO2020000248A1 (en) * | 2018-06-27 | 2020-01-02 | 大连理工大学 | Space reconstruction based method for predicting key performance parameters of transition state acceleration process of aircraft engine |
| CN109342053A (en) * | 2018-11-16 | 2019-02-15 | 东北大学 | Dish axle coupled rotor system thermal analysis test platform and its measurement method of thermal deformation |
| CN113188781A (en) * | 2021-04-25 | 2021-07-30 | 中国航发湖南动力机械研究所 | Method for correcting rotor temperature field in fatigue test of blade of aircraft engine |
| CN116542114A (en) * | 2023-07-04 | 2023-08-04 | 中国航发四川燃气涡轮研究院 | Method and device for analyzing temperature stress deformation of compressor rotor based on overall parameters |
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