CN114840931A - Method for designing blade body strength simulation test piece of turbine blade of aero-engine - Google Patents
Method for designing blade body strength simulation test piece of turbine blade of aero-engine Download PDFInfo
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- CN114840931A CN114840931A CN202210541982.XA CN202210541982A CN114840931A CN 114840931 A CN114840931 A CN 114840931A CN 202210541982 A CN202210541982 A CN 202210541982A CN 114840931 A CN114840931 A CN 114840931A
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Abstract
The application provides a method for designing a strength simulation test piece of a turbine blade body of an aero-engine, which comprises the following steps: determining data such as a geometric model of a target turbine blade to be simulated and a calculation state for strength analysis; based on data such as a geometric model and a state, strength and service life analysis of the turbine blade is carried out through finite element software, and a key concerned part and a key concerned section are selected according to the strength and service life analysis results; based on the selected concerned section, extending along the normal direction perpendicular to the section to form a blade body examination section; the inner cavity channel of the blade body examination section comprises a scheme with rib plates and a scheme without rib plates; forming a scheme comprising thickening and thinning on the basis of the original wall thickness; designing a loading shroud for mechanical load loading; designing a connecting structure of a blade body examination section and a loading blade shroud; and carrying out process feasibility analysis and strength analysis on the designed test piece, and judging whether the examination is effective or not, wherein the connection structure and the blade shroud meet the test loading requirement or not.
Description
Technical Field
The application belongs to the field of strength design of aero-engines, and particularly relates to a method for designing a strength simulation test piece of a turbine blade body of an aero-engine.
Background
The turbine blade is one of the most critical parts of the aircraft engine, the life simulation test of the turbine blade carried out in a laboratory environment is a key step for realizing forward design verification of the turbine blade from materials to components and to a complete machine, and compared with complete machine test run, the simulation test has the advantages of low test cost and strong researchability, and the research result has important significance for forward design and life evaluation prediction of the turbine blade.
In order to meet the use requirements of the turbine under the harsh working condition environment, the turbine blade usually has a complex space curved surface structure and a complex service working condition, and the problems of stress field simulation, temperature field simulation and the like need to be solved when a real blade service life simulation test is carried out in a laboratory environment.
In the prior art, the blade is loaded by welding or casting the blade shroud, so that the joint of the additional blade shroud and the blade can become a weak part, and the weak part is easy to damage in advance in the test process; for a blade structure with obvious bending and twisting and other design characteristics, the loading process inevitably leads to the complexity of the load transmission process on the blade-shaped section, and the stress and temperature distribution of the test section are difficult to meet the expectation; because a plurality of influencing factors such as the structural characteristics of the test piece, the test process and the like are not clear, the current test result cannot be clearly concluded.
Disclosure of Invention
The application aims to provide a method for designing a strength simulation test piece of a turbine blade body of an aircraft engine, so as to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: a method for designing a strength simulation test piece of a turbine blade body of an aircraft engine comprises the following steps:
Based on the data such as the geometric model and the state in the step 1, carrying out strength and service life analysis on the turbine blade through finite element software, and combining the strength and service life analysis results to select a key part of interest;
Selecting a key concerned section in the design of the strength life of the turbine blade by combining the strength analysis result of the turbine blade;
Based on the selected concerned section, extending along the normal direction perpendicular to the section to form a blade body examination section;
the inner cavity channel of the blade body examination section comprises a scheme with rib plates and a scheme without rib plates;
the wall thickness of the blade body examination section is analyzed according to the simulation out-of-tolerance influence, and a scheme comprising thickening and thinning is formed on the basis of the original wall thickness;
After the structural design of the blade body examination section is finished, designing a loading blade crown for mechanical load loading;
The connecting structure ensures that the blade body examination section and the loading blade shroud are connected and have enough strength, so that the test process is not damaged;
step 7, analyzing process feasibility
Carrying out process feasibility analysis on the test pieces designed in the steps 4-6, and properly relaxing the casting quality of the tip shroud on the premise of ensuring the casting quality of the assessment section;
And (4) carrying out strength analysis on the test piece designed in the step (4) to the step (6), and judging whether the examination is effective or not, and whether the connection structure and the blade shroud meet the test loading requirement or not.
Further, the finite element analysis software includes ANSYS and Abaqus.
Further, the sections of interest include a root section and a leaf section.
Further, the extension length of the blade body examination section in the normal direction meets the following conditions: the test fixture is not loaded in the high-temperature area range of the temperature field, the low-temperature area meets the requirement of effective assembly of the test fixture, and the process is feasible.
Further, the loaded tip shroud satisfies the following condition:
the section centroids of the loaded blade crown and the blade body examination section are the same;
the size of the loaded blade shroud meets the strength requirement and the process feasibility requirement;
the loading blade crown is provided with a gas collecting box mounting surface which is used for being connected with the gas collecting box and the ventilating joint, cooling gas inflow and outflow are achieved, the test fixture mounting surface is assembled with the test fixture and transmits load, the test fixture positioning surface is used for achieving axial and circumferential effective positioning of a test piece and the test fixture, and stability of the test piece in the loading process is guaranteed.
Compared with the prior art, the method solves the problem that the turbine blade structure simulation test is difficult to load, realizes effective loading of mechanical load, and ensures that the connecting part has enough strength in the test process; the problem of temperature and stress distribution change in the loading process caused by the bending and twisting characteristics of the blade structure is solved, and the temperature and stress in the test process are effectively monitored; the scheme of the test piece is optimized, the structural characteristics of the test piece and multiple uncertain factors in the test process are eliminated, and an effective test result is obtained.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a flow chart of a test piece design method of the present application.
FIG. 2 is a front view of a turbine blade airfoil strength simulation test piece of the present application.
FIG. 3 is a perspective view of a turbine blade body strength simulation test piece of the present application.
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 order to solve the problems of difficulty in mechanical load loading, high difficulty in stress and temperature control in the test process, poor data validity and the like in the turbine blade simulation test in the prior art scheme, the test piece design of the turbine blade body strength simulation test is provided, and the test piece design method can realize tensile, lasting, fatigue and other simulation tests, so that effective performance data of the key section of the blade body is obtained, and technical support is provided for the establishment of the turbine blade strength and service life design and the test verification method.
In order to obtain the test piece and enable the strength examination and the real mechanical property of the key section of the turbine blade to be compared and researched, the design method of the aero-engine turbine blade body strength simulation test piece provided by the application comprises the following steps:
Based on the data of the geometric model, the state and the like in the step 1, carrying out strength and service life analysis on the turbine blade by using finite element software such as ANSYS, Abaqus and the like, combining the strength and service life analysis results, and selecting a key part of interest as a reference for selecting a subsequent section;
And selecting a key concerned section in the design of the strength life of the turbine blade by combining the analysis result of the strength of the turbine blade, wherein the interface mainly comprises a blade root section, a blade leaf section and the like.
And (4) extending the concerned section (or called an assessment section) selected based on the third step along the normal direction perpendicular to the section to form a blade body assessment section.
The length of the extension in the normal direction needs to satisfy the following conditions: the test fixture is not loaded in the high-temperature area range of the temperature field, the low-temperature area meets the requirement of effective assembly of the test fixture, and the process is feasible. The test piece inner cavity channel comprises a scheme with ribs and a scheme without ribs. The wall thickness of the assessment section can be analyzed according to the simulation out-of-tolerance influence, and on the basis of the original wall thickness, the assessment section comprises a thickening scheme and a thinning scheme.
After the structural design of the blade body examination section is completed, a loading blade shroud is designed for mechanical load loading, and the design of the blade shroud needs to meet the following conditions: the section centroids of the leaf crown and the examination section are the same; the size of the blade shroud needs to meet the strength requirement and the process feasibility requirement; the blade crown is provided with a gas collecting box mounting surface which is used for being connected with the gas collecting box and the ventilating joint, cooling gas inflow and outflow are achieved, the test fixture mounting surface is assembled with the test fixture and transmits load, the test fixture positioning surface is used for achieving axial and circumferential effective positioning of the test piece and the test fixture, and stability of the test piece in the loading process is guaranteed.
The connecting structure ensures that the blade body examination section and the loading blade shroud are connected, and meanwhile, the connecting structure has enough strength and ensures that the test process is not damaged.
As shown in figures 2 and 3, the test piece structure is shown, the middle part of the test piece is a blade body examination section 1, the upper side and the lower side of the blade body examination section 1 are loading blade shrouds 3, the blade body examination section 1 and the loading blade shrouds 3 are connected through a connecting radius 2, the blade body examination section 1 is of a cavity structure to the inside, and a ventilation cavity and an inner cavity partition plate 4 are arranged in the cavity structure.
Step 7, analyzing process feasibility
And (4) carrying out process feasibility analysis on the test pieces designed in the steps 4-6, and properly relaxing the casting quality of the blade shroud on the premise of ensuring the casting quality of the assessment section.
And (4) carrying out strength analysis on the test piece designed in the step (4) to the step (6), and judging whether the examination is effective or not, and whether the connection structure and the blade shroud meet the test loading requirement or not.
The design method of the turbine blade body strength simulation test piece can realize effective loading of mechanical load and effective monitoring of temperature and stress in the test process when simulation test is carried out, so that an effective test result is obtained, and the test piece can be applied to design of turbine blade strength and service life and test verification.
Compared with the prior art, the method and the device solve the problem that the turbine blade structure is difficult to load in a simulation test, realize effective loading of mechanical load and ensure that the connecting part has enough strength in the test process; the problem of temperature and stress distribution change in the loading process caused by the bending and twisting characteristics of the blade structure is solved, and the temperature and stress in the test process are effectively monitored; the scheme of the test piece is optimized, the structural characteristics of the test piece and multiple uncertain factors in the test process are eliminated, and an effective test result is obtained.
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 (5)
1. A method for designing a strength simulation test piece of a turbine blade body of an aircraft engine is characterized by comprising the following steps:
step 1, determining a geometric model of a target turbine blade to be simulated, and a calculation state, material performance data, pneumatic data and temperature data for strength analysis;
step 2, analyzing the strength of the turbine blade test piece
Based on the data such as the geometric model and the state in the step 1, carrying out strength and service life analysis on the turbine blade through finite element software, and combining the strength and service life analysis results to select a key part of interest;
step 3, blade assessment section selection
Combining the strength analysis result of the turbine blade, and selecting a focused attention section in the strength life design of the turbine blade;
step 4, structural design of blade body examination section
Based on the selected concerned section, extending along the normal direction perpendicular to the section to form a blade body examination section;
the inner cavity channel of the blade body examination section comprises a scheme with rib plates and a scheme without rib plates;
the wall thickness of the blade body examination section forms a scheme comprising thickening and thinning on the basis of the original wall thickness according to the simulation out-of-tolerance influence analysis requirement;
step 5, loading the design of the blade shroud
After the structural design of the blade body examination section is finished, designing a loading blade crown for mechanical load loading;
step 6, design of connection structure
The connecting structure ensures that the blade body examination section and the loading blade shroud are connected and have enough strength, so that the test process is not damaged;
step 7, analyzing process feasibility
Carrying out process feasibility analysis on the test pieces designed in the steps 4-6, and properly relaxing the casting quality of the tip shroud on the premise of ensuring the casting quality of the assessment section;
step 8, intensity analysis
And (4) carrying out strength analysis on the test piece designed in the step (4) to the step (6), and judging whether the examination is effective or not, and whether the connection structure and the blade shroud meet the test loading requirement or not.
2. A method of designing a strength simulation test piece for a turbine blade body of an aircraft engine as defined in claim 1, wherein the finite element analysis software includes ANSYS and Abaqus.
3. The method for designing a strength simulation test piece for a blade body of an aircraft engine turbine blade according to claim 1, wherein the sections of interest include a blade root section and a blade leaf section.
4. The method for designing the strength simulation test piece of the blade body of the turbine blade of the aero-engine according to claim 1, wherein the extension length of the blade body examination section in the normal direction meets the following condition: the test fixture is not loaded in the high-temperature area range of the temperature field, the low-temperature area meets the requirement of effective assembly of the test fixture, and the process is feasible.
5. The design method of the strength simulation test piece for the blade body of the turbine blade of the aero-engine according to claim 1, wherein the loading shroud satisfies the following conditions:
the section centroids of the loaded blade crown and the blade body examination section are the same;
the size of the loaded blade shroud meets the strength requirement and the process feasibility requirement;
the loading blade crown is provided with a gas collecting box mounting surface which is used for being connected with the gas collecting box and the ventilating joint, cooling gas inflow and outflow are achieved, the test fixture mounting surface is assembled with the test fixture and transmits load, the test fixture positioning surface is used for achieving axial and circumferential effective positioning of a test piece and the test fixture, and stability of the test piece in the loading process is guaranteed.
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Cited By (2)
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| CN115828713A (en) * | 2023-02-22 | 2023-03-21 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aero-engine |
| CN116046408A (en) * | 2022-09-09 | 2023-05-02 | 中国航发沈阳发动机研究所 | Loading determination and testing method for fatigue test of turbine rear casing structural parts |
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Cited By (3)
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| CN116046408A (en) * | 2022-09-09 | 2023-05-02 | 中国航发沈阳发动机研究所 | Loading determination and testing method for fatigue test of turbine rear casing structural parts |
| CN115828713A (en) * | 2023-02-22 | 2023-03-21 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aero-engine |
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