CN114840931B - Design method of aero-engine turbine blade body strength simulation test piece - Google Patents
Design method of aero-engine turbine blade body strength simulation test piece Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 51
- 238000004088 simulation Methods 0.000 title claims abstract description 27
- 230000008719 thickening Effects 0.000 claims abstract description 4
- 238000005266 casting Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 238000009423 ventilation Methods 0.000 claims description 4
- 239000000112 cooling gas Substances 0.000 claims description 3
- 238000005452 bending Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000002045 lasting effect Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The application provides a design method of an aeroengine turbine blade body strength simulation test piece, which comprises the following steps: determining a target turbine blade geometric model to be simulated, calculating states for strength analysis and other data; based on the geometric model, state and other data, carrying out turbine blade strength and service life analysis through finite element software, and selecting important focusing parts and important focusing sections according to the combination 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 checking section comprises a scheme with rib plates and a scheme without rib plates; forming a solution comprising thickening and thinning on the basis of the original wall thickness; designing a loading tip shroud for mechanical load loading; designing a connection structure of a blade body examination section and a loading blade crown; and carrying out process feasibility analysis and strength analysis aiming at the designed test piece, and judging whether the examination is effective or not, and whether the connecting structure and the tip shroud meet the test loading requirement or not.
Description
Technical Field
The application belongs to the field of strength design of aeroengines, and particularly relates to a method for designing a blade body strength simulation test piece of a turbine blade of an aeroengine.
Background
The turbine blade is one of the most critical parts of the aeroengine, and the life simulation test of the turbine blade is a key step for verifying the forward design of the turbine blade from materials to components and then to the whole machine in a laboratory environment.
In order to meet the use requirement of a turbine in a severe working condition environment, a turbine blade often has a complex space curved surface structure and a complex service condition, and the problems of simulation of a stress field and a temperature field and the like are solved when a real blade 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 possibly becomes a weak part, and the joint is easy to damage in advance in the test process; for blade structures with obvious bending and twisting and other design characteristics, the loading process tends to complicate the load transmission process on the blade-shaped section, and the stress and temperature distribution of the test section are difficult to meet expectations; because the structural characteristics of the test piece, the test process and other influence factors are not clear, the current test result cannot be clearly concluded.
Disclosure of Invention
The invention aims to provide a design method of a blade body strength simulation test piece of an aeroengine turbine blade, which aims to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: a design method of an aero-engine turbine blade body strength simulation test piece comprises the following steps:
step 1, determining a target turbine blade geometric model to be simulated, and calculating states, material performance data, aerodynamic data and temperature data for strength analysis;
step 2, turbine blade test piece strength analysis
Based on the geometric model and the state and other data in the step 1, carrying out turbine blade strength and service life analysis through finite element software, and selecting important focusing parts according to the combination strength and service life analysis results;
step 3, selecting a blade checking section
Selecting a focus section in the strength life design of the turbine blade by combining the strength analysis result of the turbine blade;
step 4, blade body checking section structural design
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 checking section comprises a scheme with rib plates and a scheme without rib plates;
the wall thickness of the blade body checking 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 tip shroud design
After the structural design of the blade body examination section is completed, designing a loading blade shroud for mechanical load loading;
step 6, design of connection structure
The connecting structure ensures that the blade body checking section is connected with the loading blade shroud, and meanwhile, the connecting structure has enough strength, so that the test process is not damaged;
step 7, process feasibility analysis
Carrying out process feasibility analysis aiming at the test pieces designed in the steps 4-6, and allowing proper relaxation of the casting quality of the tip shroud on the premise of guaranteeing the casting quality of the checking section;
step 8, intensity analysis
And (3) carrying out strength analysis aiming at the test pieces designed in the steps 4-6, and judging whether the examination is effective or not, and whether the connecting structure and the tip shroud meet the test loading requirement or not.
Further, the finite element analysis software includes ANSYS and Abaqus.
Further, the concerned section comprises a blade root section and a blade middle section.
Further, the normal direction extension length of the blade body checking section meets the following conditions: the test clamp is not in the range of the high temperature area loaded by the temperature field, and the low temperature area meets the requirement that the test clamp has effective assembly and feasible process.
Further, the loading tip shroud satisfies the following condition:
the section centroid of the loading tip shroud and the section centroid of the blade body checking section are the same;
the size of the loading tip shroud meets the strength requirement and the process feasibility requirement;
the loading blade shroud is provided with a gas collecting box mounting surface and is used for being connected with a ventilation joint through the gas collecting box, cooling gas flows in and out, the test fixture mounting surface is used for being assembled with a test fixture and transmitting load, and the test fixture positioning surface is used for effectively positioning a test piece and the test fixture axially and circumferentially, so that stability of the test piece in the loading process is guaranteed.
Compared with the prior art, the method solves the problem of difficult loading of the turbine blade structure simulation test, realizes effective loading of mechanical load, and ensures that the connecting part in the test process has enough strength; the problem of temperature and stress distribution change in the loading process of the blade structure caused by the bending and twisting characteristics is solved, and the temperature and stress in the test process are effectively monitored; the test piece scheme is optimized, and the structural characteristics of the test piece and various uncertain factors in the test process are eliminated, so that an effective test result is obtained.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
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 airfoil strength simulation test piece of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to solve the problems of difficult mechanical load loading, large stress and temperature control difficulty in the test process, poor data effectiveness and the like in the turbine blade simulation test in the prior art, the design method of the test piece for the turbine blade body strength simulation test is provided, and the test piece design method can realize simulation tests such as stretching, lasting, fatigue and the like, so that effective performance data of a key section of the blade body is obtained, and technical support is provided for the establishment of the turbine blade strength, service life design and test verification method.
In order to obtain the test piece so that the strength assessment of the key section of the turbine blade and the actual mechanical property can be subjected to comparison study, the design method of the turbine blade body strength simulation test piece of the aeroengine, provided by the application, comprises the following steps:
step 1, determining a target turbine blade geometric model to be simulated, and calculating states, material performance data, aerodynamic data and temperature data for strength analysis;
step 2, turbine blade test piece strength analysis
Based on the geometric model and state data of the step 1, finite element software such as ANSYS, abaqus and the like is applied to carry out turbine blade strength and service life analysis, the strength and service life analysis results are combined, and important focused parts are selected as references for subsequent section selection;
step 3, selecting a blade checking section
And selecting a focus section in the strength life design of the turbine blade by combining the strength analysis result of the turbine blade, wherein the interface mainly comprises a blade root section, a blade middle section and the like.
Step 4, blade body checking section structural design
And (3) based on the concerned section (or the checking section) selected in the step three, extending along the normal aspect perpendicular to the section to form the blade body checking section.
The length of the normal direction extension needs to satisfy the following conditions: the test clamp is not in the range of the high temperature area loaded by the temperature field, and the low temperature area meets the requirement that the test clamp has effective assembly and feasible process. The inner cavity channel of the test piece comprises a scheme with rib plates and a scheme without rib plates. The wall thickness of the examination section can be analyzed according to the simulation out-of-tolerance influence, and the method comprises a thickening scheme and a thinning scheme on the basis of the original wall thickness.
Step 5, loading tip shroud design
After the structural design of the blade body examination section is completed, the loading blade shroud is designed for mechanical load loading, and the blade shroud design needs to meet the following conditions: the cross section centroid of the leaf cap is the same as that of the examination section; the size of the tip shroud needs to meet the strength requirement and the process feasibility requirement; the blade shroud possesses the gas collecting box installation face and is used for being connected through gas collecting box and ventilation joint, realizes that the cooling gas flows in and out, and test fixture installation face realizes with test fixture assembly and transmission load, and test fixture locating surface realizes test piece and test fixture axial and circumference effective positioning, guarantee loading process test piece stability.
Step 6, design of connection structure
The connecting structure ensures that the blade body checking section is connected with the loading blade shroud, and meanwhile, the connecting structure has enough strength, and the test process is not damaged.
As shown in fig. 2 and 3, the test piece structure is shown, the middle part of the test piece is a blade body checking section 1, loading blade crowns 3 are arranged on the upper side and the lower side of the blade body checking section 1, the blade body checking section 1 is connected with the loading blade crowns 3 through a connecting rounding 2, the inside of the blade body checking section 1 is of a cavity structure, and a ventilation cavity and an inner cavity partition board 4 are arranged in the cavity structure.
Step 7, process feasibility analysis
And (3) carrying out process feasibility analysis on the test pieces designed in the steps 4-6, and properly widening the casting quality of the tip shroud on the premise of guaranteeing the casting quality of the checking section.
Step 8, intensity analysis
And (3) carrying out strength analysis aiming at the test pieces designed in the steps 4-6, and judging whether the examination is effective or not, and whether the connecting structure and the tip 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 during simulation test, and effectively monitor temperature and stress during test, so that an effective test result is obtained, and the test piece can be applied to turbine blade strength, life design and test verification.
Compared with the prior art, the method solves the problem of difficult loading of the turbine blade structure simulation test, realizes effective loading of mechanical load, and ensures that the connecting part in the test process has enough strength; the problem of temperature and stress distribution change in the loading process of the blade structure caused by the bending and twisting characteristics is solved, and the temperature and stress in the test process are effectively monitored; the test piece scheme is optimized, and the structural characteristics of the test piece and various uncertain factors in the test process are eliminated, so that an effective test result is obtained.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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. The design method of the blade body strength simulation test piece of the turbine blade of the aeroengine is characterized by comprising the following steps of:
step 1, determining a target turbine blade geometric model to be simulated, and calculating states, material performance data, aerodynamic data and temperature data for strength analysis;
step 2, turbine blade test piece strength analysis
Based on the geometric model and the state and other data in the step 1, carrying out turbine blade strength and service life analysis through finite element software, and selecting important focusing parts according to the combination strength and service life analysis results;
step 3, selecting a blade checking section
Selecting a focus section in the strength life design of the turbine blade by combining the strength analysis result of the turbine blade;
step 4, blade body checking section structural design
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 checking section comprises a scheme with rib plates and a scheme without rib plates;
the wall thickness of the blade body checking 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 tip shroud design
After the structural design of the blade body examination section is completed, designing a loading blade shroud for mechanical load loading;
step 6, design of connection structure
The connecting structure ensures that the blade body checking section is connected with the loading blade shroud, and meanwhile, the connecting structure has enough strength, so that the test process is not damaged;
step 7, process feasibility analysis
Carrying out process feasibility analysis aiming at the test pieces designed in the steps 4-6, and allowing proper relaxation of the casting quality of the tip shroud on the premise of guaranteeing the casting quality of the checking section;
step 8, intensity analysis
And (3) carrying out strength analysis aiming at the test pieces designed in the steps 4-6, and judging whether the examination is effective or not, and whether the connecting structure and the tip shroud meet the test loading requirement or not.
2. The aircraft engine turbine blade airfoil strength simulation test piece design method of claim 1, wherein the finite element analysis software comprises ANSYS and Abaqus.
3. The aircraft engine turbine blade airfoil strength simulation test piece design method of claim 1, wherein the section of interest comprises a blade root section, a blade center section.
4. The aircraft engine turbine blade body strength simulation test piece design method according to claim 1, wherein the normal direction extension length of the blade body checking section meets the following conditions: the test clamp is not in the range of the high temperature area loaded by the temperature field, and the low temperature area meets the requirement that the test clamp has effective assembly and feasible process.
5. The aircraft engine turbine blade body strength simulation test piece design method as claimed in claim 1, wherein the loading tip shroud satisfies the following conditions:
the section centroid of the loading tip shroud and the section centroid of the blade body checking section are the same;
the size of the loading tip shroud meets the strength requirement and the process feasibility requirement;
the loading blade shroud is provided with a gas collecting box mounting surface and is used for being connected with a ventilation joint through the gas collecting box, cooling gas flows in and out, the test fixture mounting surface is used for being assembled with a test fixture and transmitting load, and the test fixture positioning surface is used for effectively positioning a test piece and the test fixture axially and circumferentially, so that stability of the test piece in the loading process is guaranteed.
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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 |
| CN115828713B (en) * | 2023-02-22 | 2023-04-18 | 中国航发沈阳发动机研究所 | Design method of single crystal turbine blade shroud of aircraft engine |
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| CN107084844A (en) * | 2017-04-19 | 2017-08-22 | 西北工业大学 | A kind of test method of blade construction simulating piece |
| CN109885882A (en) * | 2019-01-21 | 2019-06-14 | 北京航空航天大学 | A kind of design method of blade of aviation engine simulating piece |
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| CN107084844A (en) * | 2017-04-19 | 2017-08-22 | 西北工业大学 | A kind of test method of blade construction simulating piece |
| CN109885882A (en) * | 2019-01-21 | 2019-06-14 | 北京航空航天大学 | A kind of design method of blade of aviation engine simulating piece |
| RU2721514C1 (en) * | 2019-04-17 | 2020-05-19 | Евгения Викторовна Георгиевская | Method for evaluation of residual life of hydraulic turbine impeller at beyond design basis of operation |
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