CN114878375A - Airplane metal material vibration fatigue characteristic testing device and method - Google Patents
Airplane metal material vibration fatigue characteristic testing device and method Download PDFInfo
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- CN114878375A CN114878375A CN202210810938.4A CN202210810938A CN114878375A CN 114878375 A CN114878375 A CN 114878375A CN 202210810938 A CN202210810938 A CN 202210810938A CN 114878375 A CN114878375 A CN 114878375A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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Abstract
The application provides an aircraft metal material vibration fatigue characteristic testing arrangement and test method, and this testing arrangement includes: the vibrating table is used for providing driving force required by vibration for the metal test bar and is fixedly connected with one end of the metal test bar; the cylindrical balancing weight is fixedly arranged at one end of the non-fixed support of the metal test bar, the cylindrical surface of the balancing weight is at least provided with a through groove parallel to the axis of the metal test bar, and a first-order stretching frequency meeting the vibration fatigue characteristic of the metal test bar can be obtained by adjusting the weight of the balancing weight; with leading to the stopper that groove quantity is the same, this stopper has the sand grip that is on a parallel with the logical groove of metal test rod axial and adaptation, realizes preventing the torsion of metal test rod when the vibration is tensile through the cooperation of sand grip and logical groove. The testing device can be used for carrying out the conventional ultrahigh-cycle tensile-compression fatigue test research on typical metal materials of the aero-engine, and obtaining the axial tensile-compression ultrahigh-cycle vibration fatigue S-N curve parameters of the metal materials.
Description
Technical Field
The application belongs to the technical field of vibration fatigue testing, and particularly relates to a device and a method for testing vibration fatigue characteristics of an airplane metal material.
Background
The new generation of aero-engine has important performance indexes such as high thrust-weight ratio, high reliability, long service life and the like, and how to improve the reliability and prolong the safe service life of the aero-engine is one of weak links for the development, use and development of the aero-engine. In the actual work of the aero-engine, the blade disc structure bears the combined action of low-cycle load (generally composed of centrifugal load and steady-state pneumatic load) with large amplitude and low frequency and high-cycle vibration load with small amplitude and high frequency, the complex load easily induces the fatigue failure of parts, and further the major accident of the aero-engine is caused. Statistically, fatigue accounts for over 40% of aircraft engine safety issues, with ultra-high cycle fatigue (10) 7 Above the secondary cycle) is the primary cause of failure in aircraft engines and gas turbines.
The fatigue problem of the typical structure of the aero-engine is researched or verified, and the fatigue characteristic research of the typical metal material of the aero-engine must be expanded from the traditional high-cycle fatigue to the ultrahigh-cycle fatigue. But conventional studies have been to reduce low cycle fatigue (cycles to failure less than 10) 4 ~10 5 ) And high cycle fatigue (cycle to failure at 10 cycles) 5 ~10 7 ) As an important point, the problem of ultra-high cycle fatigue is rarely addressed, and therefore the ultra-high cycle vibration fatigue S-N curve of a typical metallic material for an aircraft engine is also lacking.
Disclosure of Invention
The application aims to provide an aircraft metal material vibration fatigue characteristic testing device to solve or reduce at least one problem in the background art.
The technical scheme of the application is as follows: an aircraft metal material vibration fatigue characteristic testing device, the testing device comprising:
the vibrating table is used for providing driving force required by vibration for the metal test bar and is fixedly connected with one end of the metal test bar;
the cylindrical balancing weight is fixedly arranged at one end of the non-fixed support of the metal test bar, the cylindrical surface of the balancing weight is at least provided with a through groove parallel to the axis of the metal test bar, and the first-order stretching frequency meeting the vibration fatigue characteristic of the metal test bar can be obtained by adjusting the weight of the balancing weight;
with lead to the stopper that groove quantity is the same, the stopper have be on a parallel with metal test bar axial and adaptation the sand grip of leading to the groove, through the sand grip with the cooperation of leading to the groove is realized metal test bar prevents turning round when the vibration is tensile.
Furthermore, the size and specification of the metal test bar are manufactured according to the standard of a metal tensile sample.
Furthermore, the vibration table comprises a plurality of fixing columns with threaded hole structures, the fixing columns are distributed in a scattering manner from the center of the vibration table, and the metal test bar is fixedly connected with the fixing columns at the center position through a threaded structure.
Further, the stopper is right triangle, including right angle base, right angle perpendicular limit and hypotenuse, the sand grip is located right angle perpendicular limit.
Furthermore, at least one bolt hole is formed in the bevel edge, and the limiting block is fixedly connected with the fixing column of the vibration table through a bolt.
Furthermore, the cylindrical surface of the balancing weight is provided with two or more through grooves which are uniformly distributed along the circumferential direction of the axis of the balancing weight.
Furthermore, the balancing weight is connected with the metal test bar through a threaded structure.
In addition, the application also provides a testing method adopting the device for testing the vibration fatigue characteristics of the airplane metal material, and the testing method comprises the following steps:
the method comprises the following steps: fixedly connecting one end of the metal test bar with the balancing weight;
step two: fixedly arranging the other end of the metal test bar at the center of the vibration table to form a fixed supporting structure;
step three: clamping a convex strip of the limiting block and a through groove of the balancing weight together, and adjusting the position of the limiting block to enable the limiting block to be aligned to a fixing hole position of the vibrating table and fixed by a bolt;
step four: lubricating oil is dripped into the through groove of the balancing weight to ensure smoothness, so that the resistance of the metal test rod during vibration, pulling and pressing is minimum;
step five: performing a frequency sweep test on the metal test bar through the vibration table to obtain a first-order stretching frequency of the metal test bar;
step six: performing a calibration test on a metal test bar to obtain an axial tensile displacement calibration value of the metal test bar and a strain calibration value of a dangerous point of the metal test bar, and constructing displacement-strain relation curves under different excitation magnitudes according to the displacement calibration value and the strain calibration value;
step seven: performing a vibration fatigue characteristic test on the metal test bar, and exciting a first-order natural frequency of the metal test bar until the metal test bar is damaged by using sinusoidal excitation to obtain vibration fatigue life and axial tensile displacement of the metal test bar under different excitation values, wherein the vibration fatigue life is the cycle number N;
step eight: according to displacement-strain relation curves under different excitations, deducing the axial tensile displacement of the metal test bar to obtain a strain value of a dangerous point, and then obtaining a stress value S of the dangerous point according to Hooke' S law;
step nine: and fitting to obtain an axial tension and compression ultrahigh-cycle vibration fatigue S-N curve of the metal test bar according to the cycle number N of the metal test bar under different excitation values and the stress value S of the dangerous point obtained in the seventh step and the eighth step.
Further, the axial tensile displacement of the metal test bar is obtained by measuring the height difference at the center of a balancing weight fixedly connected with the metal test bar.
Further, the dangerous point of the metal test bar is positioned in the middle of the arc area of the metal test bar.
By the testing device and the testing method, the research on the ultrahigh-cycle conventional tension-compression fatigue test of the typical metal material of the aircraft engine can be carried out, and the axial tension-compression ultrahigh-cycle vibration fatigue S-N curve parameters of the metal material can be 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 understood that the drawings described below are merely exemplary of some embodiments of the application.
Fig. 1 is a schematic structural diagram of a metal material vibration fatigue characteristic testing apparatus according to the present application.
Fig. 2 is a schematic view of a metal test bar and a balancing weight connected in the testing device of the present application.
Fig. 3 is a schematic view illustrating installation of a limiting block and a balancing weight according to an embodiment of the present application.
Fig. 4 is a relationship curve of a strain test value and a displacement test value under a certain level of excitation in the test method of the present application.
FIG. 5 is an S-N curve of axial tension-compression ultrahigh cycle vibration fatigue of a metal test bar material in the test method 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 test the ultrahigh-cycle vibration fatigue performance of a metal material test bar under axial tension and compression, the application provides a device and a method for testing the vibration fatigue characteristics of the metal material of an airplane.
As shown in fig. 1 to 3, the device for testing the vibration fatigue characteristics of the metal material of the airplane provided by the present application includes: shaking table 1, stopper 2, balancing weight 3 and metal test bar 4.
The vibration table 1 is used to provide a driving force required for vibration. The vibration table 1 provides a range of vibration frequencies that includes the range of vibration frequencies for which the metallic material is to be verified or tested. A plurality of fixing columns 11 which are scattered outwards from the center are arranged on the vibration table 1, and the fixing columns 11 can be used for fixing the limiting blocks 2 and the metal test bars 4.
The structural style and the size of the metal test bar 4 are manufactured according to the relevant national standards, and the general configuration is that the middle part is in an arc shape, and the two ends are in a cylinder shape. One end of the metal test bar 4 is fixedly connected with the vibrating table 1, and the other end of the metal test bar is fixedly provided with a balancing weight 3. In the preferred embodiment of the present application, the two end cylinders of the metal test bar 4 are provided with the thread structures 41, and the cylinder ends of the two sides of the metal test bar 4 can be respectively and fixedly connected with the fixing column 11 and the balancing weight 3 of the vibration table 1 through the thread structures 41.
The balancing weight 3 is fixed at the non-fixed support end of the metal test bar 4, and comprises a plurality of different weight specifications, and the adjustment of the stretching vibration frequency of the metal test bar 4 can be realized by the weight of the balancing weight 3. Furthermore, the peripheral face of cylinder of balancing weight 3 is equipped with one or more axial extension's logical groove 31, and this logical groove 31 can cooperate with stopper 2, realizes that metal test bar 4 is at the tensile anti-twist function of vibration.
The stopper 2 is substantially in the form of a right triangle, the bottom edge 21 of which is flush with the end surface of the fixing post 11 of the vibration table 1, and one or two bolt holes 24 are formed in the oblique edge 23, and bolts are passed through the bolt holes 24 to fix the stopper 2 to the vibration table 1. The right angle stile 22 of stopper 2 is towards metal test rod 4 and balancing weight 3, and with the axial direction parallel of metal test rod 4 and balancing weight 3, has axially extended sand grip 25 on right angle stile 22, and this sand grip 25 can cooperate with logical groove 31 of balancing weight 3, realizes the anti-twist function of metal test rod 4 when the vibration is tensile.
In some embodiments of the present application, the through slots 31 are rectangular slots, and correspondingly, the protruding strips 25 are also rectangular strips.
Furthermore, in a preferred embodiment, the number of the limiting blocks 2 is multiple, and a plurality of through grooves 31 are formed in the cylindrical surface of the counterweight block 3. The better torsion-proof function is realized through the through grooves 31 and the limiting blocks 2. For example, in the embodiment shown in the figure, the number of the limiting blocks 2 is 4, the cylindrical surface of the counterweight block 3 is provided with 4 through grooves 31, and the four limiting blocks 2 are uniformly distributed along the axis of the metal test rod 4.
The testing device provided by the application can obtain the first-order stretching frequency of the metal test bar meeting the test requirement by adjusting the weight of the balancing weight 3; the testing device has the advantages that the axial tension-compression movement of the metal test bar 4 cannot be influenced, the torsion or bending mode of the metal test bar 4 cannot be excited, the testing device is simple in structure, convenient in loading mode and convenient to disassemble.
The testing process of the metal material vibration fatigue characteristic testing device is as follows:
the method comprises the following steps: connecting one end of a metal test rod 4 with a balancing weight 3 through a thread structure 41, and performing anti-loosening treatment;
step two: screwing the other end of the metal test bar 4 into a threaded hole of a fixed column 11 in the center of the vibration table 1, and performing anti-loosening treatment;
step three: the raised strips 25 of the limiting blocks 2 are clamped with the through grooves 31 of the balancing weights 3, the positions of the limiting blocks 2 are adjusted to be aligned with the hole positions of the fixing columns 11 of the vibrating table 1 and fixed by bolts, the limiting blocks 2 are uniformly distributed around the metal test bars 4 in the circumferential direction, for example, the included angles between every two 4 limiting blocks 2 are 90 degrees, and the uniform distribution is completed;
step four: lubricating oil is dripped into the through groove 31 of the balancing weight 3 to ensure smoothness, so that the resistance of the metal test rod 4 during tension and compression vibration is minimum;
step five: performing a frequency sweep test on the metal test bar 4 through the vibration table 1 to obtain a first-order stretching frequency of the metal test bar 4;
step six: performing a calibration test on the metal test rod 4 to obtain an axial tensile displacement calibration value of the metal test rod 4 and a strain calibration value of a dangerous point or a dangerous area of the metal test rod 4, thereby constructing a displacement-strain relation curve (an excitation a-displacement delta-strain epsilon curve) under different excitation magnitudes, as shown in table 1 and fig. 4;
TABLE 1 Displacement and Strain data at different excitation levels
| Acceleration excitation a | Displacement delta | Strain epsilon |
| a 0 | Δ 0 | ε 0 |
| a 1 | Δ 1 | ε 1 |
| a 2 | Δ 2 | ε 2 |
| …… | …… | …… |
| a n | Δ n | ε n |
Wherein, the displacement measurement point of metal test bar 4 is located the 3 center departments of balancing weight on 4 tops of metal test bar, and accessible laser range finder aims at the center of balancing weight 3 and measures and obtain, and the strain measurement point of danger point is located the intermediate position of 4 circular arc regions of metal test bar (thin neck department), and the accessible bonds the foil gage and obtains the strain calibration value here.
Step seven: carrying out formal test on the metal test bar 4, exciting a first-order natural frequency of the metal test bar 4 by using sinusoidal excitation until the metal test bar is damaged, obtaining the vibration fatigue life under different excitation values, namely the cycle number N, and measuring and recording the axial tensile displacement delta of the metal test bar 4;
note that to obtain the ultrasoundsHigh cycle vibration fatigue S-N curve, cycle frequency range is set as 4 groups (10) 6 ~10 7 、10 7 ~10 8 、10 8 ~10 9 、10 9 Above).
Step eight: according to the excitation a-displacement delta-strain epsilon curve obtained in the sixth step, deducing a strain value epsilon of the dangerous point from the top displacement delta, and then obtaining a stress value S of the dangerous point according to the Hooke' S law;
step nine: and (3) obtaining the fatigue life of the metal test rod 4 under different excitation values obtained in the seventh step and the eighth step, namely the cycle number N and the stress value S of the dangerous point by adopting a scattered point method to fit and obtain an axial tension and compression ultrahigh cycle vibration fatigue S-N curve of the metal test rod material, as shown in figure 5.
By the testing method, the research on the ultrahigh-cycle conventional tension-compression fatigue test of the typical metal material of the aircraft engine can be carried out, and the axial tension-compression ultrahigh-cycle vibration fatigue S-N curve parameters of the metal material can be 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 (10)
1. An aircraft metal material vibration fatigue characteristic testing device, characterized in that, the testing device includes:
the vibrating table (1) is used for providing driving force required by vibration for the metal test bar (4), and the vibrating table (1) is fixedly connected with one end of the metal test bar (4);
the cylindrical balancing weight (3) is fixedly arranged at one end of the metal test bar (4) which is not fixedly supported, the cylindrical surface of the balancing weight (3) is at least provided with a through groove (31) parallel to the axis of the metal test bar, and the first-order stretching frequency meeting the vibration fatigue characteristic of the metal test bar can be obtained by adjusting the weight of the balancing weight (3);
with lead to stopper (2) that groove (31) quantity is the same, stopper (2) have be on a parallel with metal test rod (4) axial and adaptation sand grip (25) of leading to groove (31), through sand grip (25) with the cooperation that leads to groove (31) is realized metal test rod (4) prevent twisting when the vibration is tensile.
2. The aircraft metal material vibration fatigue characteristic testing device as claimed in claim 1, wherein the dimensions and specifications of the metal test bar (4) are manufactured according to metal tensile sample standards.
3. The aircraft metal material vibration fatigue characteristic testing device according to claim 2, wherein the vibration table (1) comprises a plurality of fixing columns (11) with threaded hole structures, the fixing columns (11) are distributed in a scattering manner from the center of the vibration table (1), and the metal test bar (4) is fixedly connected with the fixing columns (11) at the center position through threaded structures (41).
4. The aircraft metal material vibration fatigue characteristic testing device of claim 3, wherein the limiting block (2) is in a shape of a right triangle and comprises a right-angle bottom edge (21), a right-angle vertical edge (22) and a bevel edge (23), and the convex strip (25) is positioned on the right-angle vertical edge (22).
5. The aircraft metal material vibration fatigue characteristic testing device of claim 4, characterized in that at least one bolt hole (24) is arranged on the bevel edge (23), and the limiting block (2) is fixedly connected with the fixing column (11) of the vibration table (1) through a bolt.
6. The aircraft metal material vibration fatigue characteristic testing device of claim 1, wherein the cylindrical surface of the balancing weight (3) is provided with two or more through grooves (31), and the through grooves (31) are circumferentially and uniformly distributed with the axis of the balancing weight (3).
7. The aircraft metal material vibration fatigue characteristic testing device of claim 6, wherein the balancing weight (3) and the metal test bar (4) are connected through a thread structure (41).
8. A test method using the aircraft metal material vibration fatigue characteristic test apparatus according to any one of claims 1 to 7, characterized in that the test method comprises:
the method comprises the following steps: one end of the metal test bar (4) is fixedly connected with the balancing weight (3);
step two: the other end of the metal test bar (4) is fixedly arranged at the center of the vibration table (1) to form a fixed supporting structure;
step three: clamping a convex strip (25) of the limiting block (2) and a through groove (31) of the balancing weight (3) together, and adjusting the position of the limiting block (2) to enable the limiting block (2) to be aligned to a fixing hole position of the vibrating table (1) and fixed by a bolt;
step four: lubricating oil is dripped into the through groove (31) of the balancing weight (3) to ensure smoothness, so that the resistance of the metal test bar (4) during vibration, pulling and pressing is minimum;
step five: performing a frequency sweep test on the metal test bar (4) through the vibration table (1) to obtain a first-order stretching frequency of the metal test bar (4);
step six: performing a calibration test on a metal test bar (4) to obtain an axial tensile displacement calibration value of the metal test bar (4) and a strain calibration value of a dangerous point of the metal test bar (4), and constructing displacement-strain relation curves under different excitation magnitudes according to the displacement calibration value and the strain calibration value;
step seven: performing a vibration fatigue characteristic test on the metal test bar (4), and exciting a first-order natural frequency of the metal test bar (4) by using sinusoidal excitation until the first-order natural frequency is destroyed to obtain the vibration fatigue life and the axial tensile displacement of the metal test bar (4) under different excitation values, wherein the vibration fatigue life is the cycle number N;
step eight: according to displacement-strain relation curves under different excitations, deducing the axial tensile displacement of the metal test bar (4) to obtain a strain value of a dangerous point, and then obtaining a stress value S of the dangerous point according to Hooke' S law;
step nine: and fitting to obtain an axial tension-compression ultrahigh-cycle vibration fatigue S-N curve of the metal test bar (4) according to the cycle number N of the metal test bar (4) under different excitation values and the stress value S of the dangerous point obtained in the seventh step and the eighth step.
9. The test method according to claim 8, wherein the axial tensile displacement of the metal test bar (4) is obtained by measuring a height difference at the center of a weight block (3) fixedly connected to the metal test bar (4).
10. The test method according to claim 8, wherein the dangerous point of the metal test bar (4) is located at a middle position of the circular arc region of the metal test bar (4).
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Application publication date: 20220809 |