CN113866016B - Multi-axis short crack propagation life prediction method considering non-proportional loading additional damage - Google Patents
Multi-axis short crack propagation life prediction method considering non-proportional loading additional damage Download PDFInfo
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Abstract
The invention discloses a multi-axis short crack propagation life prediction method considering non-proportional path additional damage, which comprises the steps of selecting a weight critical surface as a critical surface, and utilizing damage parameters on the critical surface to represent a short crack propagation driving force; selecting two points with the farthest distance in a corresponding loading path on a critical plane, solving the distance between the two points as the maximum equivalent stress Fan Cheng, correcting the maximum equivalent stress Fan Cheng to obtain equivalent stress, taking crack closure into consideration by using a Newman closure formula, and calculating an effective stress intensity factor by combining the equivalent stress obtained before; obtaining a uniaxial short crack expansion curve by fitting the short crack expansion rate and stress intensity factor data under uniaxial loading, and carrying out next calculation by taking the uniaxial short crack expansion curve as a base line; and calculating the short crack extension full life under constant amplitude loading states such as different stress ratios, different loading paths and the like based on a Paris formula. The method can well describe the influence of additional damage on crack propagation under non-proportional loading.
Description
Technical Field
The invention relates to the application field of multi-axis fatigue strength life prediction, in particular to a multi-axis short crack propagation life prediction method considering non-proportional loading additional damage.
Background
The fatigue failure process can be divided into three stages of crack formation, crack propagation and final fracture. The crack source is often broken through crystals from large grains at the subsurface to form sub-microscopic fatigue cracks, then penetrates through several grains along the direction of shear stress, and then continues to propagate along the direction perpendicular to the tensile stress to gradually form macroscopic cracks. With the development of crack detection technology, the proportion of crack initiation life is smaller and smaller, the proportion of total life of crack propagation is larger and larger, and the short crack problem becomes a main problem because of the smaller proportion of the total life of fatigue in the long crack propagation stage.
The short crack problem is researched, fatigue is easily known from microscopic and submicroscopic levels, so that the whole fatigue process is known, the whole life prediction can be performed, the whole life prediction is not required to be divided into crack initiation life and crack expansion life, and the method is more convenient to apply to engineering. For multi-axis short crack growth, the lack of solution of equivalent stress Fan Cheng under non-proportional path loading results in the lack of accurate solution of stress intensity factors, and in addition, the difficulty in obtaining test data of multi-axis fatigue short crack is high, so that the research of the multi-axis fatigue short crack growth model is slow. Therefore, the method for predicting the multi-axis short crack life under the proportional load and the non-proportional load is studied in depth, can be applied to the field of actual engineering in an expanded mode, and is a very meaningful work.
Disclosure of Invention
Aiming at the requirements of multi-axis fatigue strength design under different load paths, the invention provides a multi-axis short crack propagation life prediction method based on consideration of non-proportional loading additional damage.
The invention provides a multiaxial short crack propagation model considering non-proportional loading additional damage, which comprises the following steps:
step 1): under multiaxial stress loading, cracks mainly sprout on critical surfaces of the thin-wall pipe fitting; the weight critical surface is selected as the critical surface, and the damage parameter on the critical surface is utilized to represent the short crack expansion driving force, and the calculation flow of the weight critical surface is as follows:
τ in max (t k )——t k A maximum shear stress value (MPa) at time;
φ -45°-45° (t k ) The angle between the normal vector of the maximum absolute shear stress surface and the x axis,
-45°≤φ -45°-45° (t k )≤45°；
φ 0°-45° (t k )——φ -45°-45° (t k ) Absolute value of (2) is 0 DEG to phi 0°-45° (t k )≤45°
In the middle ofWeight average maximumFor shear stress plane->Normal vector and x-axis angle;
W(t k )——t k weight function of time, i.e.
W total -weight function W (t) k ) From t 1 To t N Summation of moments;
step 2): establishing an effective crack stress intensity factor applicable to a multiaxial stress state based on multiaxial fatigue damage parameters under different loading paths; the effective stress intensity factor delta K eff The calculation steps are as follows:
(1) Selecting two points with the farthest distance in a corresponding loading path on a critical surfaceAnd->The distance between the two points is obtained to obtain the maximum equivalent stress Fan Cheng sigma e The following are provided:
wherein,and->And->Is the stress state at any moment on the critical surface;
(2) Correcting the maximum equivalent stress Fan Cheng, and considering the non-proportional loading additional damageTo obtain the equivalent stress delta sigma eq The following are provided:
Δσ eq ＝Δσ e (1+gF)
wherein g is a non-proportional additional damage factor related to material characteristics, and the material used for the test herein has a value of 7075-T651 that is calculated as g by 90 degrees of test life under non-proportional loading; f is a twiddle factor range of 0-1;
(3) The Newman closure formula is used to consider crack closure, combined with the equivalent stress previously found, the effective stress intensity factor Δk eff The formula is:
wherein Y is a shape factor, U is a closure coefficient, a is a half crack length, Δσ eq Is equivalent stress;
step 3): obtaining a uniaxial short crack expansion curve by fitting the short crack expansion rate and stress intensity factor data under uniaxial loading, and carrying out next calculation by taking the uniaxial short crack expansion curve as a base line; the crack growth curve in Paris is formulated as follows:
wherein,the crack propagation rate is C, m is a constant fitted under uniaxial loading;
step 4): short crack propagation life was calculated by the Paris formula:
(1) Determining the initial size of a crack, wherein the microstructure has an important influence on crack propagation, and selecting the obstacle scale of the microstructure of the material as the initial length of the short crack, wherein the initial length of the short crack is related to the grain size of the material;
(2): by using the calculated effective stress intensity factor model and based on the Paris formula, the small crack extension full life under constant amplitude loading states of different stress ratios, different loading paths and the like can be calculated, and the corresponding calculation formula is as follows:
wherein N is the crack propagation life of the sample, a 0 For the initial size of the crack, a f Is the final failure size.
The invention has the advantages that: the multi-axis short crack full life prediction method considering the non-proportional loading additional damage is applicable to life prediction of the non-proportional loading additional damage, and can also be applicable to life prediction of the non-proportional loading additional damage. According to the method, on a critical surface, the effective stress intensity factor is used for representing the short crack expansion driving force under a complex state, meanwhile, the influence of additional damage and crack closure effect of a non-proportional loading path is considered, and the method has clear physical significance and is convenient for practical engineering application.
Drawings
The method of the invention of FIG. 1 provides a flow chart of a multi-axis short crack life prediction method considering non-proportional loading additional damage.
FIG. 2 selects the maximum equivalent stress Fan Cheng Sigma in the corresponding loading path on the critical plane e Schematic diagram.
Fig. 3 is a life prediction result diagram.
Detailed Description
Specific embodiments of the present invention will be described with reference to the accompanying drawings.
The invention is further described through a fatigue test, the test is divided into two parts, one part is a small crack expansion test under the loading of uniaxial constant amplitude stress, the waveform is sine wave, the stress ratio is-1, and the surface of a thin-wall pipe test piece is subjected to replica method to obtain small crack expansion rate data for fitting Paris constant. And the other part is a multi-axis proportion and non-proportion constant amplitude test of stress control loading, so that corresponding service life data are obtained.
The multiaxial short crack life prediction method considering non-proportional loading additional damage comprises the following specific calculation method:
step 1): under the multiaxial loading state, cracks mainly initiate on a critical surface of the thin-wall pipe fitting; the weight critical surface is selected as the critical surface, and the damage parameter on the critical surface is utilized to represent the short crack expansion driving force, and the calculation flow of the weight critical surface is as follows:
τ in max (t k )——t k A maximum shear stress value (MPa) at time;
φ -45°-45° (t k ) The angle between the normal vector of the maximum absolute shear stress surface and the x axis,
-45°≤φ -45°-45° (t k )≤45°；
φ 0°-45° (t k )——φ -45°-45° (t k ) Absolute value of (2) is 0 DEG to phi 0°-45° (t k )≤45°；
In the middle of-weight average maximum absolute shear stress plane +.>Normal vector and x-axis angle;
W(t k )——t k weight function of time, i.e.
W total -weight function W (t) k ) From t 1 To t N Summation of moments;
step 2): establishing an effective crack stress intensity factor applicable to a multiaxial stress state based on multiaxial fatigue damage parameters under different loading paths; the effective stress intensity factor delta K eff The calculation steps of (a) are as follows:
(1) Selecting two points with the farthest distance in a corresponding loading path on a critical surfaceAnd->The distance between the two points is obtained to obtain the maximum equivalent stress Fan Cheng sigma e The following are provided:
wherein,and->And->Is the stress state at any moment on the critical surface;
(2) Correcting the maximum equivalent stress Fan Cheng, and obtaining the equivalent stress delta sigma by considering the influence of the non-proportional loading additional damage eq The following are provided:
Δσ eq ＝Δσ e (1+gF)
wherein g is a non-proportional additional damage factor related to material characteristics, and the material used for the test herein has a value of 7075-T651 that is calculated as g by 90 degrees of test life under non-proportional loading; f is a twiddle factor range of 0-1;
(3) The Newman closure formula is used to consider crack closure, combined with the equivalent stress previously found, the effective stress intensity factor Δk eff The formula is:
wherein Y is a shape factor, U is a closure coefficient, a is a half crack length, Δσ eq Is equivalent stress;
step 3): the effective stress intensity factor delta K can be obtained through calculation through the service life of the test piece under constant amplitude and the crack length data corresponding to the service life of the test piece obtained in the uniaxial tension and compression test eff A double logarithmic curve between the crack propagation speed and the crack propagation constant C and m are fitted, and the next calculation is carried out by taking the double logarithmic curve as a base line; the crack growth curve in Paris is formulated as follows:
wherein,the crack propagation rate is C, m is a constant fitted under uniaxial loading;
step 4): short crack propagation life was calculated by the Paris formula:
(1) Determining the initial size of a crack, wherein the microstructure has an important influence on crack propagation, and selecting the obstacle scale of the microstructure of the material as the initial length of the short crack, wherein the initial length of the short crack is related to the grain size of the material;
(2): by using the calculated effective stress intensity factor model and based on the Paris formula, the small crack extension full life under constant amplitude loading states of different stress ratios, different loading paths and the like can be calculated, and the corresponding calculation formula is as follows:
wherein N is the crack propagation life of the sample, a 0 For the initial size of the crack, a f Is the final failure size.
In order to verify the effect of the multi-axis short crack full life prediction method considering the non-proportional loading additional damage, the prediction result obtained by the method is compared with the experimental observation life obtained by the multi-axis proportional and non-proportional loading experiment. The result shows that the life predicted based on the method model is within a double error factor compared with the life observed under the test of multiaxial proportion and non-proportional loading. The method considers the influence of critical planes and non-proportional loading additional damage on crack propagation. Therefore, the calculation method can better predict the whole service life of the short crack extension under the loading of multiaxial proportion and non-proportion.
Claims (3)
1. The multiaxial short crack propagation life prediction method considering non-proportional loading additional damage is characterized in that: the steps are as follows,
step 1): under multiaxial stress loading, cracks mainly sprout on critical surfaces of the thin-wall pipe fitting; selecting a weight critical surface as a critical surface, and utilizing damage parameters on the critical surface to represent a short crack expansion driving force, wherein the calculation flow of the weight critical surface is as follows:
τ in max (t k )——t k The maximum shear stress value at the moment, MPa;
φ -45°-45° (t k ) The angle between the normal vector of the maximum absolute shear stress surface and the x axis,
-45°≤φ -45°-45° (t k )≤45°；
φ 0°-45° (t k )——φ -45°-45° (t k ) Is used for the control of the absolute value of (a),0°≤φ 0°-45° (t k )≤45°
in the middle of-weight average maximum absolute shear stress plane +.>Normal vector and x-axis angle;
W(t k )——t k weight function of time, i.e.
W total -weight function W (t) k ) From t 1 To t N Summation of moments;
angle ofThe positive and negative are determined by the following formula:
the weight average maximum shear stress value is in planeAnd->The upper parts are equal, and a plane with a larger maximum positive stress value is defined as a critical plane under the condition of constant amplitude loading;
step 2): based on different additionsEstablishing an effective crack stress intensity factor applicable to a multiaxial stress state by using multiaxial fatigue damage parameters under a load path; the effective crack stress intensity factor delta K eff The calculation steps of (a) are as follows:
(1) Selecting two points with the farthest distance in a corresponding loading path on a critical surfaceAnd->The distance between the two points is obtained to obtain the maximum equivalent stress Fan Cheng sigma e The following are provided:
wherein,and->And->Is the stress state at any moment on the critical surface;
(2) Correcting the maximum equivalent stress Fan Cheng, and taking the influence of additional damage of the non-proportional path into consideration to obtain equivalent stress delta sigma eq The following are provided:
Δσ eq ＝Δσ e (1+gF)
wherein g is a non-proportional additional damage factor and is related to the material characteristics, the material for test is 7075-T651, and the value of g is 0.1 by the test life reverse push under 90-degree non-proportional loading; f is a twiddle factor range of 0-1;
(3) Closing with NewmanThe formula considers the crack closure, combines the equivalent stresses previously found, the effective crack stress intensity factor DeltaK eff The formula is:
wherein Y is a shape factor, U is a closure coefficient, a is a half crack length, Δσ eq Is equivalent stress;
step 3): the effective crack stress intensity factor delta K is obtained through calculation by the service life of the test piece under constant amplitude and the crack length data corresponding to the service life obtained in the uniaxial tension and compression test eff A double logarithmic curve between the crack propagation speed and the crack propagation constant C and m are fitted, and the next calculation is carried out by taking the double logarithmic curve as a base line; the crack growth curve in Paris is formulated as follows:
wherein,the crack propagation rate is C, m is a constant fitted under uniaxial loading;
step 4): short crack propagation life was calculated by the Paris formula:
(1) Determining the initial size of a crack, wherein the microstructure has an important influence on crack propagation, and selecting the obstacle scale of the microstructure of the material as the initial length of the short crack, wherein the initial length of the short crack is related to the grain size of the material;
(2): by using the effective crack stress intensity factor formula and based on the Paris formula, calculating the small crack expansion life under constant amplitude loading states of different stress ratios, different loading paths and the like, wherein the corresponding calculation formula is as follows:
wherein N is the crack propagation life of the sample, a 0 For the initial size of the crack, a f Is the final failure size.
2. The multi-axis short crack propagation life prediction method considering non-proportional path additional damage as claimed in claim 1, wherein: the equivalent stress selected in the step 2 (2)) mainly considers the influence of the non-proportional path additional damage to introduce a non-proportional additional damage factor g and a rotation factor F, and calculates an effective stress intensity factor delta K by combining a crack closure effect eff And crack propagation is believed to occur at the critical plane.
3. The multi-axis short crack propagation life prediction method considering non-proportional path additional damage as claimed in claim 1, wherein: and 4) selecting the microstructure characteristic scale of the material as the initial crack size, and conforming to a crack initiation and propagation mechanism.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105466772A (en) * | 2015-11-15 | 2016-04-06 | 北京工业大学 | Multiaxial short crack propagation life prediction method based on critical surface method |
| CN108897900A (en) * | 2018-03-24 | 2018-11-27 | 北京工业大学 | A kind of lower PROPAGATION OF FATIGUE SHORT CRACKS life-span prediction method of multiaxis luffing load |
| CN109918789A (en) * | 2019-03-08 | 2019-06-21 | 北京工业大学 | Total life prediction method based on Short crack propagation under a kind of load of multiaxis luffing |
-
2021
- 2021-08-29 CN CN202110999652.0A patent/CN113866016B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105466772A (en) * | 2015-11-15 | 2016-04-06 | 北京工业大学 | Multiaxial short crack propagation life prediction method based on critical surface method |
| CN108897900A (en) * | 2018-03-24 | 2018-11-27 | 北京工业大学 | A kind of lower PROPAGATION OF FATIGUE SHORT CRACKS life-span prediction method of multiaxis luffing load |
| CN109918789A (en) * | 2019-03-08 | 2019-06-21 | 北京工业大学 | Total life prediction method based on Short crack propagation under a kind of load of multiaxis luffing |
Non-Patent Citations (12)
| Title |
|---|
| "Fatigue life prediction of laser welded 6156 Al-alloy joints based on crack closure";Hu Liu等;《Theoretical and Applied Fracture Mechanics》;全文 * |
| "Life prediction method based on short crack propagation considering additional damage under axial-torsional non-proportional loading";Xue-Peng Zhou等;《International JournalofFatigue》;全文 * |
| "Multiaxial Fatigue Life Prediction Based on Short Crack Propagation Model with Equivalent Strain Parameter";Xiang-Feng Zhao等;《Journal of Materials Engineering and Performance》;全文 * |
| "Physically short crack propagation in metals during high cycle fatigue";C. Santus等;《International Journal of Fatigue》;全文 * |
| "Short crack approach for multiaxial fatigue assessment";Kurzrisskonzept等;《Mat.-wiss. u. Werkstofftech》;全文 * |
| "Short cracks growth in low cycle fatigue under multiaxial in-phase loading";S. Foletti等;《International Journal of Fatigue》;全文 * |
| 一种考虑非比例附加损伤的多轴低周疲劳模型;崔向阳;洪克城;;力学学报(第03期);全文 * |
| 基于临界面法的缺口件多轴疲劳寿命预测;尚德广, 王大康, 李明;机械强度(第02期);全文 * |
| 基于损伤力学-临界面法预估多轴疲劳寿命;刘俭辉;王生楠;黄新春;傅益战;;机械工程学报(第20期);全文 * |
| 基于最大损伤临界平面多轴疲劳寿命预测方法;杨俊;李承彬;谢寿生;;航空动力学报(第12期);全文 * |
| 多轴变幅加载下疲劳裂纹扩展速度的研究;于强;;四川理工学院学报(自然科学版)(第04期);全文 * |
| 多轴非比例加载下疲劳短裂纹扩展速率的探讨;于强;;机械强度(第01期);全文 * |
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