CN109211665A - A kind of high-strength aluminum alloy super high cycle fatigue total life prediction method - Google Patents
A kind of high-strength aluminum alloy super high cycle fatigue total life prediction method Download PDFInfo
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- CN109211665A CN109211665A CN201810992009.3A CN201810992009A CN109211665A CN 109211665 A CN109211665 A CN 109211665A CN 201810992009 A CN201810992009 A CN 201810992009A CN 109211665 A CN109211665 A CN 109211665A
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- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000000463 material Substances 0.000 claims abstract description 15
- 230000000977 initiatory effect Effects 0.000 claims description 11
- 208000037656 Respiratory Sounds Diseases 0.000 claims description 7
- 238000009864 tensile test Methods 0.000 claims description 3
- 238000007656 fracture toughness test Methods 0.000 abstract description 6
- 238000012360 testing method Methods 0.000 abstract description 5
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000001186 cumulative effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 235000010210 aluminium Nutrition 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000013210 evaluation model Methods 0.000 description 1
- 238000009661 fatigue test Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
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- 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
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Abstract
The invention discloses a kind of high strength alumin ium alloy super high cycle fatigue total life prediction methods.The present invention obtains high strength alumin ium alloy power resistance strength and fracture toughness by tension test and fracture toughness test；It is theoretical based on tired dislocation cumulative damage theory and crack Propagation, reflection material microstructure parameter is introduced, the super high cycle fatigue life-cycle equation of material, the super high cycle fatigue life-cycle under quantitative assessment high strength alumin ium alloy difference stress amplitude are established.The present invention establishes the super high cycle fatigue life-cycle equation of the microstructural parameters containing high strength alumin ium alloy, the high strength alumin ium alloy super high cycle fatigue life-cycle can be realized by tension test and fracture toughness test.This method avoid the tests of costly, time-consuming super high cycle fatigue, have simple, quick, economic advantages.
Description
Technical field
The invention belongs to non-ferrous metal fields, in particular to a kind of high-strength aluminum alloy super high cycle fatigue total life prediction side
Method.
Background technique
High strength alumin ium alloy has many advantages, such as that high-strength light, corrosion resistance and mouldability are excellent, is widely used as aerospace structure
Component.High strength alumin ium alloy structure bears high-frequency vibration fatigue load when running at high speed, and that bears during long service follows
Ring load can be more than 107Cycle, i.e. super high cycle fatigue.Within the scope of super high cycle fatigue, high strength alumin ium alloy fatigue crack initiation in
The large-sized crystal grain of material internal, and traditional high cycle fatigue crack often germinates in specimen surface.High strength alumin ium alloy Very High Cycle
Fatigue crack initiation mechanism and its influence factor, such as microstructure model, micropore germinating model and surface gap, surface anode oxygen
Change film influence factor etc., is tired area research hot issue in recent years.But the super high cycle fatigue service life of high strength alumin ium alloy is pre-
It surveys, especially total life prediction research has not been reported.High strength alumin ium alloy super high cycle fatigue total life prediction is aerospace structure height
The basis that reliability is on active service.
Currently, the life prediction of high strength alumin ium alloy super high cycle fatigue mainly based on phenomenological S-L equation, lack it is super
High cycle fatigue fatigue crack initiation mechanism, particular without in view of material microstructure parameter, super high cycle fatigue.Cause
This, current evaluation model cannot accurately be used for high strength alumin ium alloy super high cycle fatigue total life prediction.
Summary of the invention
The invention discloses a kind of high strength alumin ium alloy super high cycle fatigue total life prediction methods.The present invention passes through tension test
High strength alumin ium alloy power resistance strength and fracture toughness are obtained with fracture toughness test；Based on tired dislocation cumulative damage theory and fatigue
Crack growth theory introduces reflection material microstructure parameter, establishes the super high cycle fatigue life-cycle equation of material, quantitative assessment
The super high cycle fatigue life-cycle under high strength alumin ium alloy difference stress amplitude.
To solve the above problems, the present invention uses following technological means.
A kind of high-strength aluminum alloy super high cycle fatigue total life prediction method, comprising the following steps:
(1) tensile test at room temperature is carried out to high strength alumin ium alloy, draws the stress strain curve of high strength alumin ium alloy, and bent according to stretching
Line computation goes out the elastic modulus E of room temperature material, tensile strength sigmab, and calculate high strength alumin ium alloy super high cycle fatigue intensity △ σD=σb/
3, it calculates material shear modulus G=E/2 (1+v)；
(2) metallurgical polishing technology is used, high strength alumin ium alloy grain size distribution is observed, counts largest grain size a0；
(3) high strength alumin ium alloy super high cycle fatigue crack initiation life equation:
Wherein, KICFor high strength alumin ium alloy fracture toughness, △ σ is Fatigue Stress Amplitude, △ σDFor Fatigue Stress Amplitude, NiniIt is tired
The labor service life.
Relevant parameter is substituted into formula (a), high strength alumin ium alloy super high cycle fatigue crack initiation life can be calculated；
(4) high strength alumin ium alloy super high cycle fatigue crack propagation life, formula (b) are calculated according to formula (b) are as follows:
Wherein, ai、afRespectively high strength alumin ium alloy crackle critical dimension, fatigue fracture critical dimension；X is crackle expansion
Rate parameter is opened up, for high-strength aluminum alloy, x=3；
(5) the high strength alumin ium alloy super high cycle fatigue life-cycle includes fatigue crack initiation life and crack propagation life, it may be assumed that
Further, high strength alumin ium alloy crackle critical dimension aiIt is calculated by material largest grain size: ai=10a0。
Further, high strength alumin ium alloy fatigue fracture critical dimension afCalculation formula are as follows:
The invention has the benefit that the present invention establishes by tension test and fracture toughness test and contains high strength alumin ium alloy
The super high cycle fatigue life-cycle equation of microstructural parameters, can be realized the high strength alumin ium alloy super high cycle fatigue life-cycle.This method
Costly, time-consuming super high cycle fatigue test is avoided, there are simple, quick, economic advantages.
Specific embodiment
It is carried out below with reference to technical effect of the embodiment to design of the invention, specific structure and generation clear, complete
Ground description, to be completely understood by the purpose of the present invention, feature and effect.Obviously, described embodiment is of the invention one
Section Example, rather than whole embodiments, based on the embodiment of the present invention, those skilled in the art are not paying creativeness
Other embodiments obtained, belong to the scope of protection of the invention under the premise of labour.In addition, what is be previously mentioned in text is all
/ connection relationship is connect, not singly refers to that component directly connects, and referring to can be according to specific implementation situation, by adding or reducing connection
Auxiliary, to form more preferably coupling structure.Each technical characteristic in the invention, under the premise of not conflicting conflict
It can be with combination of interactions.
Embodiment 1
A kind of high strength alumin ium alloy super high cycle fatigue total life prediction method, comprising the following steps:
(1) tensile test at room temperature, loading speed 0.0025s are carried out to high strength alumin ium alloy-1, draw the stretching of high strength alumin ium alloy
Curve, and calculate according to stress strain curve elastic modulus E=70GPa, the tensile strength sigma of room temperature materialb=443MPa, and estimate
High strength alumin ium alloy super high cycle fatigue intensity △ σD=σb/ 3=147.7MPa, calculating material shear modulus G=E/2 (1+v)=
25.9GPa；
(2) according to ASTM E1820-2013 fracture toughness test standard, high strength alumin ium alloy fracture toughness test K is measuredIC=
48MPam1/2；
(3) metallurgical polishing technology is used, high strength alumin ium alloy grain size distribution is observed, counts largest grain size a0=30
μm；
(4) high strength alumin ium alloy super high cycle fatigue crack initiation life equation:
Wherein, △ σ is Fatigue Stress Amplitude, △ σDFor Fatigue Stress Amplitude, NiniFor fatigue life；
(5) high strength alumin ium alloy crackle critical dimension aiIt can be by material grains size estimation: ai=10a0=300 μm；
(6) high strength alumin ium alloy fatigue fracture critical dimension a is calculated by formula (c)f:
(7) it by relevant parameter, substitutes into formula (b), high strength alumin ium alloy super high cycle fatigue crack propagation life can be calculated:
(8) the high strength alumin ium alloy super high cycle fatigue life-cycle includes fatigue crack initiation life and crack propagation life, it may be assumed that
(9) when stress amplitude is 150MPa, Fatigue Life is 4.87 × 107Cycle；When stress amplitude is 160MPa, fatigue
Life-cycle is 1.72 × 106Cycle.
Better embodiment of the invention is illustrated above, but the invention is not limited to the implementation
Example, those skilled in the art can also make various equivalent modifications on the premise of without prejudice to spirit of the invention or replace
It changes, these equivalent variation or replacement are all included in the scope defined by the claims of the present application.
Claims (3)
1. a kind of high-strength aluminum alloy super high cycle fatigue total life prediction method, which comprises the following steps:
(1) tensile test at room temperature is carried out to high strength alumin ium alloy, draws the stress strain curve of high strength alumin ium alloy, and according to stress strain curve meter
Calculate elastic modulus E, the tensile strength sigma of room temperature materialb, and calculate high strength alumin ium alloy super high cycle fatigue intensity △ σD=σb/ 3, meter
It calculates material shear modulus G=E/2 (1+v)；
(2) metallographic processing is carried out to high strength alumin ium alloy, measures the grain size distribution of high strength alumin ium alloy, obtains high strength alumin ium alloy
Largest grain size a0；
(3) high strength alumin ium alloy super high cycle fatigue crack initiation life equation:
Wherein, KICFor high strength alumin ium alloy fracture toughness, △ σ is Fatigue Stress Amplitude, △ σDFor Fatigue Stress Amplitude, NiniFor the tired longevity
Life；
Relevant parameter is substituted into formula (a), high strength alumin ium alloy super high cycle fatigue crack initiation life can be calculated；
(4) high strength alumin ium alloy super high cycle fatigue crack propagation life, formula (b) are calculated according to formula (b) are as follows:
Wherein, ai、afRespectively high strength alumin ium alloy crackle critical dimension, fatigue fracture critical dimension；X is crackle extension speed
Rate parameter, for high-strength aluminum alloy, x=3；
(5) the high strength alumin ium alloy super high cycle fatigue life-cycle includes fatigue crack initiation life and crack propagation life, it may be assumed that
2. a kind of high-strength aluminum alloy super high cycle fatigue total life prediction method according to claim 1, which is characterized in that
High strength alumin ium alloy crackle critical dimension aiIt is calculated by material largest grain size: ai=10a0。
3. a kind of high-strength aluminum alloy super high cycle fatigue total life prediction method according to claim 1, which is characterized in that
High strength alumin ium alloy fatigue fracture critical dimension afCalculation formula are as follows:
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632489A (en) * | 2019-01-16 | 2019-04-16 | 西南交通大学 | A kind of Metal Material Fatigue crack propagation model construction method based on monotonic tension parameter |
| CN110967267A (en) * | 2019-11-25 | 2020-04-07 | 中国民用航空飞行学院 | Test method for judging fatigue crack initiation life |
| CN111044349A (en) * | 2019-12-18 | 2020-04-21 | 佛山科学技术学院 | High-strength steel low-temperature ultrahigh-cycle fatigue life prediction method |
| CN111122357A (en) * | 2019-12-18 | 2020-05-08 | 中国科学院金属研究所 | Method for testing fatigue life of aluminum alloy conductor |
| CN111209677A (en) * | 2020-01-13 | 2020-05-29 | 上海工程技术大学 | Aluminum alloy fatigue life calculation method based on rapid coefficient |
| CN112986123A (en) * | 2021-05-12 | 2021-06-18 | 中国航发北京航空材料研究院 | Method for judging aluminum alloy environment induced corrosion cracking tendency |
-
2018
- 2018-08-27 CN CN201810992009.3A patent/CN109211665B/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109632489A (en) * | 2019-01-16 | 2019-04-16 | 西南交通大学 | A kind of Metal Material Fatigue crack propagation model construction method based on monotonic tension parameter |
| CN109632489B (en) * | 2019-01-16 | 2021-04-09 | 西南交通大学 | Metal material fatigue crack propagation model construction method based on monotonic stretching parameters |
| CN110967267A (en) * | 2019-11-25 | 2020-04-07 | 中国民用航空飞行学院 | Test method for judging fatigue crack initiation life |
| CN111044349A (en) * | 2019-12-18 | 2020-04-21 | 佛山科学技术学院 | High-strength steel low-temperature ultrahigh-cycle fatigue life prediction method |
| CN111122357A (en) * | 2019-12-18 | 2020-05-08 | 中国科学院金属研究所 | Method for testing fatigue life of aluminum alloy conductor |
| CN111044349B (en) * | 2019-12-18 | 2022-04-26 | 佛山科学技术学院 | High-strength steel low-temperature ultrahigh-cycle fatigue life prediction method |
| CN111209677A (en) * | 2020-01-13 | 2020-05-29 | 上海工程技术大学 | Aluminum alloy fatigue life calculation method based on rapid coefficient |
| CN111209677B (en) * | 2020-01-13 | 2022-03-25 | 上海工程技术大学 | Aluminum alloy fatigue life calculation method based on rapid coefficient |
| CN112986123A (en) * | 2021-05-12 | 2021-06-18 | 中国航发北京航空材料研究院 | Method for judging aluminum alloy environment induced corrosion cracking tendency |
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