CN110006747A - A kind of titanium alloy fatigue crack growth rate prediction technique - Google Patents
A kind of titanium alloy fatigue crack growth rate prediction technique Download PDFInfo
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- G—PHYSICS
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- 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
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- 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
- G01N2203/006—Crack, flaws, fracture or rupture
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- G01N2203/0066—Propagation of crack
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- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
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Abstract
The invention discloses a kind of titanium alloy fatigue crack growth rate prediction techniques, by determining model Elastic Modulus, tensile strength, yield strength, the contraction percentage of area and plane strain fracture toughness to titanium alloy progress tension test and fracture toughness test, then it determines to proof stress than relevant parameter, establishes titanium alloy fatigue crack growth rate prediction model；Utilize prediction model predicted titanium alloy fatigue crack growth rate.Prediction technique of the present invention, which is realized, to be predicted based on tension test and fracture toughness test result come Crack Propagation Rate, to solve the problems, such as that period in the presence of traditional crack growth rate test measurement is long, providing a solution costly, influence factor more, and works for the selection of titanium alloy engineer application and a kind of modeling tool of qualitative analysis is provided.
Description
Technical field
The invention belongs to the structures of titanium alloy and performance technologies field, and in particular to a kind of titanium alloy crack Propagation speed
Rate prediction technique.
Background technique
Titanium or titanium alloy has the characteristics that the weldability that intensity is high, density is small, corrosion-resistant and excellent, thus navigates in aviation
It, the fields such as health care, automobile, ship, the energy have increasingly extensive application prospect, with aerospace vehicle high speed and
Enlargement, such as the manufacture of the load frame of aircraft, beam, landing gear components and fastener require titanium alloy to have high temperature, Gao Qiangren
And damage tolerance performance.Requirement to titanium alloy performance changes with the design concept of aircraft designers and is changed.Aerospace component
By ancient simple Static Strength Design conceptual change to safety-Life Design concept, breakage-safety design concept, Zhi Daoxian
The damage tolerance design criterion in generation.To guarantee that projected life and damage tolerance, the material of aircraft structure must have good
Fracture toughness and resistance to crack extension performance.As the structural material of space shuttle key, titanium alloy also gradually to high-fracture toughness,
The high-damage tolerance type direction of low crack growth rate is developed.
The principal mode of structure or component failure is fatigue failure, therefore, to fatigue of materials crack propagation macroscopic law
Research has very big engineering value, not only accurately can predict and estimate the fatigue life of component, avoids losing due to fatigue
Effect and caused by heavy losses, foundation can be provided with optimization processing technology and for selection.The crack Propagation of material is divided into
Three phases, the germinating of crackle, crack propagation and final fracture, fatigue of materials crack propagation da/dN~Δ K curve is to material
Carry out the important evidence of fatigue life prediction and damage tolerance performance research, and crack Propagation grinding by decades
Study carefully, to da/dN~Δ K curve progress quantitatively characterizing formula there are many kind, is respectively suitable for each of crack Propagation
Commonly mainly there are Paris formula, Forman formula and Zheng-Hirt formula etc. in stage, these formula are all only limitted to fatigue
The moment of crack propagation, and the measurement period of fatigue of materials crack spreading zone is long, at high cost, especially fatigue crack
Threshold value must measure an even more very long laborious process, so, in order to reduce experimentation cost, facilitate that engineers and technicians' is fast
Speed uses, and urgent need establishes one kind can be with the model of predicted titanium alloy fatigue crack growth rate.
Summary of the invention
In view of the above-mentioned deficiencies in the prior art, the technical problem to be solved by the present invention is that it is tired to provide a kind of titanium alloy
Labor crack growth rate prediction technique carries out quantitatively characterizing to the Fatigue Cracks Propagation of titanium alloy.
The invention adopts the following technical scheme:
A kind of titanium alloy fatigue crack growth rate prediction technique, which is characterized in that by carrying out stretching examination to titanium alloy
It tests and determines model Elastic Modulus, tensile strength, yield strength, the contraction percentage of area and plane strain fracture with fracture toughness test
Then toughness determines to proof stress than relevant parameter, establishes titanium alloy fatigue crack growth rate prediction model；Using pre-
Survey model prediction titanium alloy fatigue crack growth rate.
Specifically, titanium alloy fatigue crack growth rate prediction model is as follows:
Wherein, a is crack length, and D is material constant relevant to stress ratio, and E is elasticity modulus, σbFor tensile strength,
σ0.2For yield strength, A is fracture ductility, and Z is the contraction percentage of area, KCFor plane strain fracture toughness, R is stress ratio.
Further, elastic modulus E specifically: tensile test at room temperature is carried out to material, according to stress strain curve stretch section
Slope determines elastic modulus E.
Further, tensile strength sigmabSpecifically: tensile test at room temperature is carried out to material, maximum when being broken according to material
Stress determines tensile strength sigmab。
Further, yield strength σ0.2Specifically: tensile test at room temperature is carried out to material, is taken on stress strain curve 0.2% residual
Stress value when remaining deformation determines yield strength σ0.2。
Further, contraction percentage of area Z specifically: the diameter of bar samples is measured before tension test, calculator is transversal
Area measures the diameter of fracture position, calculates post-rift cross-sectional area after fracture, before post-rift cross-sectional area and fracture
Cross-sectional area is compared, and the contraction percentage of area Z of sample is obtained.
Further, plane strain fracture toughness KCSpecifically: CT sample is used, fracture toughness test is carried out and determines that face is answered
Become fracture toughness KC。
Further, material constant D relevant to stress ratio specifically:
When being oriented to L-T, when stress ratio is 0.1, constant D is 2.481；When stress ratio is 0.5, constant D is 3.858；
When being oriented to T-L, when stress ratio is 0.1, constant D is 4.367；When stress ratio is 0.5, constant D is 4.899；.
Further, when R=0, threshold in fatigue crack propagation Δ KthoIt estimates as follows:
Wherein, σysFor the yield strength of material, α is material constant, for metal material, α=0.05~0.1；μ is Poisson
Than σ-1For fatigue limit；
When R ≠ 0, threshold value Δ KthIt calculates as follows:
Specifically, titanium alloy is alpha+beta series titanium alloy.
Compared with prior art, the present invention at least has the advantages that
A kind of titanium alloy fatigue crack growth rate prediction technique of the present invention, can be based on simple tension test and fracture
Toughness test is carried out Crack Propagation Rate and is predicted, testing expenses are reduced, and saves the time.
Further, setting titanium alloy fatigue crack growth rate prediction model can be in a short time more accurately to titanium
The fatigue crack growth rate of alloy provides qualitative description, provides foundation for selection.
Further, constant relevant to stress ratio is set by D in a model, simplifies model, enriched related ginseng
The physical significance of amount.
Crackle is expanded in conclusion prediction technique of the present invention is realized based on tension test and fracture toughness test result
Exhibition rate predicted, to solve, period in the presence of traditional crack growth rate test measurement is long, costly, influence factor
More problems provides a solution, and provides a kind of model of qualitative analysis for the selection of titanium alloy engineer application work
Tool.
Below by drawings and examples, technical scheme of the present invention will be described in further detail.
Detailed description of the invention
Fig. 1 is a kind of prediction model figure；
Fig. 2 is the corresponding test data figure of the first prediction model；
Fig. 3 is second of prediction model figure；
Fig. 4 is the corresponding test data figure of second of prediction model.
Specific embodiment
A kind of titanium alloy fatigue crack growth rate prediction technique of the present invention, by carrying out tension test to titanium alloy and breaking
It splits toughness test and determines model Elastic Modulus, tensile strength, yield strength, the contraction percentage of area and plane strain fracture toughness,
It determines to proof stress than relevant parameter, establishes titanium alloy fatigue crack growth rate prediction model；Using prediction model to α
The prediction of+β series titanium alloy fatigue crack growth rate.
Titanium alloy fatigue crack growth rate prediction model is as follows:
Wherein, D is material constant relevant to stress ratio, and being shown in Table 1, E is elasticity modulus, σbFor tensile strength, σ0.2It is in the wrong
Intensity is taken, A is fracture ductility, and Z is the contraction percentage of area, KCFor plane strain fracture toughness.
The occurrence of 1 parameter D of table
Fracture toughness test according to ASTM E399 " metal material linear elasticity plane strain fracture toughness test method " into
Row, tension test are carried out according to 228 metal material tensile testing at ambient temperature of GB/T.
It is suitable for steel material and aluminum alloy materials gamut fatigue crack growth rate according to what pertinent literature proposed
Characterization model:
Wherein, KICFor material fracture toughness, KmaxFor material crack extension stress intensity factor maximum value, Δ K is that stress is strong
Spend the factor, Δ KthFor crack growth threshold,For material crack spreading rate, a is crack length, and F is that crackle enters fastly
(K when fast expansion areamax/KC) value show F=in the fatigue crack propagation test of a large amount of steel alloys and aluminium alloy
0.45, but do not there is a large amount of experimental study to show that F is since the crack propagation research work development time is shorter in titanium alloy
No is a determining amount, then using F as a variable.
After deforming to formula 1, as shown in formula 2, D is unknown quantity relevant to F in formula.
It is characterized to the fatigue crack growth rate of the gamut to material, threshold value Δ KthIt is one essential
Amount, E and K in formula 2, in parameterICIt can be measured by simply testing, and threshold value Δ KthTest be one very
Complicated process, needs to expend a large amount of human and material resources and financial resources, therefore, estimates gamut crack growth rate, main
If the estimation of threshold value, thus select a suitable model come On Crack Propagation threshold value estimate it is particularly significant.
As R ≠ 0:
In formula, Δ KthoThreshold in fatigue crack propagation when for R=0, can be estimated by following formula:
Wherein, σysFor the yield strength of material, α is material constant, for metal material, α=0.05~0.1；μ is Poisson
Than σ-1It for fatigue limit, can be obtained by following formula, in conjunction with formula 2-4, titanium alloy gamut fatigue crack growth rate can be obtained:
Wherein, D is material constant relevant to stress ratio, and E is elasticity modulus, σbFor tensile strength, σ0.2It is strong to surrender
Degree, A is fracture ductility, and Z is the contraction percentage of area, KCFor plane strain fracture toughness, R is stress ratio, and minimum stress is answered with maximum
The ratio of power.
Wherein, tensile test at room temperature is carried out to material, elastic modulus E is determined according to the slope of stress strain curve stretch section.It is right
Material carries out tensile test at room temperature, and maximum stress when being broken according to material determines tensile strength sigmab.Room temperature drawing is carried out to material
Test is stretched, stress value when 0.2% residual deformation on stress strain curve is taken to determine yield strength σ0.2.The measuring stick before tension test
The diameter of shape sample, calculator cross-sectional area measure the diameter of fracture position, calculate post-rift cross-sectional area after fracture, break
Cross-sectional area after splitting obtains the contraction percentage of area Z of sample compared with the cross-sectional area before fracture.Using CT sample, break
It splits toughness test and determines face strain fracture toughness KC。
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.The present invention being described and shown in usually here in attached drawing is real
The component for applying example can be arranged and be designed by a variety of different configurations.Therefore, below to the present invention provided in the accompanying drawings
The detailed description of embodiment be not intended to limit the range of claimed invention, but be merely representative of of the invention selected
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are obtained without creative efforts
The every other embodiment obtained, shall fall within the protection scope of the present invention.
Embodiment
Certain titanium alloy forging blank is taken, feeding respectively is orientated by T-L and L-T and is processed into pole tensile sample and CT sample；
Tension test and fracture toughness test are carried out according to ASTM A370 standard and ASTM E399 standard on testing machine,
The numerical value of relevant parameter in model is obtained, as shown in table 2:
2 titanium alloy room-temperature mechanical property of table
The numerical value of table 2 is brought into prediction model, then has obtained the titanium alloy fatigue crack in T-L and L-T orientation
Da/dN~Δ K expression in spreading rate prediction model；
The gamut Fatigue Crack Propagation Curve that the model can be drawn to titanium alloy in a coordinate system by software, such as schemes
Shown in 1 curve into Fig. 4.The fatigue crack growth rate of the titanium alloy can be predicted by the curve；
In order to verify the accuracy of the model, the CT of titanium alloy forging blank processing fatigue crack growth rate is reused
Sample carries out the measurement test of the fatigue crack growth rate curve of titanium alloy, a system has been obtained after Correlation method for data processing
The expansion curve that test data point and prediction model are drawn is placed in the same coordinate system by the data point of the crack Propagation of column
In, as shown in Figure 1, as can be seen from the figure data point and curve coincide very much, and to nearly Threshold Region, stablize expansion area and quickly
Expansion area suffers from good description, titanium alloy can be predicted well in fatigue crack growth rate.
The above content is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme each falls within claims of the present invention
Protection scope within.
Claims (10)
1. a kind of titanium alloy fatigue crack growth rate prediction technique, which is characterized in that by carrying out tension test to titanium alloy
Determine that model Elastic Modulus, tensile strength, yield strength, the contraction percentage of area and plane strain fracture are tough with fracture toughness test
Property, it then determines to proof stress than relevant parameter, establishes titanium alloy fatigue crack growth rate prediction model；Utilize prediction
Model prediction titanium alloy fatigue crack growth rate.
2. titanium alloy fatigue crack growth rate prediction technique according to claim 1, which is characterized in that titanium alloy fatigue
Crack growth rate prediction model is as follows:
Wherein, D is material constant relevant to stress ratio, and E is elasticity modulus, σbFor tensile strength, σ0.2For yield strength, A is
Fracture ductility, Z are the contraction percentage of area, KCFor plane strain fracture toughness, R is stress ratio.
3. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that elastic modulus E
Specifically: tensile test at room temperature is carried out to material, elastic modulus E is determined according to the slope of stress strain curve stretch section.
4. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that tensile strength sigmab
Specifically: tensile test at room temperature is carried out to material, maximum stress when being broken according to material determines tensile strength sigmab。
5. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that yield strength
σ0.2Specifically: tensile test at room temperature is carried out to material, stress value when 0.2% residual deformation on stress strain curve is taken to determine surrender
Intensity σ0.2。
6. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that the contraction percentage of area
Z specifically: the diameter of bar samples is measured before tension test, calculator cross-sectional area measures the straight of fracture position after fracture
Diameter calculates post-rift cross-sectional area, and post-rift cross-sectional area obtains the section of sample compared with the cross-sectional area before fracture
Shrinking percentage Z.
7. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that plane strain is disconnected
Split toughness KCSpecifically: CT sample is used, fracture toughness test is carried out and determines face strain fracture toughness KC。
8. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that with stress ratio phase
The material constant D of pass specifically:
When being oriented to L-T, when stress ratio is 0.1, constant D is 2.481；When stress ratio is 0.5, constant D is 3.858；
When being oriented to T-L, when stress ratio is 0.1, constant D is 4.367；When stress ratio is 0.5, constant D is 4.899；.
9. titanium alloy fatigue crack growth rate prediction technique according to claim 2, which is characterized in that tired when R=0
Labor crack growth threshold Δ KthoIt estimates as follows:
Wherein, σysFor the yield strength of material, α is material constant, for metal material, α=0.05~0.1；μ is Poisson's ratio,
σ-1For fatigue limit；
When R ≠ 0, threshold value Δ KthIt calculates as follows:
10. titanium alloy fatigue crack growth rate prediction technique according to claim 1, which is characterized in that titanium alloy α
+ β series titanium alloy.
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Cited By (6)
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| CN110411833A (en) * | 2019-08-12 | 2019-11-05 | 武汉钢铁有限公司 | Different frequency crack growth rate prediction technique under a kind of corrosive environment of sea water |
| CN110849753A (en) * | 2019-12-09 | 2020-02-28 | 大连理工大学 | Metal material fatigue strength prediction method based on micro scratches |
| CN111855446A (en) * | 2020-07-14 | 2020-10-30 | 天津钢管制造有限公司 | Prediction method of fatigue limit of titanium alloy |
| CN113033010A (en) * | 2021-03-30 | 2021-06-25 | 中国工程物理研究院研究生院 | Crack propagation rate model for small cracks and method for performing crack propagation rate modeling on titanium alloy material |
| CN114279842A (en) * | 2021-12-27 | 2022-04-05 | 中国科学院武汉岩土力学研究所 | Method and system for determining rock crack initiation stress and damage stress |
| CN114974472A (en) * | 2022-05-16 | 2022-08-30 | 江苏省特种设备安全监督检验研究院 | TA2 industrial pure titanium welding joint mechanical property prediction method based on pre-stretching amount |
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| CN113033010A (en) * | 2021-03-30 | 2021-06-25 | 中国工程物理研究院研究生院 | Crack propagation rate model for small cracks and method for performing crack propagation rate modeling on titanium alloy material |
| CN113033010B (en) * | 2021-03-30 | 2022-07-01 | 中国工程物理研究院研究生院 | Crack propagation rate model for small cracks and method for performing crack propagation rate modeling on titanium alloy material |
| CN114279842A (en) * | 2021-12-27 | 2022-04-05 | 中国科学院武汉岩土力学研究所 | Method and system for determining rock crack initiation stress and damage stress |
| CN114279842B (en) * | 2021-12-27 | 2023-07-14 | 中国科学院武汉岩土力学研究所 | Method and system for determining cracking stress and damage stress of rock cracks |
| CN114974472A (en) * | 2022-05-16 | 2022-08-30 | 江苏省特种设备安全监督检验研究院 | TA2 industrial pure titanium welding joint mechanical property prediction method based on pre-stretching amount |
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