CN109063238A - A kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms - Google Patents
A kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms Download PDFInfo
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- 238000012360 testing method Methods 0.000 claims abstract description 50
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Abstract
The tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms that the invention discloses a kind of, it is related to multiaxis thermal mechanical fatigue strength theory field, the algorithm steps are as follows: (1) according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue, total damage is accumulated by fatigue damage, creep impairment and oxidative damage and obtained；(2) fatigue damage is calculated；(3) creep impairment is calculated；(4) oxidative damage is calculated；(5) total damage is calculated, the fatigue life under tension-torsion thermomechanically loads is obtained.In order to verify effect of the invention, the resulting prediction result of this method is compared with tension-torsion thermal mechanical fatigue test result.Verification experimental verification the result shows that, the fatigue life of prediction is differed with test result within 2 times of factors.It is therefore proposed that prediction technique can preferably predict the fatigue life under tension-torsion thermomechanically loads.
Description
Technical field
The invention belongs to multiaxis thermal mechanical fatigue strength theory field more particularly to a kind of tension-torsion heat based on damage mechanisms
Mechanical fatigue life prediction technique.
Background technique
Aero-engine, combustion gas turbine, hypersonic speed marginal space aircraft, pressure vessel, nuclear power station, power plant and
The key components and parts of the daily vehicles are often on active service in the case where harsh high-temperature heat engine tool couples loading environment, and these equipment
It is required in terms of safety military service very high.If the accident that is caused by fatigue failure occurs, it will cause personal injury accident and great
Economic loss.In the starting of the above substantial equipment, stopping and other quick operational process, hot end part is held under high temperature alternating temperature
By the reciprocation of multiaxis combined-circulation load, multiaxis thermal mechanical fatigue can be described as.
It is not able to satisfy aviation hair due to using the fatigue strength theory under room temperature or high temperature constant temperature to carry out Intensity Design to it
The requirement of the components such as motivation intensity and Life Design, therefore multiaxis thermal mechanical fatigue can be suitable for there is an urgent need to one kind and loaded
Life-span prediction method, to improve the reliability of aerospace, military industry equipment and other product hot-end component Intensity Designs.
Summary of the invention
Present invention aims at the demands for being directed to multiaxis thermal mechanical fatigue Intensity Design, propose a kind of based on damage mechanisms
Tension-torsion Life Prediction of Thermomechanical Fatigue method.
The technical solution adopted by the present invention is a kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms, this
Steps are as follows for the realization of method:
Step (1): according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue, test specimen is always damaged by fatigue damage, creep
Damage and oxidative damage are accumulated and are obtained, and calculation formula is as follows:
D=Dfat+βDcr+Dox
Wherein, D is that test specimen always damages, DfatFor test specimen fatigue damage, DcrFor test specimen creep impairment, DoxIt aoxidizes and damages for test specimen
Wound, β are along test specimen crystalline substance fracture damage Reliability equivalence factor；
Step (2): calculation testing piece fatigue damage Dfat, calculation formula is as follows:
Wherein, n is recurring number, NfFor cycle to failure；
Cycle to failure NfCalculation formula it is as follows:
Wherein, Δ γmax/ 2 be the maximum shear strain amplitude on critical surface,It minimum and maximum is cut to be adjacent on critical surface
Normal strain range between shear strain point, σ 'fFor fatigue strength coefficient, b is fatigue strength exponent, ε 'fFor tired plasticity system
Number, c are tired plasticity index；
With the strain on test specimen axially angle o plane are as follows:
γθ=(1+v) εx sin(2θ)-γxy cos(2θ)
Wherein, v is Poisson's ratio；
Using plane is critical surface where maximum shear range of strain, angle θc, to determine the fatigue damage on critical surface
Parameter:
1) the maximum shear range of strain Δ γ on critical surface is determinedmax:
Wherein, t is time point, and by minimum and maximum shear strain point corresponding time point, is defined as t1And t2；
2) the normal strain range between adjacent minimum and maximum shear strain point is determined
Step (3): calculation testing piece creep impairment Dcr, calculation formula is as follows:
Wherein, Δ t is the incremental time on i-th section of test specimen, trIt is compacted under i-th section of corresponding temperature of test specimen and permanent stress
Become rupture time；
Creep fracture time trIt is calculated by Manson-Succop (M-S) equation, as follows:
lgtr=b1+b2R+b3x+b4x2+b5x3
Wherein, R=(9T/5+32)+460, T is Celsius temperature,It is held for the creep on i-th section of test specimen
Long stress, b1、b2、b3、b4、b5For material constant；
Creep rupture stressCalculation formula it is as follows:
Wherein, σiFor the axial stress on i-th section of test specimen, τiFor the shear stress on i-th section of test specimen；
Step (4): oxidative damage D is calculatedox, calculation formula is as follows:
Wherein, acFor the critical crack length under i-th section of corresponding temperature of test specimen and stress, a0For test specimen Initial crack length,
Δ a is the crackle increment under i-th section of corresponding temperature of test specimen and stress；
Critical crack length acCalculation formula it is as follows:
Wherein, KICFor the fracture toughness under i-th section of corresponding temperature of test specimen,For i-th section of corresponding equivalent stress of test specimen,
Y is crack shape coefficient；
Crack shape coefficient Y is calculated by following formula:
Wherein, a is the semi-minor axis of Ellipse crack, and c is the semi-major axis of Ellipse crack,It is in Ellipse crack plane
The angle of the ray and semi-major axis that issued by the center of circle；
The calculation formula of crackle increment Delta a is as follows:
Wherein, K, n are crack growth associated materials constant, TrFor room temperature, h is temperature Sensitivity Index；
Step (5): calculation testing piece always damages D, and calculation formula is as follows:
When test specimen, which always damages D, reaches 1, material for test failure, then recurring number n at this time is under tension-torsion thermomechanically loads
Fatigue Life.
The present invention has the advantages that proposing a kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms.
This method is proposed according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue, it is contemplated that different damage mechanisms cause fatigue life
Influence, explicit physical meaning.Moreover, verification experimental verification the result shows that, the life-span prediction method of proposition can preferably be predicted to draw
Turn round the fatigue life under thermomechanical load.In addition, the calculating of fatigue damage, creep impairment and oxidative damage that this method is related to is just
Engineer application is convenient in victory.
Detailed description of the invention
The flow chart for the tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms that Fig. 1 the method for the present invention provides.
Specific embodiment
The present invention is described with reference to the drawings.
By the test of tension-torsion thermal mechanical fatigue, the invention will be further described, and test material is Ni based high-temperature alloy
GH4169。
A kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms, as shown in Figure 1, circular is such as
Under:
Step (1): according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue, total damage is by fatigue damage, creep impairment
It accumulates and obtains with oxidative damage, calculation formula is as follows:
D=Dfat+βDcr+Dox
Wherein, D is total damage, DfatFor fatigue damage, DcrFor creep impairment, DoxFor oxidative damage, β is grain boundary fracture damage
Hurt Reliability equivalence factor；
Step (2): fatigue damage D is calculatedfat, calculation formula is as follows:
Wherein, n is recurring number, NfFor cycle to failure；
Cycle to failure NfCalculation formula it is as follows:
Wherein, Δ γmax/ 2 be the maximum shear strain amplitude on critical surface,It minimum and maximum is cut to be adjacent on critical surface
Normal strain range between shear strain point, σ 'fFor fatigue strength coefficient, b is fatigue strength exponent, ε 'fFor tired plasticity system
Number, c are tired plasticity index；
With the strain on test specimen axially angle o plane are as follows:
γθ=(1+v) εx sin(2θ)-γxy cos(2θ)
Wherein, v is Poisson's ratio；
Using plane is critical surface where maximum shear range of strain, angle θc, to determine the fatigue damage on critical surface
Parameter:
1) the maximum shear range of strain Δ γ on critical surface is determinedmax:
Wherein, t is time point, and by minimum and maximum shear strain point corresponding time point, is defined as t1And t2；
2) the normal strain range between adjacent minimum and maximum shear strain point is determined
Step (3): creep impairment D is calculatedcr, calculation formula is as follows:
Wherein, Δ t is the incremental time on i-th section, trWhen for creep rupture under i-th section of corresponding temperature and permanent stress
Between；
Creep fracture time trIt is calculated by Manson-Succop (M-S) equation, as follows:
lgtr=b1+b2R+b3x+b4x2+b5x3
Wherein, R=(9T/5+32)+460, T is Celsius temperature,It is answered for the creep rupture on i-th section
Power, b1、b2、b3、b4、b5For material constant；
Creep rupture stressCalculation formula it is as follows:
Wherein, σiFor the axial stress on i-th section, τiFor the shear stress on i-th section；
Step (4): oxidative damage D is calculatedox, calculation formula is as follows:
Wherein, acFor the critical crack length under i-th section of corresponding temperature and stress, a0For Initial crack length, Δ a is i-th
Crackle increment under section corresponding temperature and stress；
Critical crack length acCalculation formula it is as follows:
Wherein, KICFor the fracture toughness under i-th section of corresponding temperature,For i-th section of corresponding equivalent stress, Y is crackle
Form factor；
Crack shape coefficient Y is calculated by following formula:
Wherein, a is the semi-minor axis of Ellipse crack, and c is the semi-major axis of Ellipse crack,It is in Ellipse crack plane
The angle of the ray and semi-major axis that issued by the center of circle；
The calculation formula of crackle increment Delta a is as follows:
Wherein, K, n are crack growth associated materials constant, TrFor room temperature, h is temperature Sensitivity Index；
Step (5): calculating total damage D, and calculation formula is as follows:
When total damage reaches 1, material failure, then recurring number n at this time is the fatigue life under tension-torsion thermomechanically loads.
The tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms that the present invention provides a kind of, is related to multiaxis heat engine
Tool fatigue strength theory field, this method step are as follows: (1) total to damage according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue
It is accumulated by fatigue damage, creep impairment and oxidative damage and is obtained；(2) fatigue damage is calculated；(3) creep impairment is calculated；(4) it counts
Calculate oxidative damage；(5) total damage is calculated, the fatigue life under tension-torsion thermomechanically loads is obtained.In order to verify effect of the invention,
The resulting prediction result of this method is compared with tension-torsion thermal mechanical fatigue test result.Verification experimental verification the result shows that, prediction
Fatigue life differed with test result within 2 times of factors.It is therefore proposed that prediction technique can preferably predict tension-torsion heat
Fatigue life under mechanical load.
Claims (1)
1. a kind of tension-torsion Life Prediction of Thermomechanical Fatigue method based on damage mechanisms, it is characterised in that: the realization of this method walks
It is rapid as follows:
Step (1): according to the damage mechanisms under the load of tension-torsion thermal mechanical fatigue, test specimen is always damaged by fatigue damage, creep impairment
It accumulates and obtains with oxidative damage, calculation formula is as follows:
D=Dfat+βDcr+Dox
Wherein, D is that test specimen always damages, DfatFor test specimen fatigue damage, DcrFor test specimen creep impairment, DoxFor test specimen oxidative damage, β
For along test specimen crystalline substance fracture damage Reliability equivalence factor；
Step (2): calculation testing piece fatigue damage Dfat, calculation formula is as follows:
Wherein, n is recurring number, NfFor cycle to failure；
Cycle to failure NfCalculation formula it is as follows:
Wherein, Δ γmax/ 2 be the maximum shear strain amplitude on critical surface,It is answered for minimum and maximum shearing adjacent on critical surface
Normal strain range between height, σ 'fFor fatigue strength coefficient, b is fatigue strength exponent, ε 'fFor tired plastic coefficient, c is
Tired plasticity index；
With the strain on test specimen axially angle o plane are as follows:
γθ=(1+v) εxsin(2θ)-γxycos(2θ)
Wherein, v is Poisson's ratio；
Using plane is critical surface where maximum shear range of strain, angle θc, to determine the fatigue damage parameter on critical surface:
1) the maximum shear range of strain Δ γ on critical surface is determinedmax:
Wherein, t is time point, and by minimum and maximum shear strain point corresponding time point, is defined as t1And t2；
2) the normal strain range between adjacent minimum and maximum shear strain point is determined
Step (3): calculation testing piece creep impairment Dcr, calculation formula is as follows:
Wherein, Δ t is the incremental time on i-th section of test specimen, trIt is disconnected for the creep under i-th section of corresponding temperature of test specimen and permanent stress
Split the time；
Creep fracture time trIt is calculated by Manson-Succop (M-S) equation, as follows:
lgtr=b1+b2R+b3x+b4x2+b5x3
Wherein, R=(9T/5+32)+460, T is Celsius temperature, For the creep rupture stress on i-th section of test specimen,
b1、b2、b3、b4、b5For material constant；
Creep rupture stressCalculation formula it is as follows:
Wherein, σiFor the axial stress on i-th section of test specimen, τiFor the shear stress on i-th section of test specimen；
Step (4): oxidative damage D is calculatedox, calculation formula is as follows:
Wherein, acFor the critical crack length under i-th section of corresponding temperature of test specimen and stress, a0For test specimen Initial crack length, Δ a
For the crackle increment under i-th section of corresponding temperature of test specimen and stress；
Critical crack length acCalculation formula it is as follows:
Wherein, KICFor the fracture toughness under i-th section of corresponding temperature of test specimen,For i-th section of corresponding equivalent stress of test specimen, Y is to split
Line form factor；
Crack shape coefficient Y is calculated by following formula:
Wherein, a is the semi-minor axis of Ellipse crack, and c is the semi-major axis of Ellipse crack,It is in Ellipse crack plane by justifying
The angle of ray and semi-major axis that the heart issues；
The calculation formula of crackle increment Delta a is as follows:
Wherein, K, n are crack growth associated materials constant, TrFor room temperature, h is temperature Sensitivity Index；
Step (5): calculation testing piece always damages D, and calculation formula is as follows:
When test specimen, which always damages D, reaches 1, material for test failure, then recurring number n at this time is the test specimen under tension-torsion thermomechanically loads
Fatigue life.
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Cited By (6)
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| CN109918788A (en) * | 2019-03-08 | 2019-06-21 | 北京工业大学 | A kind of luffing multiaxis Life Prediction of Thermomechanical Fatigue method based on linear damage accumulation |
| CN110220805A (en) * | 2019-06-25 | 2019-09-10 | 北京工业大学 | A kind of luffing multiaxis heat engine Prediction method for fatigue life based on creep fatigue damage accumulation |
| CN110987675A (en) * | 2019-12-23 | 2020-04-10 | 北京工业大学 | Multi-axial-amplitude thermal mechanical fatigue life prediction method based on critical surface damage |
| CN111879636A (en) * | 2020-07-31 | 2020-11-03 | 华东理工大学 | Creep-fatigue-oxidation real-time damage accumulation evaluation method for material |
| CN113109177A (en) * | 2021-03-26 | 2021-07-13 | 北京工业大学 | Based on KfMethod for predicting multi-axis constant-amplitude thermal mechanical fatigue life of notch part |
| CN115017745A (en) * | 2022-08-09 | 2022-09-06 | 天津大学 | Creep fatigue life prediction method and system for thermal power generating unit structural member |
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| CN109918788A (en) * | 2019-03-08 | 2019-06-21 | 北京工业大学 | A kind of luffing multiaxis Life Prediction of Thermomechanical Fatigue method based on linear damage accumulation |
| CN110220805A (en) * | 2019-06-25 | 2019-09-10 | 北京工业大学 | A kind of luffing multiaxis heat engine Prediction method for fatigue life based on creep fatigue damage accumulation |
| CN110220805B (en) * | 2019-06-25 | 2022-06-07 | 北京工业大学 | Variable-amplitude multi-shaft heat engine fatigue life prediction method based on creep fatigue damage accumulation |
| CN110987675A (en) * | 2019-12-23 | 2020-04-10 | 北京工业大学 | Multi-axial-amplitude thermal mechanical fatigue life prediction method based on critical surface damage |
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| CN111879636A (en) * | 2020-07-31 | 2020-11-03 | 华东理工大学 | Creep-fatigue-oxidation real-time damage accumulation evaluation method for material |
| CN113109177A (en) * | 2021-03-26 | 2021-07-13 | 北京工业大学 | Based on KfMethod for predicting multi-axis constant-amplitude thermal mechanical fatigue life of notch part |
| CN113109177B (en) * | 2021-03-26 | 2023-01-03 | 北京工业大学 | Based on K f Method for predicting multi-axis constant-amplitude thermal mechanical fatigue life of notch part |
| CN115017745A (en) * | 2022-08-09 | 2022-09-06 | 天津大学 | Creep fatigue life prediction method and system for thermal power generating unit structural member |
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