CN108170905A - A kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load - Google Patents
A kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load Download PDFInfo
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Abstract
The invention discloses a kind of life-span prediction methods under nickel base superalloy blade thermal mechanical fatigue load.Efficiently solve low all cyclic fatigue damage of the nickel base superalloy blade under TMF load,The joint of creep impairment and pre-exposure damage characterizes and life prediction problem,According to nickel-base alloy in the isothermal low-cycle fatigue life data for not causing the high-temperature effects such as creep and oxidation,Fitting obtains strain life equation,Fatigue Damage Model is obtained with reference to fatigue damage linear accumulation theory,Creep impairment model is expressed as temperature,Stress and the function of time,Pre-exposure damage is modeled based on crack tip oxide layer lasting oxidation Cracking Mechanism,Continuous damage Accumulation Mechanism is used to above-mentioned three kinds of models,By blade danger position point stress,Strain,Temperature data,So as to fulfill the combined injury model to nickel base superalloy component under thermal mechanical fatigue load,Fatigue,The accurate and reliable Unified Characterization of the damage of creep and oxidation interaction and life prediction.
Description
Technical field
The present invention relates to the life prediction fields of high temperature alloy structural member, more particularly to a kind of to be used for nickel base superalloy leaf
Life-span prediction method under piece thermal mechanical fatigue load.
Background technology
Nickel base superalloy due to characteristics such as its excellent intensity, hardness, toughness, corrosion resistance and high temperature resistants, so as to
By as high-temperature structural material.Nickel-base high-temperature alloy material technology is with technologies such as energy source and power, petrochemical industry, aerospaces
It needs and develops, mainly apply to the product in essential industry field and the high-temperature component of equipment, such as aero-turbine leaf
Piece, the turbine disk and combustion chamber etc..Although nickel base superalloy is there is many good physical-chemical characteristics, for aviation
Engine turbine blade, during service, the effect of thermal mechanical fatigue (TMF) load can bring blade all poly-injuries, specific next
It says, that is, undergos (Fatigue) tired caused by complicated transient-cycle in point state load damage；Higher combustion gas stream temperature can be right
High-temperature component generation time, temperature and the relevant creep of stress (Creep) damage；Corrosive environment such as oxidation environment reduces
Hot-end component surface quality, and poor surface quality has to form the risk in the tired source such as etch pit and micro- hole, may lead
Blade cracks germinating and extension are caused, antifatigue failure performance has an adverse effect to component, thus the environment that oxidized zone comes
(Environment) damage also can not be ignored.Under actual conditions, fatigue damage, creep impairment and environmental damage often interact
Occur, these damages can be with the growth of the active time of nickel base superalloy turbo blade and with linear or nonlinear
Form increases accumulation, and according to the accumulative theory of damage, fracture failure will occur for component when damage reaches material damage critical value.
Experiments have shown that, the nickel-base alloy under thermal mechanical fatigue load is high by testing thermo-mechanical fatigue and isothermal low-cycle fatigue
The fatigue life ratio of warm blade has that the isothermal low cycle fatigue life of temperature upper limit is short, and correlative study also confirms that, thermal mechanical fatigue
The fatigue properties of blade are more complicated than simple constant high temperature condition under load.Thus accurately predict Ni-base Alloy Blades TMF
Service life it is challenging and it is necessary to.In order to predict that thermal mechanical fatigue load acts on the lower high-temperature alloy blades service life, sent out for aviation
Motivation Life Design provides foundation, and people are mainly from both direction, first, the experiment by a large amount of difference TMF conditions
The Thermomechanical Fatigue Life data of respective alloy blade are obtained, but the dispersibility in different TMF experiment condition lower service life reaches
To -5~+10 times, experiment condition is difficult to accurately control, and randomness is larger, and experimental period is long.Another way is to establish phase
The Life Prediction Model answered avoids the higher cost of experiment and longer experimental period, improves the research and development of life prediction efficiency reduction
Period.The development of over half a century is undergone, hundreds of high temperature is proposed for different materials, load type and method
Fatigue life model, there are certain adaptability and limitation for each model.So development can be suitable for nickel-base high-temperature
Alloy vane, and simultaneously it can be considered that fatigue, creep and the research of the interactive life-span prediction method of oxidation seem very must
Will with it is significant, but at present in high-temperature alloy blades life prediction field, the service life about fatigue, creep and oxidation
Model is mostly independent lesions or part Mutual damage model, and specific to nickel-base alloy, these life model applicabilities are not
It is high.It would therefore be highly desirable to develop a kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load, this is right
There is important scientific research meaning and engineering practical value in the development of nickel-base high-temperature alloy material and structural life-time design.
Lot of domestic and foreign scholar and engineer are with regard to the high temperature alloy under thermal mechanical fatigue load or component damage characteristic and tired
Labor life prediction has carried out research and technical transform, it is proposed that over one hundred kind of fatigue damage, creep impairment and oxidative damage characterization mould
Type.Fatigue damage is directed to, common Life Prediction Model includes Masson-Coffin and range of strain stroke based on experience
Point-score etc., SWT and Ostergren models based on energy method etc., the CDM methods based on continuous damage mechanism and based on physics
MMO models of damage mechanisms etc..For creep impairment, since the damage is that time, temperature and stress are relevant, so mainstream
Creep impairment model generally include these three parameters, such as Larson-Miller models, creep model can also be temperature
Function, such as Kachanove models.For environmental damage, if Duquette-Uhlig propositions are based on power transformation under liquid environment
Fatigue Damage Model of electrochemical conditions etc..Some life models are in order to be adaptive to structure feature simultaneously, in life model
Stress concentration and multiaxis effect are considered, has developed the method for processing stress concentration and multiaxis effect：Stress concentration is imitated
Should, there are Neuber methods, critical distance theory, high volume-integration etc.；For multi-axis stress state, it is proposed that critical plane method,
Modified equivalent stress model and energy method etc..Make a general survey of these model theories, it is seen that many damage models all in specific experiment or
It is established under person's load-up condition, the principal element development in service life is also influenced both for some or a part.For Ni-based
High-temperature alloy blades fatigue life prediction, it is necessary first to prepare the material data of life assessment needs, in order to meet low-cycle fatigue
Service life according to blade loading situation, generates low-cycle fatigue, heat fatigue and Thermomechanical Fatigue Life etc., together to Ni-base Alloy Blades
When with reference to blade geometry structure feature consider stress concentration and due to influence of the blade coatings for the service life.For blade heat
Mechanical fatigue life predicts that two methods of generally use are implemented：(1) TMF data are fitted using simple formula, selected
Sluggish energy two models of model are stretched with Masson-Coffin equations, Ostergren；(2) it is established using damage accumulation method
Life model selects suitable model, and carries out appropriate amendment.The advantage of method (1) is that prediction process is very easy, but
Be due to being only conceived to macro-scale, lacking the mechanism study on crystal grain micro-scale, though equation is simple and parameter easily obtains,
But lack physical significance, technical approval degree is not high.Very difficult for method (2) prediction steps, equation expression formula is more multiple
Miscellaneous, material parameter is more, it is cumbersome to the fit procedure of parameter and lack experiment support thus precision it is insufficient so that calculating
To service life accuracy have a greatly reduced quality, and parameter value is not suitable for engineering application across scale.Up to the present, research both at home and abroad
Personnel propose a kind of reliable and have clear and definite physical significance not yet, based on nickel base superalloy blade in thermal mechanical fatigue
Fatigue, creep and oxidation reciprocation life-span prediction method under load.
In view of the above problems, the present invention proposes a kind of service life under nickel base superalloy blade thermal mechanical fatigue load
Forecasting Methodology.This method can consider that leaf structure can guarantee the precision of the prediction result of model again, efficiently solve nickel
Low all cyclic fatigue (LCF) of the based high-temperature alloy blade under TMF load is damaged, creep (Creep) damages and oxidation environment
(Environment) the joint characterization of damage and life prediction problem are not causing creep and oxidation etc. according to nickel-base alloy
The isothermal low-cycle fatigue life data of high-temperature effect, fitting obtain strain life equation, with reference to fatigue damage linear accumulation theory
Fatigue Damage Model is obtained, creep impairment model is expressed as to temperature, stress and the function of time, is aoxidized based on crack tip
Lasting oxidation-the Cracking Mechanism of layer models pre-exposure damage, accumulates machine using continuous damage to above-mentioned three kinds of models
System, by blade danger position point stress, strain, temperature data, so as to fulfill the combined injury model to nickel base superalloy
Component is under thermal mechanical fatigue load, the accurate and reliable Unified Characterization of the damage of fatigue, creep and oxidation interaction and service life
Prediction.
Invention content
The purpose of the present invention is in nickel-base alloy isothermal low cycle fatigue test data, Larson-Miller or Arrhenius
On the basis of constitutive theoryr and oxide layer continued oxidation-Cracking Mechanism, non-linear characterization is played by continuous damage Mechanism establishing
The life-span prediction method of the polynomial form of ability can be realized to low under the conditions of nickel-base alloy structural member thermal mechanical fatigue
Damage under all fatigue, creep and environmental oxidation damage synergy is characterized and is predicted, improves the Ni-base Alloy Blades longevity
Order precision of prediction.
In order to realize the studies above purpose and content, the present invention adopts the following technical scheme that：
A kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load, it is characterised in that：Root
According to nickel-base alloy in the isothermal low-cycle fatigue life data for not causing the high-temperature effects such as creep and oxidation, fitting obtains the strain longevity
Equation is ordered, Fatigue Damage Model is obtained with reference to fatigue damage linear accumulation theory, creep impairment model is expressed as to temperature, answering
The function of power and time model pre-exposure damage based on the lasting oxidation-Cracking Mechanism of crack tip oxide layer,
To above-mentioned three kinds of models using continuous damage Accumulation Mechanism, consider leaf structure, by blade danger position point stress,
Strain, temperature data, so as to fulfill the combined injury model to nickel base superalloy blade under thermal mechanical fatigue load, it is tired
Labor, the accurate and reliable Unified Characterization of creep and the damage under oxidation reciprocation and life prediction, mainly including following step
Suddenly：
Step S1 is not generating the high-temperature effects such as creep and oxidation, that is, is ensureing the low circulation under sufficiently low temperature condition
On the basis of fatigue life data, carry out the fatigue damage modeling under Ni-base Alloy Blades TMF load-up conditions and solve, to tired
Labor lifetime data carries out data fitting (least square method, Newton iteration method etc.) and obtains fatigue life NfatigueEquation, this is tired
Labor life equation can follow Masson-Coffin models or other fatigue at high temperature life models, in order to simplify the present invention only
Using plastic strain amplitude (Δ εmech)-fatigue life (Nfatigue) model, as shown in formula (1), for known blade nickel-base alloy
The fitting of low-cycle fatigue data can obtain material parameter c, d in strain fatigue life model, then accumulated and managed based on linear damage
By by TMF fatigue damages DfatigueIt is expressed as fatigue life NfatigueInverse, as shown in formula (2), obtaining blade dangerous point
Locate plastic strain amplitude Δ εmechAfterwards, substituting into formula (1) and formula (2) can solve to obtain LCF service life NfatigueAnd damage Dfatigue：
Δεmech=c (Nfatigue)d (1)
Dfatigue=1/Nfatigue (2)
In formula (1) and (2), DfatigueRepresent the low-cycle fatigue damage under heat engine fatigue condition；NfatigueRepresent that fatigue is followed
Number of rings, unit are week N；ΔεmechRepresent plastic strain amplitude, unit mm/mm.
Step S2 on the basis of the thermal mechanical fatigue load-up condition identical with step S1, carries out under TMF load-up conditions
Ni-base Alloy Blades creep impairment DcreepThe foundation and solution of model, time, temperature and the relevant nickel-base alloy creep damage of stress
Wound model can combine classical Larson-Miller theories and be provided with parametric form, as shown in formula (3) and formula (4) or base
It is integrated in Arrhenius constitutive theoryrs and to creep impairment in a load cycle, establishes the creep damage under the conditions of TMF
Wound model, as shown in formula (5) and formula (6), the parameter in model can be tested in the case where that can not directly acquire by TMF
Data are fitted to obtain, and are asked obtaining to calculate in substitution formula in the case of maximum stress and maximum temperature at the point of blade danger zone
Solution obtains blade creep impairment Dcreep, it should be noted that temperature is Fahrenheit temperature：
lgtrupture=b0+b1/T+b2x/T+b3x2/T+b4x3/T (5)
In formula (3), formula (4), formula (5) and formula (6), truptureFor creep fracture time, the meaning of symbol is only draws
The stress stretched just generates creep impairment, and unit is the second, s；<σ>For stress sign function, work as σ>When 0,<σ>=σ, works as σ<When 0,<
σ>=0；X is the function about maximum stress σ, is expressed as x=lg σ；T represents maximum temperature, and unit is °F； b0,b1,b2,b3,
b4For material constant；tcFor the time of the cycle of TMF mono-, unit is the second, s.
Step S3, on the basis of the step S1 thermal mechanical fatigue load-up conditions identical with step S2, based on crackle crackle
The lasting oxidation of tip oxide layer and Cracking Mechanism are carried out and consider that the TMF Ni-base Alloy Blades oxidative damages under corrosive environment are built
Mould, as shown in formula (7), which introduces equivalent phase factor ΦenvWith equivalent parabola constantWith
ΦenvPass through phase factor φenvInner product is recycled at one to get, as shown in formula (8), φenvThe phase of the load history of reflection
Position relationship, for characterizing the degree of environmental damage under different TMF, be aboutWith relative damage ξoxFunction, such as formula
(9) shown in,WithThe pure zirconia dynamic behavior of alloy, as shown in formula (10) and formula (11)：
In formula (7), formula (8), formula (9), formula (10) and formula (11), DenvironmentIt is expressed as TMF pre-exposure damages；For strain rate；ΔεmechRepresent plastic strain amplitude, unit mm/mm；R represents gas constant；ΦenvIt is expressed as equivalent phase
Location factor；φenvPhase factor is expressed as, for the OP TMF of Complete Bind,Represent that environmental damage is maximum,
Phase factor φenv=1, for free wxpansion,φenv→ 0, for complete IP TMF,
Environmental damage-fatigue interaction very little, φenv→0；It is expressed as oxide thickness increasing law；It is expressed as sub- table
The increasing law of the γ ' phase stripping section thickness in face；α, b, β, Beff, ξ, hcr, δ0Material parameter is represented as, is characteristic；
DoxFor material parameter, unit is μm2×s；QoxFor material parameter, unit Kg/mol；Dγ′For material parameter, unit Kg/
mol；tcFor the time of the cycle of TMF mono-, unit is the second, s.
Step S4, will be in the model on the basis of the TMF Ni-base Alloy Blades environmental damage models of step S3 foundation
Material constant merger be similar terms Beff, carry out the simplification of Ni-base Alloy Blades model of oxidative, obtaining associated materials
To TMF environmental damages D in the case of parameter and strain rateenvironmentIt is solved：
In formula (12), DenvironmentIt is expressed as TMF pre-exposure damages；For strain rate；ΔεmechRepresent that plasticity should
Variable Amplitude, unit mm/mm；φenvIt is expressed as phase factor；It is expressed as oxide thickness increasing law；It is expressed as
The increasing law of the γ ' phase stripping section thickness of sub-surface；ΔεmechRepresent plastic strain amplitude, unit mm/mm；BeffIt represents
For material parameter similar terms,α, b, β, ξ, hcr, δ0Material parameter is expressed as, (b/ β)+1 should be with environment
Damage evolution law is consistent, can be obtained using TMF fitting experimental datas.
Step S5, step S1 establish TMF load-up conditions under Ni-base Alloy Blades Fatigue Damage Model result of calculation,
Ni-base Alloy Blades creep impairment the model calculation and step S4 or step S5 under the TMF load-up conditions that step S2 is established
Under the conditions of the TMF of foundation on the basis of Ni-base Alloy Blades pre-exposure damage the model calculation, based on continuous damage machine
System carries out the foundation of the damage life equation of Ni-base Alloy Blades fatigue, creep and oxidization combination effect under TMF load-up conditions
It is solved with total damage：
Dtotal=Dfatigue+Dcreep+Denvironment (13)
In formula (13), DtotalIt is expressed as always damaging；DfatigueIt is expressed as fatigue damage；DcreepIt is expressed as creep impairment；
DenvironmentIt is expressed as oxidative damage.
Step S6 always damages D in the TMF that step S5 is calculatedtotalOn the basis of, it is managed according to based on linear cumulative damage
The formula (14) of opinion, the solution for carrying out Ni-base Alloy Blades TMF life models calculate, and can realize that nickel base superalloy blade exists
Damage characterization and the life prediction of fatigue, creep and oxidization combination effect under various TMF load：
In formula (14), DtotalIt is expressed as always damaging；NtotalRepresent period of the vanes under by TMF Cyclic Loads
Number.
Beneficial effects of the present invention：
1. a kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load proposed by the present invention,
Based on sturdy theoretical foundation, modeling process is clear, and model possesses specific physical significance.
2. a kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load proposed by the present invention,
Can take into account nickel-base alloy low-cycle fatigue, the life prediction under high-temerature creep interaction, can particularly consider ring simultaneously
Fatigue life under the damage of border, fully with reference to leaf structure, this method has nickel-base alloy leaf under the conditions of TMF completely
The characterization of low-cycle fatigue, creep and oxidization combination glycation damage and life prediction ability of piece.
3. the present invention has a good application prospect, according to the low cycle fatigue life data of nickel base superalloy blade,
It can be avoided big with fatigue, creep and the oxidization combination working life of nickel-base alloy under all TMF experimental conditions of Accurate Prediction
The experiment of amount repeats and waste, has saved considerable human and material resources and financial resources and time cost, has shortened blade material
Research and development and test period, improve nickel-bass alloy material engineer application and turbo blade safety evaluation efficiency, scientific research value with
And engineering application value is huge.
Description of the drawings
Fig. 1 gives the life-span prediction method flow being used under nickel base superalloy thermal mechanical fatigue load of the present invention
Figure.
Fig. 2 gives DZ125 alloy vane different locations and dominates damage profile figure.
Fig. 3 provides DZ125 nickel-base alloys optical wand strain-life experimental data point and fit correlation at a temperature of 760 DEG C
Figure.
Fig. 4 gives strain-temperature profile at blade inlet edge dangerous point.
Fig. 5 gives stress-temperature profile at blade inlet edge dangerous point.
Fig. 6 gives different ξoxWhen,And φenvGraph of relation.
Fig. 7 gives all TMF data points of DZ125 alloy samples and dispersion train figure.
The TMF life prediction results of fatigue, creep and oxidization combination working life model that Fig. 8 gives.
Specific embodiment
The life-span prediction method stream being used under nickel base superalloy blade thermal mechanical fatigue load provided below using Fig. 1
Journey figure simultaneously in conjunction with the embodiments illustrates the method for the present invention.The present invention is not limited only to following instance, every to utilize the present invention
Mentality of designing all enter protection scope of the present invention within.
Example：DZ125 alloys the damage characterization of fatigue, creep and oxidization combination effect and service life under the conditions of blade TMF
Forecasting Methodology
Step S1 carries out the fatigue damage modeling under Ni-base Alloy Blades TMF load-up conditions and solves.
Δεmech=c (Nfatigue)d (1)
Dfatigue=1/Nfatigue (2)
In formula (1) and (2), DfatigueRepresent the low-cycle fatigue damage under heat engine fatigue condition；NfatigueRepresent that fatigue is followed
Number of rings, unit are week N；ΔεmechRepresent plastic strain amplitude, unit mm/mm.
For certain aero-engine DZ125 directional solidification nickel-base high-temperature alloy blades, low-cycle fatigue experimental data is carried out
Under TMF fatigue damages modeling.It can intuitively find out that damage profile situation is dominated in each region of blade by Fig. 2, wherein LE represents leaf
Piece leading edge, TE represent blade trailing edge, and Hub represents blade wheel hub, and Root represents blade root, and TF represents heat fatigue, and OX represents oxidation,
LCF represents low-cycle fatigue, and TMF represents thermal mechanical fatigue, in order to complete the damage life prediction of DZ125 Ni-base Alloy Blades, choosing
The leading edge locus point for taking temperature and stress all higher is studied.Blade fatigue life is that temperature is relevant, but for the TMF longevity
The prediction of life, fatigue damage should avoid imply the high-temperature effects such as creep and oxidation, thus need using sufficiently low temperature
Under the conditions of low cycle fatigue life result.The main three parts in source of DZ125TMF test datas：(1) Materials Handbook；(2)
The test data that experimenter is done；(3) test data in open source literature under 550-1000 DEG C of temperature range.This example pair
The 760 DEG C of isothermal data experiments provided in 500-1000 DEG C and 400-900 DEG C of TMF load-up condition are only with open source literature, reason
By being：(1) 760 DEG C of isothermal data experiments frequency is sufficiently high, hardly has creep or environmental damage, and the fatigue at 760 DEG C
Service life is better than the strain fatigue life at 700 DEG C, as shown in Figure 3；(2) open source literature is without 400 DEG C or 500 DEG C or lower
Isothermal data under temperature condition.For DZ125,760 DEG C of isothermal fatigue test datas are fitted, are obtained shaped like formula (1)
Life model is strained, obtains material parameter c=0.04073, d=-0.1307, substitutes into formula (1) and (2) and obtains formula (15).Figure
3 give strain-fatigue life model and curved line relation at 760 DEG C, and do with strain-fatigue data at 700 DEG C
Comparison, the results showed that 760 DEG C of low-cycle fatigue lifes performances are more superior.According to strain-temperature curve shown in Fig. 4, strain
Amplitude Δ εmech, temperature range D is damaged with the low Zhou Xunhuan being calculated according to formula (15)fatigueThe results are shown in Table 1.
1 plastic strain amplitude Δ ε of tablemech, temperature range and low Zhou Xunhuan damage Dfatigue
| Plastic strain amplitude Δ εmech(mm/mm) | Temperature range (K) | Dfatigue |
| 0.27% | 800~1323 | 9.61×10-10 |
Step S2 carries out the Ni-base Alloy Blades creep impairment D under TMF load-up conditionscreepThe foundation and solution of model.
On the basis of the thermal mechanical fatigue load-up condition identical with step S1, carry out the Ni-based height under TMF load-up conditions
Temperature alloy creep impairment DcreepThe foundation of model.The creep impairment of material is that time, temperature and stress are relevant, and the present invention carries
The nickel-base alloy creep impairment model of two kinds of functional forms, the i.e. polynomial form of parametric form and nonparametric are gone out.This example
For blade DZ125 alloys, using the model of nonparametric form, i.e. formula (5), convolution (6) carries out DZ125 blade TMF creeps
Modeling for life is damaged, according to Materials Handbook, voluntarily experiment or open source literature, having obtained DZ125 blade TMF creep lives counts
Material parameter needed for calculating, as shown in table 2, obtains formula (16) and formula (17), according to Fig. 5 by parameter substitution formula (5) and formula (6)
Stress-temperature profile at blade inlet edge dangerous point, maximum stress σ and maximum temperature T and substitution formula (17), it is assumed that one
TMF circulation times are tc=1, the creep impairment D being calculatedcreep, as shown in table 3.
lgtrupture=b0+b1/T+b2x/T+b3x2/T+b4x3/T (5)
In formula (5) and formula (6), truptureFor creep fracture time, the meaning of symbol is that the stress only stretched just produces
Raw creep impairment, unit are the second, s；X is the function about maximum stress σ, is expressed as x=lg σ；T represents maximum temperature, unit
For oF；b0,b1,b2,b3,b4For material constant；tcFor the time of the cycle of TMF mono-, unit is the second, s.
Creep life computation model material requested parameter under the conditions of table 2DZ125 blades TMF
| b0 | b1 | b2 | b3 | b4 |
| -22.262 | 92202.77 | -31964.11 | 12467.15 | -2414.596 |
lgtrupture=-22.262+92202.77/T-31964.11lg σ/T+12467.15 (lg σ)2/T-
2414.596·(lgσ)3/T (16)
Table 3 maximum stress σ and maximum temperature T and creep impairment Dcreep
| Maximum stress σ (MPa) | Maximum temperature T (oF) | Dcreep |
| 200 | 1922 | 3.41×10-20 |
Step S3 carries out the TMF nickel-base alloys oxidative damage modeling considered under corrosive environment.
On the basis of the step S1 thermal mechanical fatigue load-up conditions identical with step S2, aoxidized based on crackle crack tip
The lasting oxidation of layer and Cracking Mechanism carry out the TMF nickel-base alloy DZ125 oxidative damages modeling for considering that corrosive environment is brought：
In formula (5), formula (6), formula (7), formula (8) and formula (9), DenvironmentIt is expressed as TMF environmental damages；To answer
Variability；ΔεmechRepresent plastic strain amplitude, unit mm/mm；R represents gas constant；ΦenvBe expressed as equivalent phase because
Son；φenvPhase factor is expressed as, for the OP TMF of Complete Bind,Represent that environmental damage is maximum, phase
Factor φenv=1, for free wxpansion,φenv→ 0, for complete IP TMF,Environment
Damage-fatigue interaction very little, φenv→0；It is expressed as oxide thickness increasing law；It is expressed as sub-surface
The increasing law of γ ' phase stripping section thickness；α, b, β, Beff, ξ, hcr, δ0Material parameter is represented as, is characteristic； DoxFor
Material parameter, unit are μm2×s；QoxFor material parameter, unit Kg/mol；Dγ′For material parameter, unit Kg/mol；tc
For the time of the cycle of TMF mono-, unit is the second, s.Fig. 6 gives different ξoxWhen,And φenvRelationship, can by figure
See, whenWhen generate peak value damage.
Step S4 carries out the simplification of Ni-base Alloy Blades TMF model of oxidative.
On the basis of the TMF nickel-base alloy environmental damage models established in step S3, the material constant in the model is returned
And it is similar terms Beff, carry out the simplification of Ni-base Alloy Blades model of oxidative.Shown in model such as formula (12) after the simplification,
Several parameters are wherein included, in the TMF life searches of the materials such as Mar-M247, GTD-111 and PW1480/1484, all will
β value is set as 1.5, and other parameters refer to Mar-M247, and all parameters are all listed in Table 2 below.It should be noted that for
DZ125 alloys, the exponential term of range of strain should be consistent with environmental damage Evolution in environmental damage, can utilize 500-
It is the OP TMF that 5.3, TMF loaded-up conditions have been constraint that TMF data under the conditions of 1000 DEG C, which are fitted to obtain b/ β+1, it is assumed that one
A TMF circulation times are tc=1, in order to simplify calculate, according to known engine from slow train to intermediate state under temperature at any time
Between data, T (t) is expressed as temperature variation relation linearly over time by this example, i.e. T (t)=22t+300, institute in environmental damage
Some parameter values are referring to table 4, the equivalent phase factor Φ that will be calculated in 4 parameter substitution formula of table (6), (8), (9)env、
Oxide thickness increasing lawThe increasing law of the γ ' phase stripping section thickness of sub-surfaceIt is shown in Table 5, it is known that
Engine is from slow train to intermediate state time about 35s, then strain rateBy table
5 data substitute into formula (12) and substitution DZ125 blade TMF oxidative damages D are calculatedenvironment, equally it is given in Table 5.
In formula (12), DenvironmentIt is expressed as TMF pre-exposure damages；For strain rate；ΔεmechRepresent that plasticity should
Variable Amplitude, unit mm/mm；ΦenvIt is expressed as the equivalent phase factor；It is expressed as oxide thickness increasing law；Table
It is shown as the increasing law of the γ ' phase stripping section thickness of sub-surface；ΔεmechRepresent plastic strain amplitude, unit mm/mm；Beff
Material parameter similar terms are expressed as,α, b, β, ξ, hcr, δ0Material parameter is expressed as, (b/ β)+1 should be with
Environmental damage Evolution is consistent, can be obtained using TMF fitting experimental datas.
4 DZ125 oxidative damage material parameters of table
| Parameter | Numerical value | Unit | Parameter | Numerical value | Unit | Parameter | Numerical value | Unit |
| α | 0.75 | - | Dox | 15400 | μm2×s | Dγ′ | 8570 | μm2×s |
| b | 6.45 | - | Qox | 175.9 | Kg/mol | Qγ′ | 163.3 | Kg/mol |
| β | 1.5 | - | Beff | 1.83E9 | - | ξ | 0.44 | - |
| R | 287 | - | - | - | - | - | - | - |
5 equivalent phase factor Φ of tableenv, oxide thickness increasing lawγ ' phase stripping section the thickness of sub-surface
Increasing lawAnd TMF pre-exposure damages Denvironment
Step S5 carries out the damage equation of Ni-base Alloy Blades fatigue, creep and oxidization combination effect under TMF load-up conditions
Foundation and solution.
Nickel-base alloy Fatigue Damage Model result of calculation, step S2 under the TMF load-up conditions established in step S1 are established
TMF load-up conditions under nickel-base alloy creep impairment the model calculation and the TMF that establishes of step S4 or step S5 under the conditions of
On the basis of nickel-base alloy pre-exposure damage the model calculation, based on continuous damage mechanism, carry out under TMF load-up conditions
The foundation of the damage life equation of nickel-base alloy fatigue, creep and oxidization combination effect：
Dtotal=Dfatigue+Dcreep+Denvironment (13)
In formula (13), DtotalIt is expressed as always damaging；DfatigueIt is expressed as fatigue damage；DcreepIt is expressed as creep impairment；
DenvironmentIt is expressed as oxidative damage.
It is for always damaging for DZ125 alloy vanes：
Dtotal=9.61 × 10-10+3.41×10-20+8.42×10-5≈8.42×10-5 (18)
Step S6, the solution for carrying out the Ni-base Alloy Blades TMF service life calculate.
D is always damaged in the TMF that step S5 is calculatedtotalOn the basis of, according to the formula based on linear cumulative damage law
(14), corresponding service life N is calculatedtotal=11876 weeks.It should be noted that this example only considers an engine from slow
Vehicle-maximum rating TMF cycles, and each circulation time is 1 hour, when the multiple TMF cycles of consideration and considers multiaxis effect
At once, which can also further shorten.
The TMF test datas of DZ125 in this example mostly come from Materials Handbook and related open source literature, Fig. 7 give
Go out on DZ125 alloy longitudinal directions, all TMF lifetime datas of optical wand sample, IP, OP and CD reflect load history respectively
Phase, IP represent same-phase, OP represent antiphase, CD represent diamond shape phase.As seen from Figure 7, different tests condition, service life
Dispersibility reach -5~+10 times, thus develop can be under the conditions of more Accurate Prediction nickel-base alloy difference TMF fatigue,
Creep and oxidative damage Life Prediction Model can save experimental cost, accelerate the research and development of blade nickel-bass alloy material and test
Card process.In order to verify the reasonability of mould life prediction of the invention, table 6 provides the different TMF being calculated with this model
Under the conditions of DZ125 blade fatigues, creep and oxidization combination damage service life, Fig. 8 is calculates using this life-span prediction method
Service life under the conditions of all TMF arrived and from document, handbook and the TMF of experiment service life normalized distributions.It can by Fig. 8
Know：(1) in 52 data points, 47 data fall within 3 times of dispersion trains, wherein 35 data points fall within 2 times of dispersions
Within band；(2) main source of prediction error is in the range of the short life of 500-1000 DEG C of IP TMF, is as a result relatively guarded.
(3) OP TMF life prediction precisions are very high, it should be noted that 500-1000 DEG C of OP TMF has only been used in the acquisition of material parameter
Data but predict the OP TMF data under 400-900 DEG C and 550-1000 DEG C of temperature condition well, this is exactly the present invention's
In place of the advantage of model.(4) it is more than all IP TMF of 100 cycles in the service life, the precision of life prediction is also higher, is worth
It is noted that 500-1000 DEG C does not use TMF data to be fitted material parameter with 550-1000 DEG C of IP TMF life prediction,
Therefore it is the life prediction in complete meaning.Therefore it can be proved that based on Ni-base Alloy Blades, using the service life proposed by the present invention
Prediction model can be with fatigue, creep and the service life of oxidization combination effect under the arbitrary TMF load-up conditions of Accurate Prediction.
The longevity of blade DZ125 fatigues, creep and oxidization combination damage under the conditions of the different TMF that 6 model of table is calculated
Life
Claims (1)
1. a kind of life-span prediction method under nickel base superalloy blade thermal mechanical fatigue load, it is characterised in that：According to
For nickel-base alloy in the isothermal low-cycle fatigue life data for not causing the high-temperature effects such as creep and oxidation, fitting obtains strain service life side
Journey, obtain Fatigue Damage Model with reference to fatigue damage linear accumulation theory, creep impairment model be expressed as to temperature, stress and when
Between function, based on crack tip oxide layer lasting oxidation-Cracking Mechanism pre-exposure damage is modeled, to above-mentioned three
Kind model considers leaf structure, by blade danger position point stress, strain, temperature using continuous damage Accumulation Mechanism
Data, so as to fulfill the combined injury model to nickel base superalloy blade under thermal mechanical fatigue load, fatigue, creep and oxygen
Change accurate and reliable Unified Characterization and the life prediction of the damage under reciprocation, mainly include the following steps that：
Step S1 is not generating the high-temperature effects such as creep and oxidation, that is, is ensureing the low-cycle fatigue under sufficiently low temperature condition
On the basis of lifetime data, carry out the fatigue damage modeling under Ni-base Alloy Blades TMF load-up conditions and solve, to fatigue life
Data carry out data fitting (least square method, Newton iteration method etc.) and obtain fatigue life NfatigueEquation, the fatigue life
Equation can follow Masson-Coffin models or other fatigue at high temperature life models, in order to simplify the present invention only with should
Variable Amplitude (Δ εmech)-fatigue life (Nfatigue) model, as shown in formula (1), for known blade nickel-base alloy low-cycle fatigue
Data fitting can obtain material parameter c, d in strain fatigue life model, then based on linear damage accumulation theory, by TMF
Fatigue damage DfatigueIt is expressed as fatigue life NfatigueInverse, as shown in formula (2), obtaining strain amplitude at blade dangerous point
It is worth Δ εmechAfterwards, substituting into formula (1) and formula (2) can solve to obtain LCF service life NfatigueAnd damage Dfatigue：
Δεmech=c (Nfatigue)d
(1)
Dfatigue=1/Nfatigue
(2)
In formula (1) and (2), DfatigueRepresent the low-cycle fatigue damage under heat engine fatigue condition；NfatigueRepresent fatigue and cyclic
Number, unit are week N；ΔεmechRepresent plastic strain amplitude, unit mm/mm；
Step S2 on the basis of the thermal mechanical fatigue load-up condition identical with step S1, carries out Ni-based under TMF load-up conditions
Alloy vane creep impairment DcreepThe foundation and solution of model, time, temperature and the relevant nickel-base alloy creep impairment mould of stress
Type can combine classical Larson-Miller theories and be provided with parametric form, as shown in formula (3) and formula (4) or be based on
Arrhenius constitutive theoryrs simultaneously integrate creep impairment in a load cycle, establish the creep impairment mould under the conditions of TMF
Type, as shown in formula (5) and formula (6), the parameter in model can be intended in the case where that can not directly acquire by TMF experimental datas
Conjunction obtains, and leaf is obtained obtaining to calculate to solve in substitution formula in the case of maximum stress and maximum temperature at the point of blade danger zone
Piece creep impairment Dcreep, it should be noted that temperature is Fahrenheit temperature：
lgtrupture=b0+b1/T+b2x/T+b3x2/T+b4x3/T
(5)
In formula (3), formula (4), formula (5) and formula (6), truptureFor creep fracture time, the meaning of symbol is answering for only stretching
Power just generates creep impairment, and unit is the second, s；<σ>For stress sign function, as σ ＞ 0,<σ>=σ, as σ ＜ 0,<σ>=
0；X is the function about maximum stress σ, is expressed as x=lg σ；T represents maximum temperature, unit F；b0, b1, b2, b3, b4For material
Expect constant；tcFor the time of the cycle of TMF mono-, unit is the second, s；
Step S3, on the basis of the step S1 thermal mechanical fatigue load-up conditions identical with step S2, based on crackle crack tip
The lasting oxidation of oxide layer and Cracking Mechanism carry out the TMF Ni-base Alloy Blades oxidative damage modeling considered under corrosive environment, such as
Shown in formula (7), which introduces equivalent phase factor ΦenvWith equivalent parabola constantWithΦenvPass through
Phase factor φenvInner product is recycled at one to get, as shown in formula (8), φenvThe phase relation of the load history of reflection is used
Characterize the degree of environmental damage under different TMF, be aboutWith relative damage ξoxFunction, as shown in formula (9),
WithThe pure zirconia dynamic behavior of alloy, as shown in formula (10) and formula (11)：
In formula (7), formula (8), formula (9), formula (10) and formula (11), DenvironmentIt is expressed as TMF pre-exposure damages；To answer
Variability；ΔεmechRepresent plastic strain amplitude, unit mm/mm；R represents gas constant；ΦenvIt is expressed as the equivalent phase factor；
φenvPhase factor is expressed as, for the OP TMF of Complete Bind,Represent that environmental damage is maximum, phase factor
φenv=1, for free wxpansion,φenv→ 0, for complete IP TMF,Environmental damage-
Fatigue interaction very little, φenv→0；It is expressed as oxide thickness increasing law；It is expressed as the γ ' phases of sub-surface
The increasing law of stripping section thickness；α, b, β, Beff, ξ, hcr, δ0Material parameter is represented as, is characteristic；DoxJoin for material
Number, unit are μm2×s；QoxFor material parameter, unit Kg/mol；Dγ′For material parameter, unit Kg/mol；tcFor TMF mono-
The time of a cycle, unit are the second, s；
Step S4, on the basis of the TMF Ni-base Alloy Blades environmental damage models of step S3 foundation, by the material in the model
Constant merger is similar terms Beff, carry out Ni-base Alloy Blades model of oxidative simplification, obtain relevant material parameters and
To TMF environmental damages D in the case of strain rateenvironmentIt is solved：
In formula (12), DenvironmentIt is expressed as TMF pre-exposure damages；For strain rate；ΔεmechRepresent plastic strain width
Value, unit mm/mm；φenvIt is expressed as phase factor；It is expressed as oxide thickness increasing law；It is expressed as sub- table
The increasing law of the γ ' phase stripping section thickness in face；ΔεmechRepresent plastic strain amplitude, unit mm/mm；BeffIt is expressed as material
Expect parameter similar terms,
α, b, β, ξ, hcr, δ0Material parameter is expressed as, (b/ β)+1 should be consistent with environmental damage Evolution, can utilize
TMF fitting experimental datas obtain；
Step S5, Ni-base Alloy Blades Fatigue Damage Model result of calculation, step under the TMF load-up conditions of step S1 foundation
What Ni-base Alloy Blades creep impairment the model calculation and step S4 or step S5 under the TMF load-up conditions that S2 is established were established
Under the conditions of TMF on the basis of Ni-base Alloy Blades pre-exposure damage the model calculation, based on continuous damage mechanism, carry out
The foundation and always damage of the damage life equation of Ni-base Alloy Blades fatigue, creep and oxidization combination effect under TMF load-up conditions
It solves：
Dtotal=Dfatigue+Dcreep+Denvirorment
(13)
In formula (13), DtotalIt is expressed as always damaging；DfatigueIt is expressed as fatigue damage；DcreepIt is expressed as creep impairment；
DenvironmentIt is expressed as oxidative damage；
Step S6 always damages D in the TMF that step S5 is calculatedtotalOn the basis of, according to based on linear cumulative damage law
Formula (14), the solution for carrying out Ni-base Alloy Blades TMF life models calculate, and nickel base superalloy blade can be realized various
Damage characterization and the life prediction of fatigue, creep and oxidization combination effect under TMF load：
In formula (14), DtotalIt is expressed as always damaging；NtotalRepresent periodicity of the vanes under by TMF Cyclic Loads.
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