CN109408900A - Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method - Google Patents
Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method Download PDFInfo
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- CN109408900A CN109408900A CN201811147466.9A CN201811147466A CN109408900A CN 109408900 A CN109408900 A CN 109408900A CN 201811147466 A CN201811147466 A CN 201811147466A CN 109408900 A CN109408900 A CN 109408900A
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Abstract
The disclosure provides a kind of Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method, this method comprises: establishing the fretting fatigue contact analysis model of Crystal Nickel-based Superalloy turbo blade tenon；The model is calculated under given operating condition, obtains analysis parameter, analysis parameter includes resolving shear stress, tangential stress and the Relative sliding distance at contact surface different location；Determine the resolving shear stress damage factor under given operating condition at the model contact surface different location；According to given operating condition and analysis parameter, the accumulative dissipated energy damage factor under given operating condition at the model contact surface different location is determined；According to resolving shear stress damage factor and accumulative dissipated energy damage factor, the fretting fatigue complex damage factor is determined, and then obtain the fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon.The Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method of the disclosure can Accurate Prediction Crystal Nickel-based Superalloy turbo blade tenon the fretting fatigue service life.
Description
Technical field
This disclosure relates to structure design and intensity technique field, in particular to a kind of Crystal Nickel-based Superalloy turbo blade
Tenon fretting fatigue life-span prediction method.
Background technique
Crystal Nickel-based Superalloy has good high temperature resistant, creep resistant, anti-oxidant and thermal mechanical fatigue performance, thus extensive
Applied in aero-engine and turbine blade of gas turbine.Turbo blade generallys use tenon connecting structure and connect with the turbine disk,
Under the action ofs periodical centrifugal load etc., fretting fatigue easily occurs for turbo blade tenon structure, and turbine high temperature, high revolving speed
Adverse circumstances make the fretting fatigue problem of nickel-based monocrystal tenon structure more prominent.Therefore, nickel-based monocrystal turbine leaf is realized
The Accurate Prediction in piece tenon fretting fatigue service life, is of great significance for the design of aero-engine and gas turbine.
The fretting fatigue life-span prediction method of traditional Conventional alloys is examined mainly according to wear law and fatigue damage feature
The many factors such as contact stress, surface state, Relative sliding, loaded-up condition are considered to the affecting laws of fretting fatigue, propose description
The comprehensive parameters of fretting damage realize crack initiation by the relationship established between fretting damage parameter and fretting fatigue service life
The prediction of position and fretting fatigue service life.In view of contact area is in multi-axis stress state, based on the micro- of non-proportional loading theory
Dynamic Prediction method for fatigue life is widely applied.
Compared with conventional polycrystalline material, the mechanical behavior of Crystal Nickel-based Superalloy has Lens epithelia, crystal orientation
The features such as sensibility, tension and compression asymmetry, anti-Schmidt's effect and medium temperature brittleness.Current fretting fatigue life-span prediction method without
Method characterizes the characteristics of nickel-base high-temperature single crystal alloy Fretting Fatigue Damage failure, and then leads to not Accurate Prediction Crystal Nickel-based Superalloy
The turbo blade tenon fretting fatigue service life.
It should be noted that information is only used for reinforcing the reason to the background of the disclosure disclosed in above-mentioned background technology part
Solution, therefore may include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
A kind of fretting fatigue life prediction side for being designed to provide Crystal Nickel-based Superalloy turbo blade tenon of the disclosure
Method can Accurate Prediction Crystal Nickel-based Superalloy turbo blade tenon the fretting fatigue service life.
According to one aspect of the disclosure, a kind of Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life prediction is provided
Method, comprising:
Establish Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue contact analysis model；
The turbo blade tenon fretting fatigue contact analysis model is calculated under given operating condition, obtains analysis ginseng
Number, the analysis parameter include resolving shear stress, tangential stress and the Relative sliding distance at contact surface different location；
According to given operating condition and the analysis parameter, determine that fretting fatigue contact analysis model contacts under the given operating condition
Resolving shear stress damage factor at the different location of face；
According to given operating condition and the analysis parameter, determine that the fretting fatigue contact analysis model under the given operating condition connects
Accumulative dissipated energy damage factor at contacting surface different location；
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, fretting fatigue complex damage is determined
The factor, and then obtain the fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon.
In a kind of exemplary embodiment of the disclosure, according to given operating condition and the analysis parameter, determine described given
Resolving shear stress damage factor under operating condition at fretting fatigue contact analysis model contact surface different location includes:
Resolving shear stress damage factor is determined according to the yield strength of resolving shear stress and material.
In a kind of exemplary embodiment of the disclosure, resolving shear stress, first formula are determined by the first formula are as follows:
τ(α)=σ: P(α)
Wherein, τ(α)For resolving shear stress, σ is the stress tensor under crystallographic axis system, P(α)For Schmidt's factor.
In a kind of exemplary embodiment of the disclosure, described determined according to the yield strength of resolving shear stress and material is cut
The stress damage factor, wherein resolving shear stress damage factor, second formula are determined by the second formula are as follows:
Wherein, DRFor resolving shear stress damage factor, τ(α)For the resolving shear stress of slip system α, τminAnd τmaxRespectively τ(α)'s
Minimum value and maximum value, σsFor the yield strength of material, m is the Damage coefficient of material.
In a kind of exemplary embodiment of the disclosure, according to given operating condition and the analysis parameter, determine described given
The accumulative dissipated energy damage factor at fretting fatigue contact analysis model contact surface different location under operating condition includes:
The Dissipated energy at a little is determined according to tangential stress and Relative sliding distance；
Accumulative dissipated energy damage factor is determined according to the Dissipated energy and energy release rate.
It is described to be determined a bit according to tangential stress and Relative sliding distance in a kind of exemplary embodiment of the disclosure
The Dissipated energy at place can determine Dissipated energy, the third formula according to third formula are as follows:
Edi=qi(x)δi(x)
Wherein, EdiFor the Dissipated energy at point x, qiIt (x) is the tangential stress at x point, δiIt (x) is the Relative sliding at x point
Distance.
It is described that accumulation is determined according to the Dissipated energy and energy release rate in a kind of exemplary embodiment of the disclosure
Dissipated energy damage factor can determine accumulative dissipated energy damage factor, the 4th formula according to the 4th formula are as follows:
Wherein, DEFor accumulative dissipated energy damage factor, G is the energy release rate of material, EdiFor the Dissipated energy at point x.
In a kind of exemplary embodiment of the disclosure, according to the resolving shear stress damage factor and the accumulative dissipated energy
Damage factor determines the fretting fatigue complex damage factor, and then obtains the fretting fatigue of Crystal Nickel-based Superalloy turbo blade tenon
Service life includes:
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, the fretting fatigue contact is determined
The fretting fatigue complex damage factor of the analysis model under the given operating condition；
The fretting fatigue longevity of Crystal Nickel-based Superalloy turbo blade tenon is determined according to the fretting fatigue complex damage factor
Life.
In a kind of exemplary embodiment of the disclosure, according to the resolving shear stress damage factor and the accumulative dissipated energy
Damage factor determines fretting fatigue complex damage of the fretting fatigue contact analysis model under the given operating condition because of attached bag
It includes:
Determine that fretting fatigue is comprehensive by the 5th formula according to resolving shear stress damage factor and accumulative dissipated energy damage factor
Damage factor, the 5th formula are as follows:
RA=a1DR 2+a2DE(DE-a3DR)
Wherein, RA is the fretting fatigue complex damage factor, DRFor resolving shear stress damage factor, DEFor accumulative dissipated energy damage
The factor, ai(i=1,2,3) (ai> 0) it is the parameter determining based on fretting fatigue testing fitting.
In a kind of exemplary embodiment of the disclosure, nickel-based monocrystal is determined according to the fretting fatigue complex damage factor
The fretting fatigue service life of alloy turbine blade tenon includes:
Fretting fatigue service life, the 6th formula are determined by the 6th formula are as follows:
RA=A+blnN
Wherein, N is the fretting fatigue service life, and RA is the fretting fatigue complex damage factor, and A, b are experiment parameter, can be by most
Small square law, which calculates, to be determined.
The fretting fatigue life-span prediction method of the Crystal Nickel-based Superalloy turbo blade tenon of the disclosure, it is contemplated that contact surface is answered
The influence of power state and fretting wear to Fretting Fatigue Damage proposes the Crystal Nickel-based Superalloy fretting fatigue complex damage factor,
And then predicted fatigue life.In the process, since the mechanical property of Crystal Nickel-based Superalloy and crystal orientation are closely related, and divide
Shearing stress can reflect the damage characteristic that translation gliding easily occurs under fretting fatigue state for Crystal Nickel-based Superalloy, thus cutting is answered
Power damage factor can characterize Fretting Fatigue Damage；Meanwhile accumulative dissipated energy damage factor and fretting wear are closely related.Therefore same
When consider the influence to Fretting Fatigue Damage of crystal orientation and fretting wear, the accuracy of fretting fatigue life prediction can be improved.
It should be understood that above general description and following detailed description be only it is exemplary and explanatory, not
The disclosure can be limited.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows the implementation for meeting the disclosure
Example, and together with specification for explaining the principles of this disclosure.It should be evident that the accompanying drawings in the following description is only the disclosure
Some embodiments for those of ordinary skill in the art without creative efforts, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is the process of disclosure embodiment Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method
Figure.
Fig. 2 is step in disclosure embodiment Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method
The flow chart of S130.
Step in Fig. 3 disclosure embodiment Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method
The flow chart of S140.
Fig. 4 is step in disclosure embodiment Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method
The flow chart of S150.
Specific embodiment
Example embodiment is described more fully in standard attached drawing now.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to example set forth herein；On the contrary, thesing embodiments are provided so that the disclosure will more
Fully and completely, and by the design of example embodiment comprehensively it is communicated to those skilled in the art.Described feature, knot
Structure or characteristic can be incorporated in any suitable manner in one or more embodiments.In the following description, it provides perhaps
More details fully understand embodiment of the present disclosure to provide.It will be appreciated, however, by one skilled in the art that can
It is omitted with technical solution of the disclosure one or more in the specific detail, or others side can be used
Method, constituent element, device, step etc..In other cases, be not shown in detail or describe known solution to avoid a presumptuous guest usurps the role of the host and
So that all aspects of this disclosure thicken.
In addition, attached drawing is only the schematic illustrations of the disclosure, it is not necessarily drawn to scale.Identical attached drawing mark in figure
Note indicates same or similar part, thus will omit repetition thereof.Term "the" and " described " are deposited to indicate
One or more elements/component part/etc.；Term " comprising " is to indicate the open meaning being included and refer to
In addition to the element listed/component part/also may be present other than waiting other element/component part/etc..
A kind of fretting fatigue prediction technique is provided in this example embodiment, as shown in Figure 1, it may include following steps:
Step S110 establishes the fretting fatigue contact analysis model of Crystal Nickel-based Superalloy turbo blade tenon；
Step S120 calculates the turbo blade tenon fretting fatigue contact analysis model under given operating condition,
Obtain analysis parameter, the analysis parameter include resolving shear stress, tangential stress and Relative sliding at contact surface different location away from
From；
Step S130 determines fretting fatigue contact point under the given operating condition according to given operating condition and the analysis parameter
Analyse the resolving shear stress damage factor at model contact surface different location；
Step S140 determines the fretting fatigue contact under the given operating condition according to given operating condition and the analysis parameter
Accumulative dissipated energy damage factor at analysis model contact surface different location；
Step S150 determines that fine motion is tired according to the resolving shear stress damage factor and the accumulative dissipated energy damage factor
The labor complex damage factor, and then obtain the fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon.
The fretting fatigue life-span prediction method of the Crystal Nickel-based Superalloy turbo blade tenon of the disclosure, it is contemplated that contact surface is answered
The influence of power state and fretting wear to Fretting Fatigue Damage, and then predicted fatigue life.In the process, due to nickel-based monocrystal
The mechanical property of alloy and crystal orientation are closely related, and resolving shear stress can reflect Crystal Nickel-based Superalloy in fretting fatigue state
The lower damage characteristic that translation gliding easily occurs, thus resolving shear stress damage factor can characterize Fretting Fatigue Damage；Meanwhile accumulating consumption
It dissipates energy damage factor and fretting wear is closely related.Therefore consider crystal orientation and fretting wear to Fretting Fatigue Damage simultaneously
It influences, the accuracy of fretting fatigue life prediction can be improved.
The fretting fatigue prediction technique of the Crystal Nickel-based Superalloy turbo blade tenon of disclosure embodiment is carried out below
It is described in detail:
As shown in Figure 1, in step s 110, establishing the fretting fatigue model of Crystal Nickel-based Superalloy turbo blade tenon.
The turbo blade tenon can be aero engine turbine blades fir tree shape tenon structure, and but not limited to this,
This will not enumerate.
As shown in Figure 1, in the step s 120, to the turbo blade tenon fretting fatigue contact analysis under given operating condition
Model is analyzed, and obtains analysis parameter, the analysis parameter includes resolving shear stress at contact surface different location, tangential stress
With Relative sliding distance.
Fretting fatigue contact analysis model can be calculated under given operating condition, obtain analysis parameter, analysis parameter can
Including resolving shear stress, tangential stress and Relative sliding distance, analyzing parameter certainly can also include other parameters, not another herein
One enumerates.
Given operating condition may include that displacement load, power load or temperature loading, certain load type are not limited with secondary, can also
To apply other load, for simulating stress condition of the turbo blade tenon under fretting fatigue state.It can be according to given work
Condition calculates fretting fatigue contact analysis model, and determines fretting fatigue model in the analysis parameter under giving operating condition.
For example, the geometrical model of Crystal Nickel-based Superalloy turbo blade tenon can be established by finite element software ABAQUS and carries out net
Lattice divide, and by applying reasonable boundary condition, and then obtain analysis parameter.It is of course also possible to pass through other software or other
Mode obtains the analysis parameter at this under giving operating condition, for example, the softwares such as ANSYS, PANTRAN, which can be used, carries out calculating analysis,
Particular determination is not done to calculation method herein.
As shown in Figure 1, in step s 130, according to given operating condition and the analysis parameter, determining under the given operating condition
Resolving shear stress damage factor at fretting fatigue contact analysis model contact surface different location.
Analysis parameter may include resolving shear stress, tangential stress and Relative sliding distance, and certainly, analysis parameter is not limited only to
This, also may include other parameters, for example, contact stress etc..Resolving shear stress can reflect Crystal Nickel-based Superalloy in fretting fatigue
The damage characteristic of translation gliding easily occurs under state, while the ratio between the minimum value of resolving shear stress and maximum value can reflect turbine leaf
The feature of the born fatigue load effect of piece tenon, thus resolving shear stress damage factor can characterize Fretting Fatigue Damage.
As shown in Fig. 2, in one embodiment, determining fretting fatigue contact analysis model contact surface under the given operating condition
Resolving shear stress damage factor at different location may include:
Step S1310 determines the resolving shear stress according to stress tensor and Schmidt's factor.
Stress tensor can be the stress tensor under crystallographic axis coordinate system.It is of course also possible to include other stress tensors.Shi Mi
The special factor can be given by the following formula:
Wherein, P(α)For Schmidt's factor, m(α)For the unit vector of the glide direction of slip system α, n(α)For the list of slide surface
Position normal vector.Resolving shear stress can be determined by corresponding relationship, and corresponding relationship can be provided by the first formula, it may be assumed that
τ(α)=σ: P(α)
Wherein, τ(α)For resolving shear stress, σ is the stress tensor under crystallographic axis system, P(α)For Schmidt's factor.
Step S1320 determines resolving shear stress damage factor according to the yield strength of resolving shear stress and material.
Resolving shear stress damage factor can be provided according to the second formula, and the second formula may be defined as:
Wherein, DRFor resolving shear stress damage factor, τ(α)For the resolving shear stress of slip system α, τminAnd τmaxRespectively τ(α)'s
Minimum value and maximum value, σsFor the yield strength of material, m is the Damage coefficient of material.
As shown in Figure 1, according to given operating condition and the analysis parameter, being determined under the given operating condition in step S140
Fretting fatigue contact analysis model contact surface different location at accumulative dissipated energy damage factor.
Given operating condition and analysis parameter can refer to the content in above-mentioned file, and details are not described herein.
As shown in figure 3, in one embodiment, determining the fretting fatigue contact analysis model contact under the given operating condition
Accumulative dissipated energy damage factor at the different location of face includes:
Step S1410 determines the Dissipated energy at a little according to tangential stress and Relative sliding distance.
By taking point x as an example, tangential stress can between fretting fatigue contact analysis model contact surface unit cross-sectional area at point x
Circumferential load, Relative sliding distance are the relative displacement contacted between object at point x.At this point, the Dissipated energy at point x can be according to
Three formula provide, and third formula may is that
Edi=qi(x)δi(x)
Wherein, EdiFor the Dissipated energy at x point, qiIt (x) is the tangential stress at x point, δiIt (x) is the Relative sliding at x point
Distance.
Step S1420 determines accumulative dissipated energy damage factor according to the Dissipated energy and energy release rate.
Specifically, product Dissipated energy damage factor can be determined by the 4th formula according to Dissipated energy and energy release rate,
Wherein, the 4th formula may be defined as:
Wherein, DEFor accumulative dissipated energy damage factor, G is the energy release rate of material, EdiFor the Dissipated energy at x point.
In the present embodiment, resolving shear stress, tangential stress and relative slippage can pass through analytic method, FInite Element, side
The analysis of the methods of boundary's member method obtains, naturally it is also possible to analyze to obtain by other methods, herein not to solving resolving shear stress, tangential
Stress and the specific method of Relative sliding distance do particular determination.It for example, can be by ABAQUS software assistant analysis, certainly
Assistant analysis, such as ANSYS software, PANTRAN software etc. can also be carried out using other software.
As shown in Figure 1, step S150, according to the resolving shear stress damage factor and the accumulative dissipated energy damage factor,
It determines the fretting fatigue complex damage factor, and then obtains the fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon.
As shown in figure 4, step S150 can include: step S1510, according to the resolving shear stress damage factor and the accumulation
Dissipated energy damage factor determines fretting fatigue complex damage of the fretting fatigue contact analysis model under the given operating condition
The factor.
The particular content of resolving shear stress damage factor and the accumulative dissipated energy damage factor is made in above-mentioned file
It elaborates, can refer to above content, details are not described herein.
The programming softwares such as MATIAB or other mathematical tools can be used to be calculated according to above-mentioned FInite Element or other methods
The fretting fatigue complex damage factor at contact surface each point, naturally it is also possible to be calculated using other methods, herein not to micro-
The method or software that the dynamic fatigue complex damage factor calculates do particular determination.The maximum of the fretting fatigue complex damage factor can be passed through
The corresponding position of value, determines Fretting Fatigue Damage maximum point.That is: the corresponding position of fretting fatigue complex damage factor maximum value
For Fretting Fatigue Damage maximum point.
The fretting fatigue complex damage factor can be calculated by the 5th formula, the 5th formula may be defined as:
RA=a1DR 2+a2DE(DE-a3DR)
Wherein, RA is the fretting fatigue complex damage factor, DRFor resolving shear stress damage factor, DEFor accumulative dissipated energy damage
The factor, ai(i=1,2,3) (ai> 0) it is the parameter determining based on fretting fatigue testing fitting.
Step S1520 determines Crystal Nickel-based Superalloy turbo blade tenon according to the fretting fatigue complex damage factor
The fretting fatigue service life.
Can be used programming software or other mathematical tools carry out simulation calculating, at the same can according to fretting fatigue complex damage because
Linear-logarithmic functional relation between son and fretting fatigue service life calculates the fretting fatigue service life.The fretting fatigue complex damage factor
It can be defined by the 6th formula with corresponding relationship, the 6th formula can are as follows:
RA=A+blnN
Wherein, N is the fretting fatigue service life, and RA is the fretting fatigue complex damage factor, and A, b are experiment parameter, can be by most
Small square law, which calculates, to be determined.
The fretting fatigue service life be consider different slip systems start, in fretting wear and reciprocation between them extremely
The result of a few effect.
In addition, although describing each step of method in the disclosure in the accompanying drawings with particular order, this does not really want
These steps must be executed in this particular order by asking or implying, or having to carry out step shown in whole could realize
Desired result.Additional or alternative, it is convenient to omit multiple steps are merged into a step and executed by certain steps, and/
Or a step is decomposed into execution of multiple steps etc..
Through the above description of the embodiments, those skilled in the art is it can be readily appreciated that example described herein is implemented
Mode can also be realized by software realization in such a way that software is in conjunction with necessary hardware.Therefore, according to the disclosure
The technical solution of embodiment can be embodied in the form of software products, which can store non-volatile at one
Property storage medium (can be CD-ROM, USB flash disk, mobile hard disk etc.) in or network on, including some instructions are so that a calculating
Equipment (can be personal computer, server, mobile terminal or network equipment etc.) is executed according to disclosure embodiment
Method.
Those skilled in the art after considering the specification and implementing the invention disclosed here, will readily occur to its of the disclosure
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the disclosure, these modifications, purposes or
Person's adaptive change follows the general principles of this disclosure and including the undocumented common knowledge in the art of the disclosure
Or conventional techniques.The description and examples are only to be considered as illustrative, and the true scope and spirit of the disclosure are by appended
Claim is pointed out.
Claims (10)
1. a kind of Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method characterized by comprising
Establish Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue contact analysis model；
The turbo blade tenon fretting fatigue contact analysis model is calculated under given operating condition, obtains analysis parameter,
The analysis parameter includes resolving shear stress, tangential stress and the Relative sliding distance at contact surface different location；
According to given operating condition and the analysis parameter, determine that fretting fatigue contact analysis model contact surface is not under the given operating condition
With the resolving shear stress damage factor at position；
According to given operating condition and the analysis parameter, the fretting fatigue contact analysis model contact surface under the given operating condition is determined
Accumulative dissipated energy damage factor at different location；
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, determine fretting fatigue complex damage because
Son, and then obtain the fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon.
2. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method according to claim 1, feature
It is, according to given operating condition and the analysis parameter, determines fretting fatigue contact analysis model contact surface under the given operating condition
Resolving shear stress damage factor at different location includes:
Resolving shear stress damage factor is determined according to the yield strength of resolving shear stress and material.
3. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 2, which is characterized in that
Resolving shear stress, first formula are determined by the first formula are as follows:
τ(α)=σ: P(α)
Wherein, τ(α)For resolving shear stress, σ is the stress tensor under crystallographic axis system, P(α)For Schmidt's factor.
4. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue life-span prediction method according to claim 2, feature
It is, the yield strength according to resolving shear stress and material determines resolving shear stress damage factor, wherein true by the second formula
Determine resolving shear stress damage factor, second formula are as follows:
Wherein, DRFor resolving shear stress damage factor, τ(α)For the resolving shear stress of slip system α, τminAnd τmaxRespectively τ(α)Minimum value
And maximum value, σsFor the yield strength of material, m is the Damage coefficient of material.
5. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 1, which is characterized in that
According to given operating condition and the analysis parameter, determine that the fretting fatigue contact analysis model contact surface under the given operating condition is different
Accumulative dissipated energy damage factor at position includes:
The Dissipated energy at a little is determined according to tangential stress and Relative sliding distance；
Accumulative dissipated energy damage factor is determined according to the Dissipated energy and energy release rate.
6. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 5, which is characterized in that
It is described that Dissipated energy at a little is determined according to tangential stress and Relative sliding distance, Dissipated energy can be determined according to third formula,
The third formula are as follows:
Edi=qi(x)δi(x)
Wherein, EdiFor the Dissipated energy at point x, qiIt (x) is the tangential stress at x point, δiIt (x) is the Relative sliding distance at x point.
7. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 5, which is characterized in that
It is described that accumulative dissipated energy damage factor is determined according to the Dissipated energy and energy release rate, it can be determined and be accumulated according to the 4th formula
Dissipated energy damage factor, the 4th formula are as follows:
Wherein, DEFor accumulative dissipated energy damage factor, G is the energy release rate of material, EdiFor the Dissipated energy at point x.
8. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 1, which is characterized in that
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, the fretting fatigue complex damage factor is determined, into
And the fretting fatigue service life for obtaining Crystal Nickel-based Superalloy turbo blade tenon includes:
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, the fretting fatigue contact analysis is determined
The fretting fatigue complex damage factor of the model under the given operating condition；
The fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon is determined according to the fretting fatigue complex damage factor.
9. Crystal Nickel-based Superalloy turbo blade tenon fretting fatigue prediction technique according to claim 8, which is characterized in that
According to the resolving shear stress damage factor and the accumulative dissipated energy damage factor, the fretting fatigue contact analysis model is determined
The fretting fatigue complex damage factor under the given operating condition includes:
Fretting fatigue complex damage is determined by the 5th formula according to resolving shear stress damage factor and accumulative dissipated energy damage factor
The factor, the 5th formula are as follows:
RA=a1DR 2+a2DE(DE-a3DR)
Wherein, RA is the fretting fatigue complex damage factor, DRFor resolving shear stress damage factor, DEFor accumulative dissipated energy damage factor,
ai(i=1,2,3) (ai> 0) it is the parameter determining based on fretting fatigue testing fitting.
10. fretting fatigue prediction technique according to claim 8, which is characterized in that damaged according to the fretting fatigue is comprehensive
Hurt the factor and determines that fretting fatigue service life of Crystal Nickel-based Superalloy turbo blade tenon includes:
Fretting fatigue service life, the 6th formula are determined by the 6th formula are as follows:
RA=A+blnN
Wherein, N is the fretting fatigue service life, and RA is the fretting fatigue complex damage factor, and A, b are experiment parameter, can pass through minimum two
Multiplication, which calculates, to be determined.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811147466.9A CN109408900B (en) | 2018-09-29 | 2018-09-29 | Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811147466.9A CN109408900B (en) | 2018-09-29 | 2018-09-29 | Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method |
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| Publication Number | Publication Date |
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| CN109408900A true CN109408900A (en) | 2019-03-01 |
| CN109408900B CN109408900B (en) | 2022-04-05 |
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| CN111859561A (en) * | 2020-07-06 | 2020-10-30 | 南京航空航天大学 | Fretting fatigue damage resistance optimization method for turbine joggling structure |
| CN111859561B (en) * | 2020-07-06 | 2024-03-29 | 南京航空航天大学 | Micro-motion fatigue damage resisting optimization method for turbine jogging structure |
| CN113297754A (en) * | 2021-06-30 | 2021-08-24 | 华中科技大学 | Fatigue-creep damage assessment method and system for solar high-temperature heat absorber |
| CN113297754B (en) * | 2021-06-30 | 2024-02-06 | 华中科技大学 | Fatigue-creep damage assessment method and system for solar high-temperature heat absorber |
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