CN109408900B - Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method - Google Patents
Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method Download PDFInfo
- Publication number
- CN109408900B CN109408900B CN201811147466.9A CN201811147466A CN109408900B CN 109408900 B CN109408900 B CN 109408900B CN 201811147466 A CN201811147466 A CN 201811147466A CN 109408900 B CN109408900 B CN 109408900B
- Authority
- CN
- China
- Prior art keywords
- fretting fatigue
- stress
- nickel
- turbine blade
- determining
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method, which comprises the following steps: establishing a fretting fatigue contact analysis model of the turbine blade tenon made of the nickel-based single crystal alloy; calculating the model under a given working condition to obtain analysis parameters, wherein the analysis parameters comprise the slitting stress, the tangential stress and the relative sliding distance at different positions of the contact surface; determining the slitting stress damage factors at different positions of the contact surface of the model under a given working condition; determining accumulated dissipation energy damage factors at different positions of the contact surface of the model under the given working condition according to the given working condition and the analysis parameters; and determining the fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor, and further obtaining the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy. The method for predicting the fretting fatigue life of the tenon of the nickel-based single crystal alloy turbine blade can accurately predict the fretting fatigue life of the tenon of the nickel-based single crystal alloy turbine blade.
Description
Technical Field
The disclosure relates to the technical field of structural design and strength, in particular to a nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method.
Background
The nickel-based single crystal alloy has good high temperature resistance, creep resistance, oxidation resistance and thermal mechanical fatigue resistance, so the nickel-based single crystal alloy is widely applied to turbine blades of aeroengines and gas turbines. The turbine blade is usually connected with the turbine disc by adopting a tenon connection structure, the tenon structure of the turbine blade is very easy to generate fretting fatigue under the action of periodic centrifugal load and the like, and the fretting fatigue problem of the nickel-based single crystal tenon structure is more prominent under the severe environment of high temperature and high rotating speed of the turbine. Therefore, the method realizes accurate prediction of the fretting fatigue life of the nickel-based single crystal turbine blade tenon, and has great significance for the design of aeroengines and gas turbines.
The traditional fretting fatigue life prediction method of the conventional alloy mainly considers the influence rule of various factors such as contact stress, surface state, relative slip and load state on fretting fatigue according to the wear rule and the fatigue damage characteristic, provides comprehensive parameters for describing fretting damage, and realizes the prediction of crack initiation positions and fretting fatigue life by establishing the relationship between the fretting damage parameters and the fretting fatigue life. Considering that the contact area is in a multi-axial stress state, the micro-motion fatigue life prediction method based on the multi-axial fatigue theory is widely applied.
Compared with the conventional polycrystalline material, the mechanical behavior of the nickel-based single crystal alloy has the characteristics of crystal orientation correlation, crystal orientation sensitivity, tension and compression asymmetry, anti-Schmidt effect, medium-temperature brittleness and the like. The conventional fretting fatigue life prediction method cannot represent the characteristic of fretting fatigue damage failure of the nickel-based single crystal superalloy, so that the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal superalloy cannot be accurately predicted.
It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
The invention aims to provide a method for predicting the fretting fatigue life of a tenon of a nickel-based single-crystal alloy turbine blade, which can accurately predict the fretting fatigue life of the tenon of the nickel-based single-crystal alloy turbine blade.
According to one aspect of the disclosure, a method for predicting fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy is provided, which includes:
establishing a nickel-based single crystal alloy turbine blade tenon fretting fatigue contact analysis model;
calculating the turbine blade tenon fretting fatigue contact analysis model under a given working condition to obtain analysis parameters, wherein the analysis parameters comprise the slitting stress, the tangential stress and the relative sliding distance of different positions of a contact surface;
determining slitting stress damage factors at different positions of a contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
determining accumulated dissipation energy damage factors at different positions of a contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
and determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor, and further obtaining the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy.
In an exemplary embodiment of the disclosure, determining the slitting stress damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition according to the given working condition and the analysis parameters comprises:
and determining the damage factor of the slitting stress according to the slitting stress and the yield strength of the material.
In an exemplary embodiment of the present disclosure, the shear stress is determined by a first formula:
τ(α)＝σ:P(α)
wherein, tau(α)For the shear stress, σ is the stress tensor under the crystal axis system, P(α)Is a schmitt factor.
In an exemplary embodiment of the present disclosure, the determining a fracture stress damage factor according to the fracture stress and the yield strength of the material, wherein the determining the fracture stress damage factor is performed by a second formula, where the second formula is:
wherein D isRIs a factor of the fracture stress damage, tau(α)For the shear stress of the slip system alpha, tauminAnd τmaxAre each tau(α)Minimum and maximum values of, σsM is the yield strength of the material and the damage coefficient of the material.
In an exemplary embodiment of the disclosure, determining the accumulated dissipated energy damage factor at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition according to the given working condition and the analysis parameter comprises:
determining the dissipation energy at one point according to the tangential stress and the relative sliding distance;
and determining a cumulative dissipated energy damage factor according to the dissipated energy and the energy release rate.
In an exemplary embodiment of the disclosure, the determining the dissipation energy at a point according to the tangential stress and the relative slip distance may be determined according to a third formula:
Edi＝qi(x)δi(x)
wherein, EdiIs the dissipated energy at point x, qi(x) Is the tangential stress at point x, δi(x) Is the relative slip distance at point x.
In an exemplary embodiment of the present disclosure, the determining a cumulative dissipated energy damage factor according to the dissipated energy and the energy release rate may determine a cumulative dissipated energy damage factor according to a fourth formula, where the fourth formula is:
wherein D isEFor cumulative dissipated energy damage factor, G is the energy release rate of the material, EdiIs at point xThe dissipated energy of.
In an exemplary embodiment of the disclosure, determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipated energy damage factor, and further obtaining the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal alloy includes:
determining a fretting fatigue comprehensive damage factor of the fretting fatigue contact analysis model under the given working condition according to the slitting stress damage factor and the accumulated dissipation energy damage factor;
and determining the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal alloy according to the fretting fatigue comprehensive damage factor.
In an exemplary embodiment of the disclosure, determining the fretting fatigue comprehensive damage factor of the fretting fatigue contact analysis model under the given working condition according to the slitting stress damage factor and the accumulated dissipated energy damage factor includes:
determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor through a fifth formula, wherein the fifth formula is as follows:
RA＝a1DR 2+a2DE(DE-a3DR)
wherein RA is fretting fatigue syndrome damage factor, DRIs a factor of the fracture stress damage, DETo accumulate a dissipation energy impairment factor, ai(i＝1,2,3)(ai> 0) are parameters determined based on fretting fatigue test fitting.
In an exemplary embodiment of the disclosure, determining the fretting fatigue life of a nickel-based single crystal alloy turbine blade tenon from the fretting fatigue composite damage factor comprises:
determining the fretting fatigue life by a sixth formula, the sixth formula being:
RA＝A+blnN
wherein N is fretting fatigue life, RA is fretting fatigue comprehensive damage factor, A, b are experimental parameters, and can be determined by least square method calculation.
The method for predicting the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy considers the influence of the stress state of the contact surface and fretting wear on fretting fatigue damage, provides a fretting fatigue comprehensive damage factor of the nickel-based single crystal alloy, and then predicts the fatigue life. In the process, because the mechanical property of the nickel-based single crystal alloy is closely related to the crystal orientation, and the cutting stress can reflect the damage characteristic that the nickel-based single crystal alloy is easy to generate crystal slippage in a fretting fatigue state, the cutting stress damage factor can represent fretting fatigue damage; meanwhile, the accumulated dissipated energy damage factor is closely related to fretting. Therefore, the influence of crystal orientation and fretting wear on fretting fatigue damage is considered at the same time, and the accuracy of fretting fatigue life prediction can be improved.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 is a flowchart of a method for predicting fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy according to an embodiment of the disclosure.
Fig. 2 is a flowchart of step S130 in the method for predicting fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy according to the embodiment of the present disclosure.
FIG. 3 is a flowchart of step S140 in the method for predicting fretting fatigue life of a turbine blade tenon made of a nickel-based single crystal alloy according to the embodiment of the present disclosure.
FIG. 4 is a flowchart of step S150 in the method for predicting fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy according to the embodiment of the disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying standard drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the disclosure. One skilled in the relevant art will recognize, however, that the subject matter of the present disclosure can be practiced without one or more of the specific details, or with other methods, components, devices, steps, and the like. In other instances, well-known technical solutions have not been shown or described in detail to avoid obscuring aspects of the present disclosure.
Furthermore, the drawings are merely schematic illustrations of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. The terms "the" and "said" are used to indicate the presence of one or more elements/components/etc.; the term "comprising" is used in an open-ended inclusive sense and means that there may be additional elements/components/etc. other than the listed elements/components/etc.
The present exemplary embodiment provides a fretting fatigue prediction method, as shown in fig. 1, which may include the following steps:
step S110, establishing a fretting fatigue contact analysis model of the turbine blade tenon made of the nickel-based single crystal alloy;
step S120, calculating the turbine blade tenon fretting fatigue contact analysis model under a given working condition to obtain analysis parameters, wherein the analysis parameters comprise the slitting stress, the tangential stress and the relative sliding distance of different positions of a contact surface;
step S130, determining slitting stress damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
step S140, determining accumulated dissipation energy damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
and S150, determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor, and further obtaining the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy.
According to the fretting fatigue life prediction method for the turbine blade tenon made of the nickel-based single crystal alloy, the influence of the stress state of the contact surface and fretting wear on fretting fatigue damage is considered, and the fatigue life is predicted. In the process, because the mechanical property of the nickel-based single crystal alloy is closely related to the crystal orientation, and the cutting stress can reflect the damage characteristic that the nickel-based single crystal alloy is easy to generate crystal slippage in a fretting fatigue state, the cutting stress damage factor can represent fretting fatigue damage; meanwhile, the accumulated dissipated energy damage factor is closely related to fretting. Therefore, the influence of crystal orientation and fretting wear on fretting fatigue damage is considered at the same time, and the accuracy of fretting fatigue life prediction can be improved.
The method for predicting fretting fatigue of a turbine blade tenon made of a nickel-based single crystal alloy according to an embodiment of the present disclosure will be described in detail below:
as shown in FIG. 1, in step S110, a fretting fatigue model of a turbine blade tenon of a nickel-based single crystal alloy is established.
The turbine blade tenon can be a fir-tree tenon structure of a turbine blade of an aircraft engine, but the structure is not limited to the structure, and is not listed any more.
As shown in fig. 1, in step S120, the turbine blade tenon fretting fatigue contact analysis model is analyzed under a given working condition, and analysis parameters are obtained, where the analysis parameters include a cutting stress, a tangential stress and a relative sliding distance at different positions of a contact surface.
The fretting fatigue contact analysis model can be calculated under a given working condition to obtain analysis parameters, wherein the analysis parameters can comprise the slitting stress, the tangential stress and the relative sliding distance, and the analysis parameters can also comprise other parameters which are not listed one by one.
The given working condition can comprise displacement load, force load or temperature load, although the load type is not limited, and other loads can be applied to simulate the stress condition of the turbine blade tenon in the fretting fatigue state. The fretting fatigue contact analysis model can be calculated according to a given working condition, and analysis parameters of the fretting fatigue model under the given working condition are determined. For example, a geometric model of the turbine blade tenon made of the nickel-based single crystal alloy can be established through finite element software ABAQUS and is subjected to meshing, and analysis parameters are obtained by applying reasonable boundary conditions. Of course, the analysis parameters under the given condition may also be obtained by other software or other means, for example, software such as ANSYS, panaran, etc. may be used for calculation and analysis, and the calculation method is not particularly limited herein.
As shown in fig. 1, in step S130, according to a given working condition and the analysis parameters, determining the slitting stress damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition.
The analysis parameters may include the part stress, the tangential stress, and the relative slip distance, but of course, the analysis parameters are not limited thereto, and may include other parameters, such as the contact stress, etc. The cutting stress can reflect the damage characteristic that the nickel-based single crystal alloy is easy to generate crystal slippage in the fretting fatigue state, and the ratio of the minimum value to the maximum value of the cutting stress can reflect the characteristic of the fatigue load effect borne by the tenon of the turbine blade, so that the cutting stress damage factor can represent fretting fatigue damage.
In one embodiment, as shown in fig. 2, determining the slitting stress damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition may include:
step S1310, determining the slitting stress according to the stress tensor and the schmitt factor.
The stress tensor can be a stress tensor in a crystallographic coordinate system. Of course, other stress tensors may be included. The schmitt factor can be given by the following equation:
wherein, P(α)Is a Schmidt factor, m(α)Is a unit vector of slip direction of slip system alpha, n(α)Is the unit normal vector of the slip plane. The slitting stress can be determined by a correspondence, and the correspondence can be given by a first formula, namely:
τ(α)＝σ:P(α)
wherein, tau(α)For the shear stress, σ is the stress tensor under the crystal axis system, P(α)Is a schmitt factor.
Step S1320, determining a fracture stress damage factor according to the fracture stress and the yield strength of the material.
The slitting stress damage factor can be given according to a second formula, which can be defined as:
wherein D isRIs a factor of the fracture stress damage, tau(α)For the shear stress of the slip system alpha, tauminAnd τmaxAre each tau(α)Minimum and maximum values of, σsM is the yield strength of the material and the damage coefficient of the material.
As shown in fig. 1, in step S140, according to a given condition and the analysis parameters, cumulative dissipation energy damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given condition are determined.
The given conditions and analysis parameters can refer to the contents in the above documents, and are not described herein again.
As shown in fig. 3, in an embodiment, determining the accumulated dissipated energy damage factor at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition includes:
and step S1410, determining the dissipation energy at one point according to the tangential stress and the relative sliding distance.
Taking point x as an example, the tangential stress can be a tangential load per unit cross-sectional area at point x between contact surfaces of the fretting fatigue contact analysis model, and the relative sliding distance is a relative displacement between contact objects at point x. At this time, the dissipated energy at point x may be given according to a third formula, which may be:
Edi＝qi(x)δi(x)
wherein, EdiIs the dissipated energy at point x, qi(x) Is the tangential stress at point x, δi(x) Is the relative slip distance at point x.
And step S1420, determining a cumulative dissipated energy damage factor according to the dissipated energy and the energy release rate.
Specifically, the product dissipation energy damage factor may be determined from the dissipation energy and the energy release rate by a fourth formula, wherein the fourth formula may be defined as:
wherein D isEFor cumulative dissipated energy damage factor, G is the energy release rate of the material, EdiIs the dissipated energy at point x.
In the present embodiment, the shear stress, the tangential stress, and the relative slip amount may be obtained by analysis using an analytical method, a finite element method, a boundary element method, or the like, or may be obtained by analysis using other methods, and specific methods for solving the shear stress, the tangential stress, and the relative slip distance are not particularly limited. For example, the analysis may be assisted by ABAQUS software, but other software may be used for the analysis, such as ANSYS software, panaran software, and the like.
As shown in fig. 1, in step S150, determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor, and further obtaining the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy.
As shown in fig. 4, step S150 may include: and step S1510, determining a fretting fatigue comprehensive damage factor of the fretting fatigue contact analysis model under the given working condition according to the slitting stress damage factor and the accumulated dissipation energy damage factor.
The specific contents of the cutting stress damage factor and the accumulated dissipation energy damage factor are described in detail in the above documents, and reference is made to the above contents, which are not repeated herein.
The fretting fatigue comprehensive damage factor at each point of the contact surface can be calculated by adopting programming software such as MATIAB or other mathematical tools according to the finite element method or other methods, and of course, other methods can be adopted for calculation, and the method or software for calculating the fretting fatigue comprehensive damage factor is not specially limited. And determining the maximum point of the fretting fatigue damage according to the position corresponding to the maximum value of the fretting fatigue comprehensive damage factor. Namely: and the position corresponding to the maximum value of the fretting fatigue comprehensive damage factor is the maximum point of the fretting fatigue damage.
The fretting fatigue composite damage factor can be calculated by a fifth formula, which can be defined as:
RA＝a1DR 2+a2DE(DE-a3DR)
wherein RA is fretting fatigue syndrome damage factor, DRIs a factor of the fracture stress damage, DETo accumulate a dissipation energy impairment factor, ai(i＝1,2,3)(ai> 0) are parameters determined based on fretting fatigue test fitting.
And S1520, determining the fretting fatigue life of the turbine blade tenon made of the nickel-based single crystal alloy according to the fretting fatigue comprehensive damage factor.
The simulation calculation can be carried out by adopting programming software or other mathematical tools, and the fretting fatigue life can be calculated according to the linear logarithmic function relationship between the fretting fatigue comprehensive damage factor and the fretting fatigue life. The fretting fatigue composite damage factor and the correspondence may be defined by a sixth formula, which may be:
RA＝A+blnN
wherein N is fretting fatigue life, RA is fretting fatigue comprehensive damage factor, A, b are experimental parameters, and can be determined by least square method calculation.
The fretting fatigue life is a result of taking into account at least one of different slip train starts, fretting and interactions between them.
Moreover, although the steps of the methods of the present disclosure are depicted in the drawings in a particular order, this does not require or imply that the steps must be performed in this particular order, or that all of the depicted steps must be performed, to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken down into multiple step executions, etc.
Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein may be implemented by software, or by software in combination with necessary hardware. Therefore, the technical solution according to the embodiments of the present disclosure may be embodied in the form of a software product, which may be stored in a non-volatile storage medium (which may be a CD-ROM, a usb disk, a removable hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which may be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiments of the present disclosure.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (7)
1. A nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method is characterized by comprising the following steps:
establishing a nickel-based single crystal alloy turbine blade tenon fretting fatigue contact analysis model;
calculating the turbine blade tenon fretting fatigue contact analysis model under a given working condition to obtain analysis parameters, wherein the analysis parameters comprise the slitting stress, the tangential stress and the relative sliding distance of different positions of a contact surface;
determining slitting stress damage factors at different positions of a contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
determining accumulated dissipation energy damage factors at different positions of a contact surface of the fretting fatigue contact analysis model under a given working condition according to the given working condition and the analysis parameters;
determining a fretting fatigue comprehensive damage factor of the fretting fatigue contact analysis model under the given working condition according to the slitting stress damage factor and the accumulated dissipation energy damage factor;
determining the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal alloy according to the fretting fatigue comprehensive damage factor;
determining the fretting fatigue comprehensive damage factor of the fretting fatigue contact analysis model under the given working condition according to the slitting stress damage factor and the accumulated dissipation energy damage factor comprises the following steps:
determining a fretting fatigue comprehensive damage factor according to the slitting stress damage factor and the accumulated dissipation energy damage factor through a fifth formula, wherein the fifth formula is as follows:
RA＝a1DR 2+a2DE(DE-a3DR)
wherein RA is fretting fatigue syndrome damage factor, DRIs a factor of the fracture stress damage, DETo accumulate a dissipation energy impairment factor, ai i＝1，2，3，aiMore than 0 is a parameter determined based on fretting fatigue test fitting;
determining the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal alloy according to the fretting fatigue comprehensive damage factor comprises the following steps:
determining the fretting fatigue life by a sixth formula, the sixth formula being:
RA＝A+blnN
wherein N is fretting fatigue life, RA is fretting fatigue comprehensive damage factor, A, b are experimental parameters, and can be determined by least square method calculation.
2. The method for predicting the fretting fatigue life of the turbine blade tenon of the nickel-based single crystal alloy according to claim 1, wherein determining the slitting stress damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition according to the given working condition and the analysis parameters comprises:
and determining the damage factor of the slitting stress according to the slitting stress and the yield strength of the material.
3. The method of predicting fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy of claim 2, wherein the shear stress is determined by a first formula, the first formula being:
τ(α)＝σ：P(α)
wherein, tau(α)For the shear stress, σ is the stress tensor under the crystal axis system, P(α)Is a schmitt factor.
4. The method for predicting the fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy according to claim 2, wherein the fracture stress damage factor is determined according to the fracture stress and the yield strength of the material, wherein the fracture stress damage factor is determined by a second formula, and the second formula is as follows:
wherein D isRIs a factor of the fracture stress damage, tau(α)For the shear stress of the slip system alpha, tauminAnd τmaxAre each tau(α)Minimum and maximum values of, σsM is the yield strength of the material and the damage coefficient of the material.
5. The method for predicting the fretting fatigue life of a turbine blade tenon of a nickel-based single crystal alloy according to claim 1, wherein determining the accumulated dissipated energy damage factors at different positions of the contact surface of the fretting fatigue contact analysis model under the given working condition according to the given working condition and the analysis parameters comprises:
determining the dissipation energy at one point according to the tangential stress and the relative sliding distance;
and determining a cumulative dissipated energy damage factor according to the dissipated energy and the energy release rate.
6. The method of predicting fretting fatigue life of a nickel-based single crystal alloy turbine blade tenon of claim 5, wherein said determining dissipated energy at a point based on tangential stress and relative sliding distance is performed according to a third formula:
Edi＝qi(x)δi(x)
wherein, EdiIs the dissipated energy at point x, qi(x) Is the tangential stress at point x, δi(x) Is the relative slip distance at point x.
7. The method of predicting fretting fatigue life of a turbine blade of a nickel-based single crystal alloy according to claim 5, wherein said determining a cumulative dissipated energy damage factor from said dissipated energy and an energy release rate is performed according to a fourth formula, said fourth formula being:
wherein D isEFor cumulative dissipated energy damage factor, G is the energy release rate of the material, EdiIs the dissipated energy at point x.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109408900A CN109408900A (en) | 2019-03-01 |
| CN109408900B true CN109408900B (en) | 2022-04-05 |
Family
ID=65465649
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811147466.9A Active CN109408900B (en) | 2018-09-29 | 2018-09-29 | Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109408900B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109933952B (en) * | 2019-04-04 | 2022-09-30 | 西北工业大学 | Method for predicting fatigue life of nickel-based single crystal alloy by considering surface roughness |
| CN110096769A (en) * | 2019-04-16 | 2019-08-06 | 西北工业大学 | A kind of engine single crystal blade Thermomechanical Fatigue Life fast evaluation method |
| CN110232223B (en) * | 2019-05-27 | 2022-09-27 | 西北工业大学 | Prediction method of nickel-based single crystal superalloy microstructure raft type |
| CN110348056A (en) * | 2019-06-12 | 2019-10-18 | 南京航空航天大学 | A kind of Temperature Fretting fatigue life prediction model and its method based on continuum damage mechanics |
| CN111323316B (en) * | 2020-01-06 | 2021-07-13 | 湖南大学 | Multi-axial fatigue life prediction method and device |
| 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 |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630450A (en) * | 2013-12-10 | 2014-03-12 | 云南云岭高速公路养护绿化工程有限公司 | Asphalt mixture life prediction method considering fatigue-creep interaction damage effect |
| CN107884290A (en) * | 2017-10-16 | 2018-04-06 | 北京理工大学 | A kind of fretting fatigue cracks extension life-span prediction method under consideration effect of attrition |
| CN108334716A (en) * | 2018-03-07 | 2018-07-27 | 西北工业大学 | Monocrystalline air film pole high-cycle fatigue life method |
| CN108375468A (en) * | 2016-12-22 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of simulation test experiment platform of achievable fretting wear and tired complex conditions |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6612181B2 (en) * | 2001-09-04 | 2003-09-02 | Jalees Ahmad | Method and system for determining crack nucleation of a part subject to fretting fatigue |
-
2018
- 2018-09-29 CN CN201811147466.9A patent/CN109408900B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630450A (en) * | 2013-12-10 | 2014-03-12 | 云南云岭高速公路养护绿化工程有限公司 | Asphalt mixture life prediction method considering fatigue-creep interaction damage effect |
| CN108375468A (en) * | 2016-12-22 | 2018-08-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of simulation test experiment platform of achievable fretting wear and tired complex conditions |
| CN107884290A (en) * | 2017-10-16 | 2018-04-06 | 北京理工大学 | A kind of fretting fatigue cracks extension life-span prediction method under consideration effect of attrition |
| CN108334716A (en) * | 2018-03-07 | 2018-07-27 | 西北工业大学 | Monocrystalline air film pole high-cycle fatigue life method |
Non-Patent Citations (3)
| Title |
|---|
| Finite element simulation of surface deformation of polycrystal with a rough surface under repeated load;Fang, Xiong等;《FINITE ELEMENTS IN ANALYSIS AND DESIGN》;20121130;第60卷;全文 * |
| 配合间隙对涡轮叶片榫头/榫槽接触的影响*;王少飞等;《推进技术》;20150131;第36卷(第1期);全文 * |
| 镍基单晶合金高温低周疲劳微观损伤及断裂机制;曹刚等;《热加工工艺》;20171130;第46卷(第22期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109408900A (en) | 2019-03-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109408900B (en) | Nickel-based single crystal alloy turbine blade tenon fretting fatigue life prediction method | |
| CN109933952B (en) | Method for predicting fatigue life of nickel-based single crystal alloy by considering surface roughness | |
| Getsov et al. | Thermal fatigue analysis of turbine discs on the base of deformation criterion | |
| CN111090957B (en) | Dangerous point stress-strain calculation method for high-temperature structure | |
| Tomevenya et al. | Probabilistic fatigue-creep life reliability assessment of aircraft turbine disk | |
| Newman Jr et al. | Fatigue and crack growth in 7050-T7451 aluminum alloy under constant-and variable-amplitude loading | |
| CN110232223A (en) | The prediction technique of nickel-base high-temperature single crystal alloy micro-structure raft type | |
| Das et al. | Multiaxial fatigue life prediction of a high temperature steam turbine rotor using a critical plane approach | |
| Kadau et al. | Probabilistic fracture mechanics for heavy-duty gas turbine rotor forgings | |
| Arakere | High-temperature fatigue properties of single crystal superalloys in air and hydrogen | |
| Mücke et al. | A cyclic life prediction approach for directionally solidified nickel superalloys | |
| Enright et al. | Probabilistic fretting fatigue assessment of aircraft engine disks | |
| Lv et al. | Lifetime prediction for turbine discs based on a modified Walker strain model | |
| Holdsworth | Advances in the assessment of creep data during the past 100 years | |
| Chan et al. | Probabilistic high-cycle fretting fatigue assessment of gas turbine engine components | |
| Vasilyev et al. | NUMERICAL METHOD OF SINGLE-CRYSTAL TURBINE BLADE STATIC STRENGTH ESTIMATION TAKING INTO ACCOUNT PLASTICITY AND CREEP EFFECTS. | |
| Mazur et al. | Evaluation of Creep Damage in a Gas Turbine First Stage Blade | |
| Nozhnitsky et al. | Numerical simulation of spin testing for turbo machine disks using energy-based fracture criteria | |
| Huang et al. | A physically based methodology for predicting anisotropic creep properties of Ni-based superalloys | |
| CN114139276A (en) | Fatigue life analysis method for disk-shaft integrated blisk structure | |
| Daroogheh et al. | Engine life evaluation based on a probabilistic approach | |
| Wu et al. | Material selection issues for a nozzle guide vane against service-induced failure | |
| MacLachlan et al. | The effect of material behaviour on the analysis of single crystal turbine blades: Part II–Component analysis | |
| Dileep et al. | Effect of fatigue damage parameter on the cumulative life of a turbine rotor under multiaxial loading | |
| Qin et al. | Fundamental frequencies of turbine blades with geometry mismatch in fir-tree attachments |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |