CN112069716A - Alloy part service life assessment management method and system - Google Patents
Alloy part service life assessment management method and system Download PDFInfo
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- CN112069716A CN112069716A CN202011249968.XA CN202011249968A CN112069716A CN 112069716 A CN112069716 A CN 112069716A CN 202011249968 A CN202011249968 A CN 202011249968A CN 112069716 A CN112069716 A CN 112069716A
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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Abstract
The invention discloses a method and a system for evaluating and managing the service life of an alloy part. The method comprises the steps of carrying out a load-holding test on an alloy part sample to obtain an-N curve, carrying out fitting interpolation on the-N curve, carrying out finite element analysis on the alloy part to obtain the stress state and the temperature of a dangerous point, obtaining the load-holding fatigue life of the alloy part by combining the obtained-N curve and the result of the finite element analysis, obtaining the theoretical running time according to a design load spectrum, and carrying out load-holding fatigue life evaluation on the alloy part based on a Miner linear cumulative damage criterion. The system comprises a load-holding test module, a load-holding test result processing module, a finite element analysis module, a load-holding fatigue life calculation module and a life evaluation and management module. The method and the system for evaluating and managing the service life of the alloy part consider the influence of the load-holding time of the part under the peak load, and realize the efficient evaluation and management of the service life of the alloy part in the service process.
Description
Technical Field
The invention relates to alloy parts, in particular to a method for evaluating and managing the service life of a titanium alloy part by considering a load-holding effect.
Background
The titanium alloy material is an alloy material based on titanium, has the advantages of light weight, high specific strength, good corrosion resistance and the like, and is widely applied to various engine systems.
Statistically, for light weight and economy, titanium alloys with high specific strength are currently selected for aircraft engines/gas turbines as the material of approximately 1/3, such as those commonly used for fan disks, blisks, and the like.
However, the titanium alloy tends to maintain the load fatigue phenomenon at low temperature (generally below 200 ℃), and the fatigue failure of the structure is not only related to the number N of cycles, but also related to the time t of single cycle environmental load. Even though the number of part cycles is small, the fatigue failure problem can occur early due to the holding under peak load for a period of time. Typically manifested as a period of time during which the stress remains loaded at the peak of fatigue, a significant reduction in life occurs compared to conventional cyclic low cycle fatigue. In addition, cracks usually originate in subsurface, are difficult to be effectively detected in the service process of parts, and seriously jeopardize the safety and reliability of the aircraft engine.
In order to ensure that the aircraft engine/gas turbine can be safely, reliably and durably used, the titanium alloy parts need to be subjected to load-holding life assessment and life management.
At present, in the service life evaluation and service life management processes of titanium alloy parts of aeroengines/gas turbines, the fatigue test data under triangular wave cyclic load of titanium alloy materials are all based, and the influence of the holding time of the parts under peak load, namely the influence of rectangular wave cyclic load, is not considered. This may overestimate the fatigue life of some titanium alloys under real operating conditions, causing serious safety accidents.
The problem of titanium alloy holding tends to have one typical characteristic: fatigue failure depends on the total dwell time T of the part at peak load, i.e., T = N × T (N is the number of cycles and T is the time to single cycle load), and test safety can be ensured by limiting the total run time T (i.e., the total dwell time).
Based on the above, the invention provides a calculation method for evaluating the load-holding life of an aircraft engine/gas turbine titanium alloy part, a load-holding life management method and a system thereof.
Disclosure of Invention
This summary is provided to introduce a selection of concepts in a simplified form that are further described below in the detailed description. This summary is not intended to identify key features or essential features of the claimed subject matter; nor is it intended to be used as an aid in determining or limiting the scope of the claimed subject matter.
The invention provides an assessment method and a load-holding life management method for the fatigue life of titanium alloy parts of an aircraft engine/gas turbine by considering the influence of a load-holding effect on the fatigue life of the titanium alloy, introduces the influence of the load-holding effect on the fatigue performance of a titanium alloy material through a titanium alloy part fatigue life model under rectangular wave cyclic load, and solves the problem that the design of the service life of the titanium alloy part is biased in the prior art.
The method of the invention can also be used for guiding the fatigue life evaluation and the load-holding life management of alloy parts in other engines with load-holding effect alloy materials.
The invention discloses a method for evaluating and managing the service life of an alloy part, which comprises the following steps:
carrying out a load-holding test on an alloy part sample to obtain a-N curve, wherein the total strain is N, and the service life is N;
fitting interpolation is carried out on the obtained-N curve;
carrying out finite element analysis on the alloy part to obtain the stress state and the temperature of a dangerous point;
combining the obtained-N curve and the result of finite element analysis to obtain the load-holding fatigue life of the alloy part; and
and obtaining theoretical running time according to a design load spectrum, and carrying out load-holding fatigue life evaluation on the alloy part based on a Miner linear accumulated damage criterion.
The invention relates to an alloy part service life evaluation management system, which comprises:
the holding test module is used for carrying out holding test on the sample of the alloy part and acquiring a-N curve;
a load-holding test result processing module for performing fitting interpolation on the-N curve from the load-holding test module;
the finite element analysis module is used for carrying out finite element analysis on the alloy part and acquiring the stress state and the temperature of a dangerous point;
the load-holding fatigue life calculating module is used for receiving the analysis result from the finite element analysis module and the processing result from the load-holding test result processing module to calculate the fatigue life; and
and the service life evaluation and management module is used for evaluating and managing the service life of the alloy part.
The method and the system firstly determine the single cycle load-holding time of the rectangular wave load-holding test, carry out the rectangular wave load-holding test on the alloy part sample to obtain the alloy sample part load-holding fatigue life under different load-holding peak loads and different temperatures, and draw
-N curve,
-N curve and
-an N-curve; wherein the content of the first and second substances,
in order to be the total strain,
in order to be elastically strained,
is a plastic strain. Then according to different temperatures
-N curve and
an N curve is obtained by utilizing a log-log linear relation and fitting a unitary quadratic equation to obtain parameter equations at different temperatures, and the parameters and the related temperature are interpolated and substituted into a coffee-Mason equation to obtain a coffee-Mason equation at the corresponding temperature; meanwhile, establishing a finite element model of the alloy part, carrying out finite element calculation on the loading load and the boundary condition, taking the stress maximum node in the calculation result as a dangerous point, and extracting the stress of the dangerous point
And the corresponding temperature Ti; stress according to danger point
And corresponding temperature Ti, acquiring a strain history based on a rain flow counting method and a Neuber method elastic-plastic correction, and acquiring the load-holding fatigue life of the alloy part by combining a Coffin-Mason equation after interpolation; for life assessment and management.
The method and the system for carrying out the load-holding life evaluation and the life management on the titanium alloy part effectively solve the efficient evaluation and management under the condition that the fatigue failure problem occurs in advance when the titanium alloy is stored at a low temperature and subjected to the load-holding fatigue phenomenon. The safety and the reliability of the aircraft engine are improved, and safety accidents are effectively prevented.
Drawings
The present invention will now be described more fully hereinafter with reference to the accompanying drawings, in which specific embodiments of the invention are shown.
FIG. 1 is a flow chart of a method of alloy part life assessment and management according to an embodiment of the present invention.
Fig. 2 is a triangular wave test loading spectrum over time.
Fig. 3 is a rectangular wave test loading spectrum over time.
FIG. 4 is a block diagram of an alloy part life assessment and management system according to an embodiment of the invention.
The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s).
Detailed Description
The present invention will now be described more fully hereinafter with reference to the accompanying drawings, in which specific embodiments of the invention are shown.
FIG. 2 is a schematic diagram of a triangular wave cyclic load test of a titanium alloy material in the process of life evaluation and life management of a titanium alloy part in the prior art.
FIG. 3 is a schematic diagram of the rectangular wave cyclic load test of the present invention, which takes into account the effect of the dwell time of the part under peak load.
The method for evaluating and managing the service life of the alloy part according to the embodiment of the invention is explained in the following with reference to fig. 1.
The method comprises the steps of firstly carrying out a titanium alloy sample holding test in step 101 to obtain a-N curve. The method specifically comprises the following steps: determining the single-cycle load-holding time of the rectangular wave load-holding test, carrying out the rectangular wave load-holding test on the sample to obtain the load-holding fatigue life (time) of the titanium alloy sample under different load-holding peak loads and different temperatures, and drawing
-N curve,
-N curve and
-N curve.
Next, in step 102, finite element analysis of the titanium alloy component is performed to obtain the stress state and temperature of the dangerous point. The method specifically comprises the following steps: and establishing a finite element model of the titanium alloy part, and loading the load and boundary conditions in each actual working state or test state to perform finite element calculation. Taking the stress maximum node in the calculation result as a dangerous point under the working condition, and extracting the stress of the point
And the corresponding temperature Ti.
The titanium alloy holding test-N curve is subjected to fitting interpolation in step 103. The method specifically comprises the following steps:
according to the temperature
-N curve and
-N curves, using a log-log linear relationship, fitting by a quadratic equation of unity to obtain parametric equations at different temperatures:
will be parameter
、
、
And
and interpolating the temperature and substituting the temperature into a Coffin-Manson equation to obtain the Coffin-Manson equation at the corresponding temperature. Wherein the content of the first and second substances,bin order to be an index of the fatigue strength,cis the plasticity (toughness) index. Parameter(s)dIt is selected according to the material characteristics.
In step 104, the finite element analysis result and the load-holding test-N curve are combined to obtain the load-holding fatigue life. The method specifically comprises the following steps: according to the single-point maximum stress of the titanium alloy part finite element model under each working condition
And corresponding to the temperature Ti, acquiring a strain history based on a rain flow counting method and a Neuber method elastic-plastic correction, and acquiring the load-holding fatigue life Ti of the titanium alloy part by combining a Coffin-Mason equation after interpolation.
Finally, in step 105, fatigue life assessment and remaining life management are performed based on the Miner's linear cumulative damage criterion. Step 105 further comprises:
a) evaluating the load-holding fatigue life of the titanium alloy part: obtaining theoretical running time ti _ design under each working condition needing considering the problem of the overload fatigue according to a design load spectrum of the titanium alloy part, and evaluating the overload fatigue life of the titanium alloy part based on a Miner linear accumulated damage criterion:
require that
The threshold is obtained from "1/life dispersion factor".
b) Managing the titanium alloy part load-holding fatigue life: counting the actual running time ti _ test of the titanium alloy part under each working condition needing to consider the overload fatigue problem according to the test process, and managing the residual life of the test piece based on a Miner linear accumulated damage criterion:
guarantee
The threshold is obtained from "1/life dispersion factor".
The alloy part life evaluation and management system of an embodiment of the present invention is explained below with reference to fig. 4.
The system comprises a load-holding test module 401, a load-holding test result processing module 403, a finite element analysis module 402, a load-holding fatigue life calculation module 404, and a life evaluation and management module 405.
The division of the modules is only one logical function division, and other division manners may be available in actual implementation, and for example, a plurality of modules may be combined or integrated into another module, or some features may be omitted or not executed.
The modules described as separate parts may or may not be physically separate, and the parts described as modules may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of them can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
The holding test module 401 develops a titanium alloy sample holding test to obtain an-N curve, which includes holding peak loads and holding fatigue lives (time) of the titanium alloy samples at different temperatures, and draws the fatigue lives
-N curve,
-N curve and
-N curve.
The load-holding test result processing module 403 communicates with the load-holding test module 401, receives the-N curve from the load-holding test module 401, and performs fitting interpolation on the-N curve to obtain a Coffin-Mason equation at a corresponding temperature.
The finite element analysis module 402 establishes a titanium alloy part finite element model to carry out finite element analysis on the titanium alloy part, loads and boundary conditions in each actual working state or test state to carry out finite element calculation, takes the stress maximum node in the calculation result as a dangerous point under the working condition, and extracts the stress state and the temperature of the dangerous point.
The overload fatigue life calculation module 404 is in communication with the overload test result processing module 403 and the finite element analysis module 402, receives the analysis processing results from the overload test result processing module and the finite element analysis module, acquires a strain history based on a rain flow counting method and a Neuber method elastoplasticity correction, and acquires the overload fatigue life of the titanium alloy part by combining with a Coffin-Mason equation after interpolation.
The service life evaluation and management module 405 receives the calculation result from the self-loading fatigue life calculation module 404, obtains the theoretical operating time ti _ design under each working condition needing to consider the loading fatigue problem according to the design load spectrum of the titanium alloy part and counts the actual operating time ti _ test of the titanium alloy part under each working condition needing to consider the loading fatigue problem according to the test history, and performs the loading fatigue life evaluation and management of the titanium alloy part.
The system may further include a display module 406 that displays the evaluation results to the user.
The foregoing flowchart and block diagrams illustrate the architecture, functionality, and operation of possible implementations of systems, methods according to embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved.
The technical solution of the present application, or portions thereof that substantially contribute to the prior art, may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to perform all or part of the steps of the method according to the embodiments of the present application. The foregoing storage medium includes: u disk, removable hard disk, read only memory, random access memory, magnetic or optical disk, etc. for storing program codes.
The method and the system for evaluating and managing the service life of the titanium alloy part consider the influence of the load retention time of the part under the peak load, and realize the efficient evaluation and management of the service life of the titanium alloy part in the service process. The safety and the reliability of the aircraft engine are improved, and safety accidents can be effectively prevented. The method of the invention can also be used for guiding the fatigue life evaluation and the load-holding life management of alloy parts in other engines with load-holding effect alloy materials.
The above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; those of ordinary skill in the art will understand that: modifications can be made to the technical solutions described in the foregoing embodiments, or some or all of the technical features can be equivalently replaced; the modifications and the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application, and all of the technical solutions are intended to be covered by the scope of the present application.
Claims (10)
1. An alloy part life evaluation management method comprises the following steps:
carrying out a load holding test on the alloy part sample to obtain a-N curve;
fitting interpolation is carried out on the obtained-N curve;
carrying out finite element analysis on the alloy part to obtain the stress state and the temperature of a dangerous point;
combining the obtained-N curve and the result of the finite element analysis to obtain the load-holding fatigue life of the alloy part; and
and obtaining theoretical running time according to a design load spectrum, and carrying out load-holding fatigue life evaluation on the alloy part based on a Miner linear accumulated damage criterion.
2. The method of claim 1, further comprising:
and counting the actual running time of the alloy part according to the test process, and managing the residual service life of the alloy part based on a Miner linear accumulated damage criterion.
3. The method of claim 1, wherein the step of performing a holding test on the alloy part sample to obtain an-N curve further comprises:
determining the single-cycle load-holding time of the rectangular wave load-holding test;
carrying out a rectangular wave load-holding test on the alloy part sample to obtain the load-holding fatigue life of the alloy part sample under different load-holding peak loads and different temperatures, and drawing
-N curve,
-N curve and
-N curve.
4. The method of claim 1, wherein the step of fitting interpolation to the acquired-N curve further comprises:
according to the temperature
-N curve and
-N curves, using a log-log linear relationship, fitting by a quadratic equation of unity to obtain parametric equations at different temperatures:
will be parameter
、
、
And
and interpolating the temperature and substituting the temperature into a Coffin-Manson equation to obtain the Coffin-Manson equation at the corresponding temperature.
5. The method of claim 1, wherein performing a finite element analysis on the alloy part to obtain the stress state and temperature at the risk point further comprises:
establishing a finite element model of the alloy part;
carrying out finite element calculation on the loading load and the boundary condition; and
taking the stress maximum node in the calculation result as a dangerous point, and extracting the stress of the dangerous point
And the corresponding temperature Ti.
6. The method of claim 5, wherein the step of obtaining the dwell fatigue life of the alloy part in combination with the obtained-N curve and the results of the finite element analysis further comprises:
according to the stress of the danger point
And corresponding to the temperature Ti, acquiring a strain history based on a rain flow counting method and a Neuber method elastic-plastic correction, and acquiring the load-holding fatigue life of the alloy part by combining a Coffin-Mason equation after interpolation.
7. The method of claim 1, wherein the step of performing an in-service fatigue life assessment on the alloy part further comprises:
require that
The threshold is derived from "1/life dispersion factor".
8. The method of claim 2, wherein managing the remaining life of the alloy part further comprises:
guarantee
The threshold is derived from "1/life dispersion factor".
9. An alloy part life assessment management system comprising:
the load-holding test module is used for carrying out a load-holding test on the sample of the alloy part and acquiring a-N curve;
a load-holding test result processing module for performing fitting interpolation on the-N curve from the load-holding test module;
the finite element analysis module is used for carrying out finite element analysis on the alloy part and acquiring the stress state and the temperature of a dangerous point;
the load-holding fatigue life calculation module is used for receiving the analysis result from the finite element analysis module and the processing result from the load-holding test result processing module and calculating the fatigue life; and
a life evaluation and management module for evaluating and managing the life of the alloy part.
10. The system of claim 9, wherein:
the load-holding test module determines the single cycle load-holding time of a rectangular wave load-holding test and carries out a rectangular wave load-holding test on the alloy part sample to obtain the load-holding fatigue of the alloy part sample under different load-holding peak loads and different temperaturesLabor life and drawing
-N curve,
-N curve and
-an N-curve;
the load-holding test result processing module is used for processing the load-holding test result according to different temperatures
-N curve and
-N curves, using a log-log linear relationship, fitting by a quadratic equation of unity to obtain parametric equations at different temperatures:
will be parameter
、
、
And
interpolating the temperature and substituting the temperature into a Coffin-Mason equation to obtain the Coffin-Mason equation at the corresponding temperature;
the finite element analysis module establishes a finite element model of the alloy part, loads and boundary stripsFinite element calculation is carried out on the part, the maximum stress node in the calculation result is taken as a dangerous point, and the stress of the dangerous point is extracted
And the corresponding temperature Ti;
the load-holding fatigue life calculation module calculates the stress according to the dangerous points
And corresponding temperature Ti, acquiring a strain history based on a rain flow counting method and a Neuber method elastic-plastic correction, and acquiring the load-holding fatigue life of the alloy part by combining a Coffin-Mason equation after interpolation; and
the life evaluation and management module is based on a formula
And performing life evaluation and management, wherein the threshold value is obtained by '1/life dispersion coefficient'.
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