CN107895088A - A kind of aeroengine combustor buring room life-span prediction method - Google Patents
A kind of aeroengine combustor buring room life-span prediction method Download PDFInfo
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Abstract
The present invention relates to a kind of aeroengine combustor buring room life-span prediction method, including：Aeroengine combustor buring room CFD is analyzed；Aeroengine combustor buring room elastoplasticity statics Analysis；The loading spectrum establishment of aeroengine combustor buring room；The matrix alloy fatigue test piece design of aeroengine combustor buring room：Design Hastelloy creep-fatigue experiments experimental standard part；The matrix alloy Fatigue Testing Loads design of aeroengine combustor buring room；The matrix alloy experiment of aeroengine combustor buring room；The method being combined using SVMs (SVM) with genetic algorithm (GA), establish aeroengine combustor buring room matrix alloy damage forecast model；The life prediction of aeroengine combustor buring room.
Description
Technical field
The present invention relates to a kind of aeroengine combustor buring room life-span prediction method
Background technology
To improve the thrust-weight ratio of modern aeroengine, the operating temperature more and more higher of aero-engine, aero-engine
Hot junction part heat load is increasing, and this becomes increasingly conspicuous to aero-engine hot-end component fatigue reliability sex chromosome mosaicism.Aviation is sent out
Motivation combustion chamber is the crucial hot-end component of aero-engine, and its fatigue reliability is safe for operation to aircraft certification to be had to pass weight
The influence wanted, Accurate Prediction is carried out to the aeroengine combustor buring room life-span to be had to development aero-engine hot-end component defect theory
Important scientific meaning, to ensureing flight safety and improving ground maintenance efficiency and economy have engineering application value.
Limited by civil aviaton's regulation safe for operation and experimental cost, it is difficult to aviation is reproduced by real engine running experiment and sent out
The severe Service Environment in motivation combustion chamber.Existing aeroengine combustor buring room life-span prediction method is that combustion chamber is applied mostly
Simple thermal boundary condition carries out the stress/strain distribution that finite element analysis obtains combustion chamber, base to aeroengine combustor buring room
It is pre- in Maansson-Coffin formula or the Maansson-Coffin formula of amendment to be carried out to aeroengine combustor buring room the life-span
Survey [1,2,3].Because aeroengine combustor buring room actual operating mode is complicated and changeable, simple thermal boundary condition can not accurately again
The severe working environment in existing aeroengine combustor buring room；And there are some researches show[4,5], combustion chamber MATRIX CRACKING failure mainly by
Cause in fatigue and the reciprocation of creep, the Maansson-Coffin formula of Maansson-Coffin formula or amendment all without
Existing influence of the creep to the aeroengine combustor buring room life-span of body of laws.Also there are some scholars to propose some at present and be based on damage mechanics
Or the creep-fatigue life model of fracture mechanics[6,7], but these models need to enter the empirical parameter in model by experiment
Row fitting, because the influence factor in creep-fatigue life-span is more, establishing accurate life model needs to carry out substantial amounts of fatigue examination
Test, this causes, and the test period is long, experimental cost is high；And because aeroengine combustor buring room load is more complicated, these models are difficult
To carry out accurate life prediction to aeroengine combustor buring room.Therefore, in aeroengine combustor buring room life prediction research
Permitted to need to propose that a kind of system, comprehensive method improve aeroengine combustor buring room life prediction precision, so as to be sent out for aviation
The design of motivation is modified and maintaining provides guidance.
Bibliography
[1] the easily quiet that admires is navigated based on the burner inner liner Thermal Fatigue of heat-fluid-wall interaction and life prediction [D] Beijing Aviations
Its university, 2014.
[2] Geng little Liang, Guo Yunqiang, Zhang Keshi, burner inner liners Thermal Fatigue and life estimation [J] mechanical strengths are waited,
2007,29(2):305-309.
[3] Yi Hui toroidal combustion chambers burner inner liner intensity life-span technical research [D] Nanjing Aero-Space University, 2008.
[4]Lv F,Li Q,Fu G.Failure analysis of an aero-engine combustor liner
[J].Engineering Failure Analysis,2010,17(5):1094-1101.
[5]Kiewel H,Aktaa J,Munz D.Advances in the Inelastic Failure Analysis
of Combustor Structures[M]//High Intensity Combustors-Steady Isobaric
Combustion.2005:375-390.
[6]Sham T L,Jetter R I,Wang Y.Elevated Temperature Cyclic Service
Evaluation Based on Elastic-Perfectly Plastic Analysis and Integrated Creep-
Fatigue Damage[C]//ASME 2016Pressure Vessels and Piping Conference.2016:
V01BT01A022.
[7]Kauppila P,Kouhia R,J,et al.A continuum damage model for
creep fracture and fatigue analyses[J].Procedia Structural Integrity,2016,2:
887-894.
The content of the invention
It is an object of the invention to provide a kind of more accurately aeroengine combustor buring room life-span prediction method；The present invention passes through
CFD analyses obtain the distribution of aeroengine combustor buring room temperature load；By nonlinear static analysis, aero-engine is obtained
Combustion chamber stress/strain distribution, establishes aeroengine combustor buring room military service loading spectrum；Set based on optimal Latin hypercube design method
Meter and the matrix material fatigue test of aeroengine combustor buring room；It is combined using SVMs (SVM) with genetic algorithm (GA)
Method, aeroengine combustor buring room matrix alloy damage forecast model is established, with reference to aeroengine combustor buring room military service load
Spectrum carries out accurate life prediction to aeroengine combustor buring room, and technical solution of the present invention is as follows：
A kind of aeroengine combustor buring room life-span prediction method, comprises the following steps：
(1) aeroengine combustor buring room CFD is analyzed：The typical condition of aero-engine is obtained, typical condition is obtained and issues
The engine operating state parameter such as combustion chamber gateway aerodynamic parameter and fuel consumption in the motivation course of work；To aeroplane engine
Machine physical model carries out non-contact 3-D scanning, obtains cloud data and generates engines three-dimensional model, with reference to engine
Structure chooses suitable computational fields to threedimensional model, discrete to computational fields progress grid, considers burned in engine working process
Journey, hot and cold air blending procedure, fluid domain and solid domain diabatic process, real test data is surveyed using test bay CFD model is set
Boundary condition, CFD simulations are carried out to the complex process carried out in combustion chamber in engine working process, obtain combustion chamber matrix
The distribution of temperature, pressure parameter；
(2) aeroengine combustor buring room elastoplasticity statics Analysis：Carry out aeroengine combustor buring room matrix material high temperature
Tension test, aeroengine combustor buring room matrix alloy load-deformation curve under different temperatures is obtained, establish aero-engine combustion
Burn room matrix alloy elasto-plastic Constitutive Model；The temperature that CFD is calculated is as load；With reference to aeroengine combustor buring room base
Body alloy elasto-plastic Constitutive Model；According to combustion chamber practical set situation, constraint combustion chamber matrix obtains each operating mode to the free degree
Lower aeroengine combustor buring room stress/strain distribution；
(3) aeroengine combustor buring room loading spectrum is worked out：Each operating mode time accounting of aircraft is obtained, with reference to step (1), step
(2) analysis result obtains the corresponding relation of aeroengine combustor buring room each position temperature-strain-time, works out aeroplane engine
Machine combustion chamber loading spectrum；
(4) matrix alloy fatigue test piece in aeroengine combustor buring room designs：It is real to design the experiment of Hastelloy creep-fatigue
Test standard component；
(5) matrix alloy Fatigue Testing Loads in aeroengine combustor buring room design：Using optimal Latin hypercube design side
Method, carried in temperature, mean strain, strain ratio, guarantor in multiple dimensions such as time, loading velocity, uniformly orthogonally contrived experiment carries
Lotus, experiment number is reduced as far as on the premise of ensureing that load is uniformly filled in each dimensional space of influence factor；
(6) aeroengine combustor buring room matrix alloy is tested：Aviation hair is carried out on the premise of step (4) and step (5)
The matrix alloy fatique testing at elevated temperature of motivation combustion chamber, obtain different temperatures, mean strain, strain ratio, stretching guarantor's load time, compression
Protect and carry aeroengine combustor buring room matrix alloy fatigue life under time, loading velocity, obtain the lower aviation hair of single test circulation
Motivation combustion chamber matrix alloy damage Dd；
(7) method being combined using SVMs (SVM) with genetic algorithm (GA), establishes aeroengine combustor buring room
Matrix alloy damage forecast model, method are as follows：Selection temperature, mean strain, strain ratio, stretching are protected and carry the time, compression guarantor carries
Time, loading velocity form initial characteristicses subset, are rejected using the feature subset selection method based on genetic algorithm and aviation is sent out
Motivation combustion chamber matrix alloy damage forecast model prediction accuracy influences small characteristic factor, obtains optimal feature subset；Using
Kernel function of the RBF as aeroengine combustor buring room matrix alloy damage forecast model prediction model；Calculated using heredity
Method optimizes the character subset and SVMs parameter of aeroengine combustor buring room matrix alloy damage forecast model simultaneously；
(8) aeroengine combustor buring room life prediction：Model is obtained using the loading spectrum that step (3) obtains as step (7)
Input quantity, obtain the fatigue damage D of the lower aeroengine combustor buring room of circulation of rising and falling every timei, calculate aeroengine combustor buring room
Total damage D, when D reaches 1, it is believed that parts fail, and fatigue rupture occurs, and now n is aeroengine combustor buring room hair
Raw cycle-index of rising and falling when destroying, the cycle-index of rising and falling when aeroengine combustor buring room is destroyed, which is multiplied by single, rises and falls and follows
The working time of ring is working time when aeroengine combustor buring room is destroyed.
Brief description of the drawings
Fig. 1 CFD analogue technique routes
The optimal Latin Hypercube Samplings of Fig. 2
Fig. 3 GA-SVM flow charts
Embodiment
The present invention will be described with reference to the accompanying drawings and examples.
(1) aeroengine combustor buring room CFD is analyzed：Aircraft QAR data can be analyzed, obtain the allusion quotation of aero-engine
Type operating mode, test run is carried out to engine on test bay, obtain under typical condition combustion chamber gateway in engine working process
The engine operating state parameter such as aerodynamic parameter and fuel consumption；CFM56-3 engines physical model is carried out contactless
3-D scanning, obtain CFM56-3 engines cloud data and simultaneously generate engines three-dimensional model, with reference to engine structure to three-dimensional
Model carries out Rational Simplification and chooses suitable computational fields, discrete to computational fields progress grid, considers to fire in engine working process
Burning process, hot and cold air blending procedure, fluid domain and solid domain diabatic process, real test data is surveyed using test bay CFD is set
Model boundary condition, CFD simulations are carried out to the complex process carried out in combustion chamber in engine working process, obtain combustion chamber base
The distribution of the temperature, pressure and other parameters of body.Particular technique route is as shown in Figure 1.
(2) aeroengine combustor buring room elastoplasticity statics Analysis：Aero-engine is carried out based on GB/T228.2-2015
Combustion chamber matrix material high temperature tension test, it is bent to obtain aeroengine combustor buring room matrix alloy stress-strain under different temperatures
Line, establish aeroengine combustor buring room matrix alloy elasto-plastic Constitutive Model；The temperature that CFD is calculated is as load；Knot
Close aeroengine combustor buring room matrix alloy elasto-plastic Constitutive Model；According to combustion chamber practical set situation, combustion chamber base is constrained
Body is solved by Finite Element to combustion chamber matrix equation in a basic balance by MSC.Nastran, obtained to the free degree
Aeroengine combustor buring room stress/strain is distributed under each operating mode.
(3) aeroengine combustor buring room loading spectrum is worked out：Statistical analysis is carried out to aircraft QAR data, when obtaining each operating mode
Between accounting, obtain aeroengine combustor buring room each position temperature-strain-time with reference to step (1), the analysis result of step (2)
Corresponding relation, establishment aeroengine combustor buring room loading spectrum.
(4) matrix alloy fatigue test piece in aeroengine combustor buring room designs：With reference to GB/T26077-2010, GB/
T228.2-2015, ASTM E739, HB5217-1982 etc. are both at home and abroad and industry standard design Hastelloy creep-fatigue is tested
Experimental standard part.
(5) matrix alloy Fatigue Testing Loads in aeroengine combustor buring room design：Temperature, mean strain, strain ratio, guarantor carry
Time, loading velocity have considerable influence to aeroengine combustor buring room matrix alloy fatigue life, must take into consideration in experimentation
These factors.Traditional means of experiment can cause experiment number can be with the exponentially form growth of each variable level；The present invention is using most
Excellent Latin hypercube design method, carried in temperature, mean strain, strain ratio, guarantor in multiple dimensions such as time, loading velocity,
Even orthogonally contrived experiment load, ensureing load on the premise of each dimensional space of influence factor uniformly filling as much as possible
Reduce experiment number.Optimal Latin Hypercube Sampling schematic diagram is as shown in Figure 2.
(6) aeroengine combustor buring room matrix alloy is tested：Aviation hair is carried out on the premise of step (4) and step (5)
The matrix alloy fatique testing at elevated temperature of motivation combustion chamber, obtain different temperatures, mean strain, strain ratio, stretching guarantor's load time, compression
Protect and carry aeroengine combustor buring room matrix alloy fatigue life under time, loading velocity, obtaining single test by formula (1) circulates
Lower aeroengine combustor buring room matrix alloy damage.
In formula：DdCirculate and damage for single test, N is test cycle number when test specimen destroys.
(7) aeroengine combustor buring room matrix alloy damage forecast model：This research is using SVMs (SVM) with losing
The method that propagation algorithm (GA) is combined, establish aeroengine combustor buring room matrix alloy damage forecast model.SVM regression models are special
It is substantially the search characteristics space under certain required precision to levy subset selection, to obtain the searching method closest to optimal solution.
The Rational choice of character subset is most important to establishing accurate aeroengine combustor buring room matrix alloy damage forecast model：It is special
The factor of sign subset selection can excessively cause the computational load of whole model system to increase, calculate pressure increase, cause to calculate easily
Endless loop is absorbed in, model is directly contributed and establishes failure, but the factor of feature subset selection is crossed can not embody extraneous factor at least
Influence to aeroengine combustor buring room matrix alloy damage forecast model so that model prediction accuracy is low.The present invention chooses temperature
Degree, mean strain, strain ratio, stretching are protected and carry the time, compression guarantor carries the time, loading velocity forms initial characteristicses subset, using base
Rejected in the feature subset selection method of genetic algorithm to aeroengine combustor buring room matrix alloy damage forecast model prediction essence
Degree influences small characteristic factor, obtains optimal feature subset.In the present invention, using RBF as aeroengine combustor buring
The kernel function of room matrix alloy damage forecast model prediction model.Aeroengine combustor buring room base is optimized using genetic algorithm simultaneously
The character subset and SVMs parameter of body alloy damage forecast model.GA-SVM algorithm flow charts are as shown in Figure 3.
(8) aeroengine combustor buring room life prediction：Model is obtained using the loading spectrum that step (3) obtains as step (7)
Input quantity, obtain the fatigue damage D of the lower aeroengine combustor buring room of circulation of rising and falling every timei, aeroengine combustor buring room is always damaged
Hinder and be：
When D reaches 1, it is believed that parts fail, and fatigue rupture occurs, and now n is aeroengine combustor buring room hair
Raw cycle-index of rising and falling when destroying, the cycle-index of rising and falling when aeroengine combustor buring room is destroyed, which is multiplied by single, rises and falls and follows
The working time of ring is working time when aeroengine combustor buring room is destroyed.
Claims (1)
1. a kind of aeroengine combustor buring room life-span prediction method, comprises the following steps：
(1) aeroengine combustor buring room CFD is analyzed：The typical condition of aero-engine is obtained, obtains engine under typical condition
The engine operating state parameter such as combustion chamber gateway aerodynamic parameter and fuel consumption in the course of work；It is real to aero-engine
Body Model carries out non-contact 3-D scanning, obtains cloud data and generates engines three-dimensional model, with reference to the structure of engine
Suitable computational fields are chosen to threedimensional model, it is discrete that computational fields are carried out with grid, considers combustion process in engine working process, cold
Thermal current blending procedure, fluid domain and solid domain diabatic process, real test data is surveyed using test bay CFD model perimeter strip is set
Part, the complex process progress CFD simulations to being carried out in combustion chamber in engine working process, the temperature of acquisition combustion chamber matrix,
The distribution of pressure parameter；
(2) aeroengine combustor buring room elastoplasticity statics Analysis：Carry out aeroengine combustor buring room matrix material drawing by high temperature
Experiment, aeroengine combustor buring room matrix alloy load-deformation curve under different temperatures is obtained, establishes aeroengine combustor buring room
Matrix alloy elasto-plastic Constitutive Model；The temperature that CFD is calculated is as load；Closed with reference to aeroengine combustor buring room matrix
Golden elasto-plastic Constitutive Model；According to combustion chamber practical set situation, constraint combustion chamber matrix is obtained and navigated under each operating mode to the free degree
Empty engine chamber stress/strain distribution；
(3) aeroengine combustor buring room loading spectrum is worked out：Each operating mode time accounting of aircraft is obtained, with reference to step (1), step (2)
Analysis result obtain the corresponding relation of aeroengine combustor buring room each position temperature-strain-time, establishment aero-engine combustion
Burn room loading spectrum；
(4) matrix alloy fatigue test piece in aeroengine combustor buring room designs：Design Hastelloy creep-fatigue experiments experiment mark
Quasi- part；
(5) matrix alloy Fatigue Testing Loads in aeroengine combustor buring room design：Using optimal Latin hypercube design method,
Temperature, mean strain, strain ratio, protect and carry the time, in multiple dimensions such as loading velocity, uniformly orthogonally contrived experiment load,
Ensure that load is reduced as far as experiment number on the premise of each dimensional space of influence factor uniformly filling；
(6) aeroengine combustor buring room matrix alloy is tested：Aero-engine is carried out on the premise of step (4) and step (5)
Combustion chamber matrix alloy fatique testing at elevated temperature, acquisition different temperatures, mean strain, strain ratio, stretching are protected and carry the time, compression guarantor carries
Aeroengine combustor buring room matrix alloy fatigue life under time, loading velocity, obtain the lower aero-engine of single test circulation
Combustion chamber matrix alloy damage Dd；
(7) method being combined using SVMs (SVM) with genetic algorithm (GA), establishes aeroengine combustor buring room matrix
Alloy damage forecast model, method are as follows：Selection temperature, mean strain, strain ratio, stretching are protected and carry the time, compression guarantor carries the time,
Loading velocity forms initial characteristicses subset, is rejected using the feature subset selection method based on genetic algorithm and aero-engine is fired
Burning room matrix alloy damage forecast model prediction accuracy influences small characteristic factor, obtains optimal feature subset；Using radial direction base
Kernel function of the function as aeroengine combustor buring room matrix alloy damage forecast model prediction model；Using genetic algorithm simultaneously
Optimize the character subset and SVMs parameter of aeroengine combustor buring room matrix alloy damage forecast model；
(8) aeroengine combustor buring room life prediction：The defeated of model is obtained using the loading spectrum that step (3) obtains as step (7)
Enter amount, obtain the fatigue damage D of the lower aeroengine combustor buring room of circulation of rising and falling every timei, calculate aeroengine combustor buring room and always damage
Hinder D, when D reaches 1, it is believed that parts fail, and fatigue rupture occurs, and now n is that aeroengine combustor buring room occurs to break
The cycle-index of rising and falling of bad when, the cycle-index of rising and falling when aeroengine combustor buring room is destroyed are multiplied by single and risen and fallen circulation
Working time is working time when aeroengine combustor buring room is destroyed.
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