CN108038320A - A kind of multiple response face method for calculating mistuned bladed disk vibration reliability - Google Patents
A kind of multiple response face method for calculating mistuned bladed disk vibration reliability Download PDFInfo
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- CN108038320A CN108038320A CN201711388954.4A CN201711388954A CN108038320A CN 108038320 A CN108038320 A CN 108038320A CN 201711388954 A CN201711388954 A CN 201711388954A CN 108038320 A CN108038320 A CN 108038320A
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Abstract
A kind of multiple response face method for calculating mistuned bladed disk vibration reliability, its detailed process are as follows：Leaf dish off resonance is simulated by varying the elasticity modulus of each blade, determines to influence the factor of leaf dish vibration reliability；Structural loads in influence factor are analyzed；Vibration-mode analysis, instantaneous response analysis are carried out to leaf dish under the influence of structural loads, obtain the basic parameter of leaf dish vibration reliability analysis；Build the multiple response face method mathematical model of mistuned bladed disk vibration reliability analysis；The analysis for carrying out reliability is vibrated to mistuned bladed disk using multiple response face method；Validation verification is carried out to multiple response face method.The method of the present invention calculating speed is fast, precision is high, can intuitively show the variation relation of output response, and a kind of new way is provided for Reliability Engineering analysis.
Description
The present invention relates to a kind of multiple response face method for calculating mistuned bladed disk vibration reliability, belong to reliability theory technology
Field.
Background technology
The leaf dish of aero-engine is subject to aerodynamic loading, temperature loading, mechanical load etc. to influence, and the vibration suffered by it carries
Lotus is continuously increased, and failure is more and more caused by vibration, and aero-engine bladed-disk assemblies usually have a Cyclic Symmetry, but due to
The reasons such as mismachining tolerance, material character, service wear, the characteristic of each leaf dish are inevitably present fine difference, i.e. off resonance,
The Cyclic Symmetry that off resonance destroys structure causes its vibrational energy to concentrate on one or several blades, makes shaking for these blades
Width reaches several times of other blade amplitudes, causes the stress failures of local blade, therefore for the vibration reliability of mistuned bladed disk
Probability analysis is very necessary.
Fail-safe analysis widely uses in fields such as civil construction, water conservancies, in recent years applied to mechanical structure can
By fields such as property analysis, sensitivity analysis, the analysis of empty engine leaf dish vibration reliability is a kind of complicated dynamic probability point
Analysis, is also actually a random process problem, with traditional response phase method to aero-engine bladed-disk assemblies vibration reliability
Calculation amount it is still very big and inefficient, it is impossible to meet the needs of its precision and efficiency.
The content of the invention
The purpose of the present invention is：Off resonance factor is considered in the analysis of leaf dish vibration reliability, considers to influence leaf dish vibration
The randomness of reliability external load and the randomness of structural parameters.The mode localization of mistuned bladed disk is obtained by analysis and is shaken
Dynamic response localizes, when carrying out the calculating of mistuned bladed disk vibration reliability, influencing each other between consideration fluid-wall interaction field and material
Expect attribute, for the deficiency of Traditional calculating methods, propose a kind of multiple response for calculating aero-engine leaf dish vibration reliability
Face method, ensures its precision, improves its calculating speed and efficiency,
The present invention considers the off resonance situation of leaf dish, it is proposed that a kind of multiple response face for calculating mistuned bladed disk vibration reliability
Method, its detailed process are as follows：
A, blade off resonance is simulated by varying the elasticity modulus of each blade；
B, determine the basic parameter of leaf dish off resonance fail-safe analysis as stochastic inputs variable；
C, transmittance process fluid-wall interaction load in influence factor is analyzed；
D, vibration-mode analysis is carried out to mistuned bladed disk under fluid-wall interaction loading effect, transient dynamic analysis obtains leaf dish
The basic parameter of vibration reliability analysis；
E, the multiple response face method mathematical model of mistuned bladed disk vibration reliability analysis is built；
F, the analysis of vibration reliability is carried out to mistuned bladed disk using multiple response face method；
G, validation verification is carried out to multiple response face method.
A kind of multiple response face method of the calculating mistuned bladed disk vibration reliability, in the step a, bladed-disk assemblies
Off resonance be mostly derived from various factors caused by interlobate difference, the mistake of blade is simulated by varying paddles elastomeric modulus
It is humorous, and off resonance is accounted for as Random Effect factor.
The multiple response face method of a kind of calculating mistuned bladed disk vibration reliability, in the step b, according to starting
Machine leaf dish Vibration Analysis, determines that influencing the external load factor of mistuned bladed disk vibration reliability and structural behaviour itself joins
Number.
A kind of multiple response face method of calculating mistuned bladed disk vibration reliability, in the step c, utilizes
The Pneumatic pressure data transfer that ANSYS software inhouses program is obtained fluid analysis by interpolation method utilizes list to bladed-disk assemblies
First shape function obtains the numerical value needed for analysis object with Displacement of elemental node, as input load, passes through finite element software
Excuse be delivered in leaf dish, the analysis of structure field is carried out to it by unit shape function.
The multiple response face method of a kind of calculating mistuned bladed disk vibration reliability, in the step d, in step c
Under middle fluid-wall interaction loading effect, vibration-mode analysis is carried out to leaf dish, qualitative description is carried out to mode localization, passes through wink
State dynamic analysis, calculates deformation, stress and strain value that each blade changes over time, is mistuned bladed disk vibration reliability
Calculate and parameter is provided.
A kind of multiple response face method of calculating mistuned bladed disk vibration reliability, in the step e, considers blade
Off resonance factor and load dynamic, using Latin Hypercube Sampling technology to stochastic inputs variable carry out small lot sampling,
Corresponding output response is calculated according to sample point, the required sample point of fit equation is obtained, is passed through based on least square method
MATLAB matrix labotstories tool box carries out regression analysis to data and establishes multiple response face mathematical model.
A kind of multiple response face method of calculating mistuned bladed disk vibration reliability, in the step f, use is multiple
Response phase method carries out mistuned bladed disk the analysis of vibration reliability, and program and the multiple response of Calculation of Reliability are write with MATLAB
Face method mathematical model carries out the calculating of off resonance vibration reliability.
The multiple response face method of a kind of calculating mistuned bladed disk vibration reliability, in the step g, to multiple sound
Answer face method to carry out validation verification, i.e., under identical design conditions, using generally acknowledged reliability calculation method Monte Carlo Method as
Benchmark, and response phase method compare.
The present invention has the advantages that compared with prior art：
1. the present invention considers the off resonance situation of aero-engine leaf dish, closer to the actual conditions of engine work, draw
Data and characteristic are more nearly reality, intuitively react the changing rule between each output response, each output was responded with the time
Changing rule, under conditions of meeting precision, significantly improves computational efficiency, reduces and calculate cost, effectively solve background technology
Described in the problem of, this method can use MATLAB in existing sort program by data-interface file realize to finite element
Analysis software ANSYS directly invokes, and using MATLAB easily programing function and ANSYS analytic functions, facilitates engineer to make
With.
Brief description of the drawings
Fig. 1 is the fail-safe analysis flow chart that mistuned bladed disk vibrates multiple response face method.
Embodiment
Embodiment 1
A kind of multiple response face method of calculating mistuned bladed disk vibration reliability, comprises the following steps：
A, blade off resonance is simulated by varying the elasticity modulus of each blade；
B, determine the basic parameter of leaf dish off resonance fail-safe analysis as stochastic inputs variable；
C, transmittance process fluid-wall interaction load in influence factor is analyzed；
D, under fluid-wall interaction loading effect to leaf dish carry out vibration-mode analysis, instantaneous response analysis obtain leaf dish vibration can
By the basic parameter of property analysis；
E, the multiple response face method mathematical model of leaf dish vibration reliability analysis is built；
F, the analysis of vibration reliability is carried out to leaf dish using multiple response face method；
G, validation verification is carried out to multiple response face method.
Embodiment 2
The multiple response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step a, leaf dish
The off resonance of structure is mostly derived from interlobate difference caused by various factors, and blade is simulated by varying paddles elastomeric modulus
Off resonance, and off resonance is taken into account as Random Effect factor.
Embodiment 3
The multiple response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step b, according to
Engine leaf dish Vibration Analysis, determines to influence the external load factor and structural behaviour itself of mistuned bladed disk vibration reliability
Parameter.
Embodiment 4
The multiple response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step c, utilizes
The Pneumatic pressure data transfer that ANSYS software inhouses program is obtained fluid analysis by interpolation method utilizes list to bladed-disk assemblies
First shape function obtains the numerical value needed for analysis object with Displacement of elemental node, as input load, passes through finite element software
Excuse be delivered in leaf dish, the analysis of structure field is carried out to it by unit shape function.
Embodiment 5
The double-response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step d, in step
In rapid c under fluid-wall interaction loading effect, vibration-mode analysis is carried out to leaf dish, qualitative description is carried out to mode localization, is passed through
Transient dynamic analysis, calculates deformation, stress and strain value that each blade changes over time, is mistuned bladed disk vibration reliability
Calculating provide parameter.
Embodiment 6
The double-response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step e, considers
The off resonance factor of blade and the dynamic of load, small lot pumping is carried out using Latin Hypercube Sampling technology to stochastic inputs variable
Sample, is calculated corresponding output response according to sample point, obtains the required sample point of fit equation, led to based on least square method
Cross MATLAB matrix labotstories tool box and multiple response face mathematical model is established to data progress regression analysis.
Embodiment 7
The double-response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step f, uses
Multiple response face method carries out mistuned bladed disk the analysis of vibration reliability, and the program of Calculation of Reliability and multiple is write with MATLAB
Response phase method mathematical model carries out the calculating of off resonance vibration reliability.
Embodiment 8
The multiple response face method of calculating mistuned bladed disk vibration reliability according to embodiment 1, in the step g, to more
Weight response phase method carries out validation verification, i.e., under identical design conditions, with generally acknowledged reliability calculation method Monte Carlo
On the basis of method, and response phase method compares.
Claims (5)
1. a kind of multiple response face method for calculating aero-engine mistuned bladed disk vibration reliability, it is characterised in that including following
Step：
A, blade off resonance is simulated by varying the elasticity modulus of each blade；
B, determine the basic parameter of leaf dish off resonance fail-safe analysis as stochastic inputs variable；
C, transmittance process fluid-wall interaction load in influence factor is analyzed；
D, vibration-mode analysis is carried out to mistuned bladed disk under fluid-wall interaction loading effect, transient dynamic analysis obtains leaf dish
The basic parameter of vibration reliability analysis；
E, the multiple response face method mathematical model of mistuned bladed disk vibration reliability analysis is built；
F, the analysis of vibration reliability is carried out to mistuned bladed disk using multiple response face method；
G, validation verification is carried out to multiple response face method.
2. a kind of multiple response face method for calculating aero-engine mistuned bladed disk vibration reliability according to claim 1,
In the step a, the off resonance of bladed-disk assemblies is mostly derived from interlobate difference caused by various factors, by varying blade bullet
Property modulus is taken into account off resonance as Random Effect factor to simulate the off resonance of blade.
3. according to a kind of multiple response face method of calculating aero-engine mistuned bladed disk vibration reliability described in claim 1, institute
In the step c stated, using ANSYS software inhouses program by interpolation method by the Pneumatic pressure data transfer that fluid analysis obtains to
Bladed-disk assemblies, range site shape function and Displacement of elemental node obtain the numerical value needed for analysis object, as input load,
It is delivered to by the excuse of finite element software in leaf dish, the analysis of structure field is carried out to it by unit shape function.
4. according to a kind of multiple response face method of calculating aero-engine mistuned bladed disk vibration reliability described in claim 1, institute
In the step d stated, in step c under fluid-wall interaction loading effect, vibration-mode analysis is carried out to leaf dish, to mode localization
Qualitative description is carried out, by transient dynamic analysis, deformation, stress and strain value that each blade changes over time is calculated, is
The calculating of mistuned bladed disk vibration reliability provides parameter.
5. according to a kind of multiple response face method of calculating aero-engine mistuned bladed disk vibration reliability described in claim 1, institute
In the step e stated, the off resonance factor of blade and the dynamic of load are considered, using Latin Hypercube Sampling technology to stochastic inputs
Variable carries out small lot sampling, calculates corresponding output response according to sample point, obtains the required sample point of fit equation,
Regression analysis is carried out to data by MATLAB matrix labotstories tool box based on least square method and establishes multiple response face mathematics
Model.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109359392A (en) * | 2018-10-19 | 2019-02-19 | 北京化工大学 | A kind of turbo blade Stress Calculation method using non-cpntact measurement |
| CN109710993A (en) * | 2018-12-06 | 2019-05-03 | 上海交通大学 | For the optimization method and system of detuning impeller disturbance rejection |
| CN111597497A (en) * | 2020-04-02 | 2020-08-28 | 西安理工大学 | Maximum localized vibration response method for detuned blade disc |
| CN112182802A (en) * | 2020-09-29 | 2021-01-05 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109359392A (en) * | 2018-10-19 | 2019-02-19 | 北京化工大学 | A kind of turbo blade Stress Calculation method using non-cpntact measurement |
| CN109710993A (en) * | 2018-12-06 | 2019-05-03 | 上海交通大学 | For the optimization method and system of detuning impeller disturbance rejection |
| CN109710993B (en) * | 2018-12-06 | 2020-11-06 | 上海交通大学 | Method and system for optimizing disturbance resistance of detuned impeller |
| CN111597497A (en) * | 2020-04-02 | 2020-08-28 | 西安理工大学 | Maximum localized vibration response method for detuned blade disc |
| CN111597497B (en) * | 2020-04-02 | 2023-05-05 | 西安理工大学 | Maximum localized vibration response method for reducing detuned blisk |
| CN112182802A (en) * | 2020-09-29 | 2021-01-05 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
| CN112182802B (en) * | 2020-09-29 | 2021-10-19 | 上海交通大学 | Method for realizing optimized design of aeroelasticity of impeller machinery with random detuning |
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Application publication date: 20180515 |