CN105740507B - The equivalent modeling method of aero-engine complex rotor system - Google Patents
The equivalent modeling method of aero-engine complex rotor system Download PDFInfo
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Abstract
The invention discloses a kind of equivalent modeling methods of aero-engine complex rotor system, carry out static(al) equivalent analysis by the entity rotor structure to complex rotor system, obtain the geometric dimension of equivalent model；According to the geometric dimension of equivalent model, the material parameter of entity rotor structure is rebuild just, the rotor structure after determining Equivalent Modeling；Power verifying is carried out to the rotor structure after determining Equivalent Modeling.The present invention effectively combine rotor-support-foundation system static analysis result and kinematic analysis as a result, improve complex rotor system computational accuracy；Overcome the problems, such as that three-dimensional finite element unit computational efficiency is low, the computational efficiency of rotor dynamics Nonlinear Dynamic response can be greatly promoted.
Description
Technical field
The present invention relates to the rotor of engine modeling fields to be particularly related to a kind of aero-engine complex rotor system
Equivalent modeling method.
Background technique
Rotating machinery is widely used in including the machinery such as gas turbine, industrial compressors, motor and aero-engine
In device.Very important effect is played in aviation field by it, and one is also formed to the research of its kinetic characteristics
Special subject --- rotor dynamics.Rotor dynamics is that research is all related with rotary machine rotor and its component and structure
Kinetic characteristics, the Men Xue including dynamic response, vibration, intensity, fatigue, stability, reliability, fault diagnosis and control
Section.
The research model of rotor dynamics, Foppl in 1895 propose initial and simplest Jeffcott rotator model,
The model be the massless that a both ends have just been propped up axis and in the middle disk composition.And with the improvement of calculation method and
The raising of computer speed successively occurs such as Riccati transfer matrix method, transfer matrix-Impedance Coupling, transfer matrix-
The analysis method that point vibration shape synthesis and transfer matrix-direct integration method etc. are established specifically for rotor-support-foundation system, also develops
Analysis software of many based on finite element, analyzes the mechanical property of rotor-support-foundation system.Utilize turning for finite element analysis software
Subdynamics analysis be mainly based upon finite element modeling method, although key step as shown in Figure 1, its relative to transfer matrix method
For, computational accuracy is improved, but there are a variety of different modeling methods for rotor-support-foundation system, computational accuracy and efficiency depend on
The engineering experience of different engineers, the standardized method without modeling.
Therefore, the computational efficiency of complex rotor system is low and computational accuracy is not high, is a urgent problem to be solved.
Summary of the invention
The present invention provides a kind of equivalent modeling methods of aero-engine complex rotor system, to solve complicated rotor system
The technical problem that the computational efficiency of system is low and computational accuracy is not high.
The technical solution adopted by the invention is as follows:
The present invention provides a kind of equivalent modeling method of aero-engine complex rotor system, comprising steps of
Static(al) equivalent analysis is carried out to the entity rotor structure of complex rotor system, obtains the geometric dimension of equivalent model；
According to the geometric dimension of equivalent model, the material parameter of entity rotor structure is rebuild just, determines equivalent build
Rotor structure after mould；
Power verifying is carried out to the rotor structure after determining Equivalent Modeling.
Further, static(al) equivalent analysis is carried out to the entity rotor structure of complex rotor system, obtains equivalent model
The step of geometric dimension includes:
Static(al) equivalent analysis is carried out to entity rotor structure, according to the material property and rigidity of entity rotor structure, is obtained
The equivalent outer diameter of armature spindle.
Further, entity rotor structure is hollow rotor shafts, carries out static(al) equivalent analysis to entity rotor structure, according to
The material property and rigidity of entity rotor structure, the step of obtaining armature spindle equivalent outer diameter include:
Obtain the armature spindle internal diameter and armature spindle outer diameter of hollow rotor shafts；
According to the armature spindle internal diameter and armature spindle outer diameter of acquisition, the cross section polar moment of inertia of hollow rotor shafts is calculated；
According to the cross section polar moment of inertia of calculated hollow rotor shafts, under the premise of armature spindle constant inner diameter, obtain
The equivalent outer diameter of armature spindle.
Further, according to the cross section polar moment of inertia of calculated hollow rotor shafts, before armature spindle constant inner diameter
The step of putting, obtaining armature spindle equivalent outer diameter further include:
Under the fixed case of constraint in entity rotor structure one end, complex rotor system in all directions quiet is calculated
Displacement, and pick out maximum Static Correction；
According to the maximum Static Correction picked out, the equivalent outer diameter of armature spindle is calculated.
Further, the expression formula of the cross section polar moment of inertia calculated are as follows:
Wherein, I is cross section polar moment of inertia, and π is pi constant, and D is armature spindle outer diameter, and d is armature spindle internal diameter.
Further, the expression formula of the equivalent outer diameter of armature spindle are as follows:
Wherein, D ' is the equivalent outer diameter of armature spindle, and F is the cross force applied, and l is rotor length, and E is elasticity modulus, and I is
Cross section polar moment of inertia, wmaxFor the maximum Static Correction of complicated finite element rotator model, d is armature spindle internal diameter.
Further, material parameter includes density of material, according to the geometric dimension of equivalent model, to entity rotor structure
The step of material parameter is rebuild just, rotor structure after determining Equivalent Modeling include:
According to the equivalent outer diameter of the armature spindle calculated, the density of material of entity rotor structure is rebuild just, is utilized
The principle of mass conservation determines revised rotor equivalent density.
Further, the expression formula of rotor equivalent density are as follows:
Wherein, ρ ' is revised density of material, and ρ is structure original material density, and D is armature spindle outer diameter, and D ' is rotor
The equivalent outer diameter of axis, d are armature spindle internal diameter.
Further, include: to the step of rotor structure progress power verifying after determining Equivalent Modeling
Model analysis is carried out to the rotor structure after Equivalent Modeling using limited element analysis technique, rotor modal frequency is calculated and misses
Difference carries out power verifying to the rotor structure after determining Equivalent Modeling.
Further, model analysis is carried out to the rotor structure after Equivalent Modeling using limited element analysis technique, calculates rotor
Modal frequency error, to after determining Equivalent Modeling rotor structure carry out power verifying the step of include:
Compare the modal frequency before and after Equivalent Modeling, if the rotor modal frequency error calculated is in allowable error range
Within, then the Equivalent Modeling success of complex rotor system.
The invention has the following advantages:
The equivalent modeling method of aero-engine complex rotor system proposed by the present invention, by complex rotor system
Entity rotor structure carries out static(al) equivalent analysis, obtains the geometric dimension of equivalent model；It is right according to the geometric dimension of equivalent model
The material parameter of entity rotor structure is rebuild just, the rotor structure after determining Equivalent Modeling；After determining Equivalent Modeling
Rotor structure carry out power verifying.Static analysis result that the present invention effectively combines rotor-support-foundation system and kinematic analysis are as a result, mention
High complex rotor system computational accuracy；Overcome the problems, such as that three-dimensional finite element unit computational efficiency is low, it is dynamic that rotor can be greatly promoted
The computational efficiency of mechanic nonlinearity dynamic response.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is flow diagram in the prior art based on finite element modeling method；
Fig. 2 is the flow diagram of one embodiment of equivalent modeling method of aero-engine complex rotor system of the present invention；
Fig. 3 is aero-engine complex rotor system structural schematic diagram of the present invention；
Fig. 4 is the equivalent rotor schematic diagram of aero-engine complex rotor system of the present invention；
Fig. 5 is the equivalent preceding armature spindle schematic diagram of aero-engine complex rotor system of the present invention；
Fig. 6 is the cross-sectional view of the equivalent preceding armature spindle of aero-engine complex rotor system of the present invention；
Fig. 7 is armature spindle schematic diagram after aero-engine complex rotor system of the present invention is equivalent；And
Fig. 8 is the power verification result contrast schematic diagram of one embodiment of aero-engine complex rotor system of the present invention.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Referring to Fig.1, the preferred embodiment of the present invention provides a kind of Equivalent Modeling of aero-engine complex rotor system
Method, comprising steps of
Step S100, static(al) equivalent analysis is carried out to the entity rotor structure of complex rotor system, obtains equivalent model
Geometric dimension.
Static(al) equivalent analysis is carried out to the entity rotor structure of complex rotor system, obtains the geometric dimension of equivalent model,
The geometric dimension of the equivalent model can be the equivalent outer diameter of armature spindle, or the equivalent internal diameter of armature spindle, it is not another herein
One enumerates.In the present embodiment, according to the material property and rigidity of entity rotor structure, the equivalent outer diameter of armature spindle is obtained.Specifically
Ground obtains the armature spindle internal diameter and armature spindle of hollow rotor shafts according to the armature spindle of complex rotor system as shown in Figure 3 first
Outer diameter calculates the cross section polar moment of inertia of hollow rotor shafts then according to the armature spindle internal diameter of acquisition and armature spindle outer diameter, by
Mostly using isotropic material in rotor, i.e. the elasticity modulus of all directions is equal, and its mode of oscillation is mainly mode of flexural vibration, therefore
Only it needs to be determined that equivalent bending stiffness.Again since the armature spindle is hollow circular section, as shown in fig. 6, therefore its cross section pole
The calculation formula of the moment of inertia I are as follows:
Wherein, I is cross section polar moment of inertia, and π is pi constant, and D is armature spindle outer diameter, and d is armature spindle internal diameter.
In the present embodiment, all directions Static Correction (amount of deflection) of the one end of armature spindle under the conditions of fixed constraint is calculated,
And maximum Static Correction is picked out, and according to the maximum Static Correction picked out, calculate the equivalent outer diameter of armature spindle.Static(al) deformation deflection
Calculation formula are as follows:
Wherein, wmaxFor the maximum Static Correction of complicated finite element rotator model, i.e. maximum defluxion；F is the transverse direction that is applied
Power, l are rotor length, and E is elasticity modulus, and I is by the cross section polar moment of inertia that is calculated in formula (1).Equivalent preceding rotor
The parameter of axis is specifically as shown in Figure 3 and Figure 5.
Finally according to the cross section polar moment of inertia of calculated hollow rotor shafts, under the premise of armature spindle constant inner diameter,
Obtain the equivalent outer diameter of armature spindle.In this implementation, under the premise of internal diameter d is constant, by solving in formula (1) and formula (2) with true
Rotor outer radius values, according to the stiffnes s equivalent of structure, obtain it is equivalent after armature spindle overall diameter D ', it is equivalent after armature spindle it is each
Parameter is specifically as shown in figs. 4 and 7:
Wherein, D ' is the equivalent outer diameter of armature spindle, and F is the cross force applied, and l is rotor length, and E is elasticity modulus, and I is
Cross section polar moment of inertia, wmaxFor the maximum Static Correction of complicated finite element rotator model, d is armature spindle internal diameter.
Step S200, according to the geometric dimension of equivalent model, the material parameter of entity rotor structure is rebuild just, really
Rotor structure after determining Equivalent Modeling.
After the geometric dimension for determining equivalent model, since structure combination size has been changed, so needing to reality
The material parameter of body rotor structure is rebuild just, i.e., is rebuild just to the density of entity rotor structure, and modified basic
Principle is according to the principle of mass conservation, if mbeforeAnd mafterThe quality of equivalent front and back is respectively indicated, then
mafter=mbefore (4)
Wherein, mafterFor equivalent preceding quality, mbeforeBe it is equivalent after quality.
If structure original material density is ρ, and revised density of material is ρ ', then its revised density of material calculates
Formula are as follows:
Wherein, ρ ' is revised density of material, and ρ is structure original material density, and D is armature spindle outer diameter, and D ' is rotor
The equivalent outer diameter of axis, d are armature spindle internal diameter.All revised geometry of complex rotor system and material parameter are finally obtained, is obtained
Rotor structure after Equivalent Modeling, as shown in figs. 4 and 7.
Step S300, power verifying is carried out to the rotor structure after determining Equivalent Modeling.
Model analysis is carried out to the rotor structure after equivalent, using finite element analysis software, by comparing equivalent front and back
The modal frequency of rotor structure, it is ensured that its calculated result is within the scope of allowable error, i.e. the Engineering Error of e < [e]=5%.
Can assert it is equivalent after rotor structure can guarantee the computational accuracy of equivalent preceding rotor computation model, and can be to make
For the simplified model of subsequent analysis.
Wherein, e indicates the calculating error of equivalent front and back modal frequency, and [e] is the allowable error range being previously set,
freqbeforeFor equivalent preceding modal frequency, freqafterBe it is equivalent after modal frequency.
For complex rotor system as shown in Figure 3, Equivalent Modeling is carried out according to the equivalent method mentioned in the present embodiment,
Obtain equivalent rear analysis structure as shown in Figure 4.Kinematic analysis finally is carried out to two kinds of models, to verify equivalent modeling method
Validity.As a result can as can be seen from Figure 8, equivalent preceding first step mode frequency is 259.7Hz, and equivalent rear first step mode frequency is
258.43Hz；Equivalent preceding second-order modal frequency is 783.1Hz, and equivalent rear second-order modal frequency is 751.8Hz；Pass through formula
(6), the error difference of preceding two ranks modal frequency (first step mode frequency and second-order modal frequency) can be calculated separately out
Are as follows: -0.54% and -4.00%, that is, it is less than the Engineering Error limit value 5% being previously set, so as to obtain, after equivalent-simplification
Model analysis frequency error it is lower, be less than Engineering Error 5%, meet project analysis calculate require.
The equivalent modeling method for the aero-engine complex rotor system that the present embodiment proposes, by complex rotor system
Entity rotor structure carry out static(al) equivalent analysis, obtain the geometric dimension of equivalent model；According to the geometric dimension of equivalent model,
The material parameter of entity rotor structure is rebuild just, the rotor structure after determining Equivalent Modeling；To determining Equivalent Modeling
Rotor structure afterwards carries out power verifying.The present embodiment effectively combines the static analysis result and kinematic analysis knot of rotor-support-foundation system
Fruit improves complex rotor system computational accuracy；Overcome the problems, such as that three-dimensional finite element unit computational efficiency is low, can greatly promote and turn
The computational efficiency of subdynamics Nonlinear Dynamic response.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of equivalent modeling method of aero-engine complex rotor system, which is characterized in that comprising steps of
Static(al) equivalent analysis is carried out to the entity rotor structure of the complex rotor system, obtains the geometric dimension of equivalent model；
According to the geometric dimension of equivalent model, rebuild according to density parameter of the principle of mass conservation to entity rotor structure
Just, the rotor structure after determining Equivalent Modeling；
Power verifying is carried out to the rotor structure after determining Equivalent Modeling.
2. the equivalent modeling method of aero-engine complex rotor system according to claim 1, which is characterized in that
The entity rotor structure to complex rotor system carries out static(al) equivalent analysis, obtains the geometric dimension of equivalent model
Step includes:
Static(al) equivalent analysis is carried out to the entity rotor structure, according to the material property and rigidity of the entity rotor structure,
Obtain the equivalent outer diameter of armature spindle.
3. the equivalent modeling method of aero-engine complex rotor system according to claim 2, which is characterized in that
The entity rotor structure is hollow rotor shafts, described to carry out static(al) equivalent analysis to entity rotor structure, according to described
The material property and rigidity of entity rotor structure, the step of obtaining armature spindle equivalent outer diameter include:
Obtain the armature spindle internal diameter and armature spindle outer diameter of the hollow rotor shafts；
According to the armature spindle internal diameter and the armature spindle outer diameter of acquisition, the cross section for calculating the hollow rotor shafts is extremely used
Property square；
According to the cross section polar moment of inertia of the calculated hollow rotor shafts, under the premise of the armature spindle constant inner diameter,
Obtain the equivalent outer diameter of the armature spindle.
4. the equivalent modeling method of aero-engine complex rotor system according to claim 3, which is characterized in that
The cross section polar moment of inertia according to the calculated hollow rotor shafts, in the premise of the armature spindle constant inner diameter
Under, the step of obtaining the armature spindle equivalent outer diameter further include:
Under the fixed case of constraint in entity rotor structure one end, the complex rotor system is calculated in all directions
Static Correction, and pick out maximum Static Correction；
According to the maximum Static Correction picked out, the equivalent outer diameter of the armature spindle is calculated.
5. the equivalent modeling method of aero-engine complex rotor system according to claim 3 or 4, which is characterized in that
The expression formula of the cross section polar moment of inertia calculated are as follows:
Wherein, I is cross section polar moment of inertia, and π is pi constant, and D is armature spindle outer diameter, and d is armature spindle internal diameter.
6. the equivalent modeling method of aero-engine complex rotor system according to claim 3 or 4, which is characterized in that
The expression formula of the equivalent outer diameter of armature spindle are as follows:
Wherein, D ' is the equivalent outer diameter of armature spindle, and F is the cross force applied, and l is rotor length, and E is elasticity modulus, wmaxIt is multiple
The maximum Static Correction of miscellaneous finite element rotator model, d are armature spindle internal diameter.
7. the equivalent modeling method of aero-engine complex rotor system according to claim 4, which is characterized in that
The geometric dimension according to equivalent model, rebuilds just the density parameter of entity rotor structure, determines equivalent build
The step of rotor structure after mould includes:
According to the equivalent outer diameter of the armature spindle calculated, the density of material of entity rotor structure is rebuild just,
Using the principle of mass conservation, revised rotor equivalent density is determined.
8. the equivalent modeling method of aero-engine complex rotor system according to claim 7, which is characterized in that
The expression formula of the rotor equivalent density are as follows:
Wherein, ρ ' is revised density of material, and ρ is structure original material density, and D is armature spindle outer diameter, and D ' is armature spindle etc.
Outer diameter is imitated, d is armature spindle internal diameter.
9. the equivalent modeling method of aero-engine complex rotor system according to claim 8, which is characterized in that
Rotor structure after described pair of determining Equivalent Modeling carries out the step of power verifying and includes:
Model analysis is carried out to the rotor structure after Equivalent Modeling using limited element analysis technique, calculates rotor modal frequency error,
Power verifying is carried out to the rotor structure after determining Equivalent Modeling.
10. the equivalent modeling method of aero-engine complex rotor system according to claim 9, which is characterized in that
It is described that model analysis is carried out to the rotor structure after Equivalent Modeling using limited element analysis technique, it calculates rotor modal frequency and misses
Difference, to after determining Equivalent Modeling rotor structure carry out power verifying the step of include:
Compare the modal frequency before and after Equivalent Modeling, if the rotor modal frequency error calculated allowable error range it
It is interior, then the Equivalent Modeling success of the complex rotor system.
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| CN104268342A (en) * | 2014-09-28 | 2015-01-07 | 中航工业哈尔滨轴承有限公司 | Method for analyzing vibration characteristics of bearing retainer based on finite elements |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104268342A (en) * | 2014-09-28 | 2015-01-07 | 中航工业哈尔滨轴承有限公司 | Method for analyzing vibration characteristics of bearing retainer based on finite elements |
Non-Patent Citations (3)
| Title |
|---|
| 航空发动机支承不同心转子系统力学模型研究;张振波 等;《工程力学》;20140725;第31卷(第7期);第208-214、228页 |
| 航空发动机整机振动分析与控制;艾延廷 等;《沈阳航空航天大学学报》;20151025;第32卷(第5期);第1-25页 |
| 车用发动机曲轴结构设计中的三维有限元分析;苏铁熊 等;《华北工学院学报》;20020228;第23卷(第1期);第71-74页 |
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Address after: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee after: AECC HUNAN AVIATION POWERPLANT Research Institute Country or region after: China Address before: Dong Jiaduan 412002 in Hunan province Zhuzhou city Lusong District Patentee before: CHINA AVIATION POWER MACHINERY INSTITUTE Country or region before: China |