CN110153664A - Multistage components assembly method and device are equipped in large high-speed revolution based on BP neural network - Google Patents
Multistage components assembly method and device are equipped in large high-speed revolution based on BP neural network Download PDFInfo
- Publication number
- CN110153664A CN110153664A CN201910217522.XA CN201910217522A CN110153664A CN 110153664 A CN110153664 A CN 110153664A CN 201910217522 A CN201910217522 A CN 201910217522A CN 110153664 A CN110153664 A CN 110153664A
- Authority
- CN
- China
- Prior art keywords
- rotor
- speed
- circle
- alpha
- unbalance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Balance (AREA)
Abstract
The invention proposes the large high-speed revolutions based on BP neural network to equip multistage components assembly method and device, belongs to Automatic manual transmission art field.The method considers engine practical structures feature, to assemble phase as control variable, under the conditions of in two sections, balance is with maximum (top) speed, the influence of the extensional rigidity and bending stiffness of contact surface is assembled between consideration rotor, match phase change high-speed response parameter by rotating dress, when choosing optimal assembly phase, vibration at high speed response amplitude parameter is obtained by solving system kinetics equation, high-speed response magnitude parameters are optimal after assembling multi-stage rotor, realize the optimization to aero-engine multi-stage rotor high-speed response.Described device includes pedestal, air floating shaft system, and aligning tune inclines workbench, precision force transducer, static balance measuring table, left column, right column, the components such as telescopic inductance sensor of lower-left transverse direction measuring staff and lower-left.
Description
Technical field
The present invention relates to the large high-speed revolutions based on BP neural network to equip multistage components assembly method and device, belongs to
In Automatic manual transmission art field.
Background technique
The mechanism complex of aero-engine, and working in the high-revolving environment of high temperature, in the process of running can be by
To the effect of a variety of uneven excitations, including periodic excitation and aperiodicity excitation, itself uneven excitation and the external world are uneven
The influence of weighing apparatus air-flow.They can directly or indirectly influence the vibration at high speed response of aeroengine rotor, including amplitude, phase
Position, critical speed etc..The failure of 70% or more aero-engine is all related to vibration according to statistics, and serious vibration can be to aviation
The performance of engine causes tremendous influence.Therefore the control of research with the vibration of vibration mechanism becomes aero-engine and developed
A crucial problem in journey.Existing assembly optimization method has problems in that: only individually having carried out the list of concentricity
Objective optimization, and the concentricity model established does not consider the rotation error around X and Y-axis, does not consider that single stage rotor circle contour filters
Error is influenced in the transmitting and amplification of assembling process, does not account for uneven parameter, stiffness parameters, and do not set up vibration at high speed
Response measurement model can not achieve the optimization of aero-engine multi-stage rotor high-speed response.
Summary of the invention
In view of the deficiency of the prior art, propose it is a kind of based on vibratory response characteristic under full-power turnup most
Multistage components assembly method is equipped in the large high-speed revolution of optimization, is asked with solving the vibration optimization of aero-engine multi-stage rotor
Topic realizes the optimization of multi-stage rotor high-speed response.
Multistage components assembly is equipped in large high-speed revolution based on vibratory response characteristic optimization under full-power turnup
Method, which comprises
The first step establishes the Morphologic filters based on unequal interval sampling angle using Borrow's Filter Principle, from function
It can angle progress contours extract；
Second step, the equation of locus that the alpha disk inside and outside circle center of circle is obtained in conjunction with contours extract；
Third step determines alpha envelope boundary according to the equation of locus in the alpha disk inside and outside circle center of circle of second step acquisition
Relationship between sampled point polar coordinates；It can be obtained using the relationship between alpha envelope boundary and sampled point polar coordinates
It obtains circle contour and acquires data；Then, circle contour acquisition data are subjected to validity processing by incoordinate interval filtering device,
Obtain effective circle contour data；
4th step is assembled according to multi-stage rotor, and single stage rotor positioning, orientation error will do it transmitting and accumulation, influence
This case that the amount of unbalance after multi-stage rotor assembly, determine n-th grade of rotor as caused by rotor fixed positions at different levels and orientation error
Amount of unbalance；
5th step, the imbalance that will be introduced in single stage rotor itself amount of unbalance and assembling process by positioning and orientation error
Amount carries out vector addition, obtains the amount of unbalance of any primary rotor after multi-stage rotor assembly；
Rotor unbalance values at different levels are projected to two more positive, foundation dynamic balancing formula synthesis injustice by the 6th step respectively
It measures, the prediction model of multi-stage rotor amount of unbalance can be established；
7th step is established using single stage rotor positioning, orientation error and amount of unbalance as input quantity, after practical set not
BP neural network of the aequum as output quantity selects hidden layer activation primitive and output layer activation primitive respectively, utilizes study
Curve and regression curve determine network model the number of iterations, Studying factors, the hidden layer number of plies and number of nodes, establish multi-stage rotor
Amount of unbalance forecast value revision model；
8th step is calculated separately according to the prediction model and is assembled between the sectional area S and rotor that assemble contact surface between rotor
The cross sectional moment of inertia I of contact surface；
9th step determines the equation of motion of the armature spindle element under fixed coordinate system, utilizes extensional rigidity and bending stiffness
Form stiffness matrix；
Tenth step, the dynamic response parameter that rotor-support-foundation system is solved using Finite Element, in conjunction with assembling contact surface between rotor
Sectional area S and rotor between assemble the cross sectional moment of inertia I of contact surface and obtain dynamic response parameter and rotor interfaces at different levels and beat
With the relationship of amount of unbalance, and then obtain dynamic response parameter objective function；
The rotor speed in the dynamic response parameter objective function is set maximum (top) speed by 11st step, is shaken
Dynamic magnitude parameters assemble phases by adjusting rotors at different levels, and high-speed response vibration amplitude parameter is most after assembling multi-stage rotor
It is excellent, realize the optimization to aero-engine multi-stage rotor high-speed response.
Further, the detailed process of the equation of locus in the acquisition alpha disk inside and outside circle center of circle described in second step includes:
Step 1: taking any point P in the 2-d spatial coordinate point set S of circle contour sampled point1, will be with point P1For starting point,
With P1Point of the distance less than 2 α constitutes subset S1, wherein α is alpha disc radius；
Step 2: in subset S1In take any point P2, then the alpha disk that two radiuses are α is formed；Described two half
The alpha disk that diameter is α crosses P respectively1And P2Two o'clock,
Step 3: determining the equation of locus in the alpha disk inside and outside circle center of circle, institute using the alpha disk that two radiuses are α
State the equation of locus in the alpha disk inside and outside circle center of circle are as follows:
Or
Wherein,
ρ0、ρ0'、ρ1、ρ2、Respectively point P0、P0'、P1、P2Polar diameter and polar angle under polar coordinates.
Further, the relationship between alpha envelope boundary and sampled point polar coordinates described in third step are as follows:
Wherein, n is circle contour sampling number, and F is that the unequal interval Morphologic filters based on alpha shape theory are set
Count rule； ρi、Respectively point PiPolar diameter and polar angle under polar coordinates.
Further, n-th grade of rotor unbalance value as caused by rotor fixed positions at different levels and orientation error described in the 4th step are as follows:
Wherein, Ux0-nFor the amount of unbalance of n-th grade of rotor measurement face in the X-axis direction after assembly；Uy0-nIt is after assembly n-th
The amount of unbalance of grade rotor measurement face in the Y-axis direction；m0-nFor the quality of n-th grade of rotor after assembly；piFor i-stage rotor diameter
To the ideal position vector in the measuring surface center of circle；dpiFor the mismachining tolerance vector of i-stage rotor radial measuring surface center location；Sri
θ is rotated about the z axis for i-stage rotorriThe spin matrix of angle；Sr1For unit matrix；Sxj-1It is flat to turn stator benchmark for -1 grade of jth
Face rotates θ around X-axisxj-1The spin matrix of angle；Syj-1Turn stator datum plane for -1 grade of jth and rotates θ around Y-axisyj-1The rotation of angle
Torque battle array；Srj-1Turn stator for -1 grade of jth and rotates θ about the z axisrj-1The spin matrix of angle.
Further, the section for assembling contact surface between son described in the 8th step between the sectional area S and rotor of assembly contact surface is used
Property square I is respectively indicated are as follows:
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityIt is eccentric
Angle d θ=arctan (dy0-n/dx0-n), extensional rigidity ES, E are the elasticity modulus of material；
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityIt is eccentric
Angle d θ=arctan (dy0-n/dx0-n), bending stiffness EI, wherein E is the elasticity modulus of material.
Further, the equation of motion of the armature spindle element under fixed coordinate system described in the 9th step are as follows:
Wherein,Indicate mass matrix,Indicate that inertial matrix, G are gyroscopic effect matrix, Ω is rotor angle of rotation
Speed, q are generalized displacement vector, KeFor stiffness matrix；QeExternal force suffered by expression system；Subscript e indicates axis element.
Further, maximum (top) speed described in the 11st step is the 85% of specified maximum (top) speed --- 100%.
Multistage components assembly is equipped in large high-speed revolution based on vibratory response characteristic optimization under full-power turnup
Device, it includes that air floating shaft system 2 is nested in 1 center of pedestal that multistage components assembly device is equipped in the large high-speed revolution
On, aligning tune inclines the configuration of workbench 3 on 2 center of air floating shaft system, and three precision force transducers 4a, 4b, 4c are uniformly configured
Incline on workbench 3 in aligning tune；Static balance measuring table 5 is on three precision force transducers 4a, 4b, 4c；Left column 6 and the right side
Column 7 is symmetrically distributed in the two sides of air floating shaft system 2 and is packed on pedestal 1；It is successively moved from top to bottom on left column 6
Adjustably it is set with upper left transverse direction measuring staff 10 and lower-left transverse direction measuring staff 8, the telescopic inductance sensor 11 in upper left and upper left transverse direction measuring staff
10 are connected；The telescopic inductance sensor 9 in lower-left is connected with lower-left transverse direction measuring staff 8；It is successively removable from top to bottom on right column 7
Dynamic to be adjustably set with upper right transverse direction measuring staff 14 and bottom right transverse direction measuring staff 12, upper right lever inductance sensor 15 and upper right are lateral
Measuring staff 14 is connected；Bottom right lever inductance sensor 13 and bottom right transverse direction measuring staff 12 are connected；16 both ends of gate crossbeam and left column
6 upper ends and 7 upper end of right column are connected；It is moved on gate crossbeam 16 and is adjustably set with longitudinal measuring staff 17, the middle telescopic electricity in position
Propagated sensation sensor 18 and longitudinal measuring staff 17 are connected.
The invention has the advantages that:
Large high-speed revolution equipment proposed by the present invention based on vibratory response characteristic optimization under full-power turnup is more
Grade components assembly method consider engine practical structures feature, with assemble phase for control variable, two sections balance and most
Under the conditions of big revolving speed (the 85%~100% of maximum (top) speed), the extensional rigidity and bending stiffness of assembly contact surface between rotor are considered
Influence, by rotating dress match phase change high-speed response parameter, when choosing optimal assembly phase, by solving system move
Mechanical equation obtains vibration at high speed response amplitude parameter, and high-speed response magnitude parameters are optimal after assembling multi-stage rotor, realization pair
The optimization of aero-engine multi-stage rotor high-speed response.
Large high-speed revolution equipment proposed by the present invention based on vibratory response characteristic optimization under full-power turnup is more
Grade components assembly device effectively can accurately realize that multistage components assembly is equipped in large high-speed revolution, effectively improve portion
Part assembly efficiency and assembly precision.
Detailed description of the invention
Fig. 1 is the spatial distribution schematic diagram of two-dimentional point set S of the present invention, wherein O is the sampled contour center of circle, and S is circle wheel
The 2-d spatial coordinate point set of wide sampled point, P1For any point in two-dimentional point set S, S1For with point P1Start therewith apart from small
In the point set that the point of 2 α is constituted, α is alpha disc radius, P2For point set S1Middle any point, P0And P0' it is respectively two
The center of circle of alpha disk；
Fig. 2 is that the large high-speed of the present invention based on vibratory response characteristic optimization under full-power turnup turns round equipment
The structural schematic diagram of multistage components assembly device；
(1 is pedestal, and 2 be air floating shaft system, and 3 incline workbench for aligning tune, and 4a, 4b, 4c are respectively precision force transducer, and 5 are
Static balance measuring table, 6 be left column, and 7 be right column, and 8 be lower-left transverse direction measuring staff, and 9 be the telescopic inductance sensor in lower-left,
10 be upper left transverse direction measuring staff, and 11 be the telescopic inductance sensor in upper left, and 12 be bottom right transverse direction measuring staff, and 13 be bottom right lever electricity
Propagated sensation sensor, 14 be upper right transverse direction measuring staff, and 15 be upper right lever inductance sensor, and 16 be gate crossbeam, and 17 survey to be longitudinal
Bar, 18 be the telescopic inductance sensor in middle position)
Specific embodiment
The present invention will be further described combined with specific embodiments below, but the present invention should not be limited by the examples.
Embodiment 1:
Multistage components assembly is equipped in large high-speed revolution based on vibratory response characteristic optimization under full-power turnup
Method, which comprises
The first step establishes the Morphologic filters based on unequal interval sampling angle using Borrow's Filter Principle, from function
It can angle progress contours extract；
Second step, the equation of locus that the alpha disk inside and outside circle center of circle is obtained in conjunction with contours extract；
Third step determines alpha envelope boundary according to the equation of locus in the alpha disk inside and outside circle center of circle of second step acquisition
Relationship between sampled point polar coordinates；It can be obtained using the relationship between alpha envelope boundary and sampled point polar coordinates
It obtains circle contour and acquires data；Then, circle contour acquisition data are subjected to validity processing by incoordinate interval filtering device,
Obtain effective circle contour data；
4th step is assembled according to multi-stage rotor, and single stage rotor positioning, orientation error will do it transmitting and accumulation, influence
This case that the amount of unbalance after multi-stage rotor assembly, determine n-th grade of rotor as caused by rotor fixed positions at different levels and orientation error
Amount of unbalance；
5th step, the imbalance that will be introduced in single stage rotor itself amount of unbalance and assembling process by positioning and orientation error
Amount carries out vector addition, obtains the amount of unbalance of any primary rotor after multi-stage rotor assembly；
Rotor unbalance values at different levels are projected to two more positive, foundation dynamic balancing formula synthesis injustice by the 6th step respectively
It measures, the prediction model of multi-stage rotor amount of unbalance can be established；
7th step is established using single stage rotor positioning, orientation error and amount of unbalance as input quantity, after practical set not
BP neural network of the aequum as output quantity selects hidden layer activation primitive and output layer activation primitive respectively, utilizes study
Curve and regression curve determine network model the number of iterations, Studying factors, the hidden layer number of plies and number of nodes, establish multi-stage rotor
Amount of unbalance forecast value revision model；
8th step is calculated separately according to the prediction model and is assembled between the sectional area S and rotor that assemble contact surface between rotor
The cross sectional moment of inertia I of contact surface；
9th step determines the equation of motion of the armature spindle element under fixed coordinate system, utilizes extensional rigidity and bending stiffness
Form stiffness matrix；
Tenth step, the dynamic response parameter that rotor-support-foundation system is solved using Finite Element, in conjunction with assembling contact surface between rotor
Sectional area S and rotor between assemble the cross sectional moment of inertia I of contact surface and obtain dynamic response parameter and rotor interfaces at different levels and beat
With the relationship of amount of unbalance, and then obtain dynamic response parameter objective function；
The rotor speed in the dynamic response parameter objective function is set maximum (top) speed by 11st step, is shaken
Dynamic magnitude parameters assemble phases by adjusting rotors at different levels, and high-speed response vibration amplitude parameter is most after assembling multi-stage rotor
It is excellent, realize the optimization to aero-engine multi-stage rotor high-speed response, wherein the maximum (top) speed is specified maximum (top) speed
85% --- 100%.
The detailed process of equation of locus that the alpha disk inside and outside circle center of circle is obtained described in second step includes:
Step 1: as shown in Fig. 2, taking any point P in the 2-d spatial coordinate point set S of circle contour sampled point1, will be with
Point P1For starting point, with P1Point of the distance less than 2 α constitutes subset S1, wherein α is alpha disc radius；
Step 2: in subset S1In take any point P2, then the alpha disk that two radiuses are α is formed；Described two half
The alpha disk that diameter is α crosses P respectively1And P2Two o'clock,
Step 3: determining the equation of locus in the alpha disk inside and outside circle center of circle, institute using the alpha disk that two radiuses are α
State the equation of locus in the alpha disk inside and outside circle center of circle are as follows:
Or
Wherein,
ρ0、ρ0'、ρ1、ρ2、Respectively point P0、P0'、P1、P2Polar diameter and polar angle under polar coordinates.
Relationship between alpha envelope boundary and sampled point polar coordinates described in third step are as follows:
Wherein, n is circle contour sampling number, and F is that the unequal interval Morphologic filters based on alpha shape theory are set
Count rule； ρi、Respectively point PiPolar diameter and polar angle under polar coordinates.
N-th grade of rotor unbalance value as caused by rotor fixed positions at different levels and orientation error described in 4th step are as follows:
Wherein, Ux0-nFor the amount of unbalance of n-th grade of rotor measurement face in the X-axis direction after assembly；Uy0-nIt is after assembly n-th
The amount of unbalance of grade rotor measurement face in the Y-axis direction；m0-nFor the quality of n-th grade of rotor after assembly；piFor i-stage rotor diameter
To the ideal position vector in the measuring surface center of circle；dpiFor the mismachining tolerance vector of i-stage rotor radial measuring surface center location；Sri
θ is rotated about the z axis for i-stage rotorriThe spin matrix of angle；Sr1For unit matrix；Sxj-1It is flat to turn stator benchmark for -1 grade of jth
Face rotates θ around X-axisxj-1The spin matrix of angle；Syj-1Turn stator datum plane for -1 grade of jth and rotates θ around Y-axisyj-1The rotation of angle
Torque battle array；Srj-1Turn stator for -1 grade of jth and rotates θ about the z axisrj-1The spin matrix of angle.
The cross sectional moment of inertia I difference of contact surface is assembled between son described in 8th step between the sectional area S and rotor of assembly contact surface
It indicates are as follows:
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityIt is eccentric
Angle d θ=arctan (dy0-n/dx0-n), extensional rigidity ES, E are the elasticity modulus of material；
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityIt is eccentric
Angle d θ=arctan (dy0-n/dx0-n), bending stiffness EI, wherein E is the elasticity modulus of material.
The equation of motion of the armature spindle element under fixed coordinate system described in 9th step are as follows:
Wherein,Indicate mass matrix,Indicate that inertial matrix, G are gyroscopic effect matrix, Ω is rotor angle of rotation
Speed, q are generalized displacement vector, KeFor stiffness matrix；QeExternal force suffered by expression system；Subscript e indicates axis element.
Large high-speed revolution equipment proposed by the present invention based on vibratory response characteristic optimization under full-power turnup is more
Grade components assembly method consider engine practical structures feature, with assemble phase for control variable, two sections balance and most
Under the conditions of big revolving speed (the 85%~100% of maximum (top) speed), the extensional rigidity and bending stiffness of assembly contact surface between rotor are considered
Influence, by rotating dress match phase change high-speed response parameter, when choosing optimal assembly phase, by solving system move
Mechanical equation obtains vibration at high speed response amplitude parameter, and high-speed response magnitude parameters are optimal after assembling multi-stage rotor, realization pair
The optimization of aero-engine multi-stage rotor high-speed response.
Embodiment 2
Multistage components assembly is equipped in large high-speed revolution based on vibratory response characteristic optimization under full-power turnup
Device, as shown in Fig. 2, it includes that air floating shaft system 2 is nested in pedestal that multistage components assembly device is equipped in large high-speed revolution
On 1 center, aligning tune inclines the configuration of workbench 3 on 2 center of air floating shaft system, three precision force transducer 4a, 4b,
4c is uniformly configured in aligning tune and inclines on workbench 3；Static balance measuring table 5 is on three precision force transducers 4a, 4b, 4c；It is left
Column 6 and right column 7 are symmetrically distributed in the two sides of air floating shaft system 2 and are packed on pedestal 1；On left column 6 from top to bottom according to
Secondary removable adjustably suit upper left transverse direction measuring staff 10 and lower-left transverse direction measuring staff 8, the telescopic inductance sensor 11 in upper left and upper left
Lateral measuring staff 10 is connected；The telescopic inductance sensor 9 in lower-left is connected with lower-left transverse direction measuring staff 8；On right column 7 from top to bottom
Successively move and be adjustably set with upper right transverse direction measuring staff 14 and bottom right transverse direction measuring staff 12, upper right lever inductance sensor 15 with
Upper right transverse direction measuring staff 14 is connected；Bottom right lever inductance sensor 13 and bottom right transverse direction measuring staff 12 are connected；16 both ends of gate crossbeam
It is connected with 6 upper end of left column and 7 upper end of right column；It is moved on gate crossbeam 16 and is adjustably set with longitudinal measuring staff 17, middle position
Telescopic inductance sensor 18 is connected with longitudinal measuring staff 17.
Large high-speed revolution equipment proposed by the present invention based on vibratory response characteristic optimization under full-power turnup is more
Grade components assembly device effectively can accurately realize that multistage components assembly is equipped in large high-speed revolution, effectively improve portion
Part assembly efficiency and assembly precision.
Although the present invention has been disclosed in the preferred embodiment as above, it is not intended to limit the invention, any to be familiar with this
The people of technology can be various changes and modification, therefore guarantor of the invention without departing from the spirit and scope of the present invention
Shield range should subject to the definition of the claims.
Claims (8)
1. multistage components assembly method is equipped in the large high-speed revolution based on BP neural network, which is characterized in that the method
Include:
The first step establishes the Morphologic filters based on unequal interval sampling angle using Borrow's Filter Principle, from function angle
Degree carries out contours extract；
Second step, the equation of locus that the alpha disk inside and outside circle center of circle is obtained in conjunction with contours extract；
Third step determines alpha envelope boundary according to the equation of locus in the alpha disk inside and outside circle center of circle of second step acquisition and adopts
Relationship between sampling point polar coordinates；It can be obtained circle using the relationship between alpha envelope boundary and sampled point polar coordinates
Profile acquisition data；Then, circle contour acquisition data are subjected to validity processing by incoordinate interval filtering device, are had
The circle contour data of effect；
4th step is assembled according to multi-stage rotor, and single stage rotor positioning, orientation error will do it transmitting and accumulation, influence multistage
This case that the amount of unbalance after rotor assembly, determine n-th grade of rotor injustice as caused by rotor fixed positions at different levels and orientation error
It measures；
5th step, by single stage rotor itself amount of unbalance and assembling process by positioning and orientation error introduce amount of unbalance into
Row vector addition obtains the amount of unbalance of any primary rotor after multi-stage rotor assembly；
Rotor unbalance values at different levels are projected to two more positive, foundation dynamic balancing formula synthesis amount of unbalances by the 6th step respectively,
The prediction model of multi-stage rotor amount of unbalance can be established；
The imbalance of 7th step, foundation using single stage rotor positioning, orientation error and amount of unbalance as input quantity, after practical set
The BP neural network as output quantity is measured, hidden layer activation primitive and output layer activation primitive is selected respectively, utilizes learning curve
And regression curve determines network model the number of iterations, Studying factors, the hidden layer number of plies and number of nodes, establishes multi-stage rotor imbalance
Measure forecast value revision model；
8th step calculates separately according to the prediction model and assembles contact between the sectional area S and rotor that assemble contact surface between rotor
The cross sectional moment of inertia I in face；
9th step determines the equation of motion of the armature spindle element under fixed coordinate system, is formed using extensional rigidity and bending stiffness
Stiffness matrix；
Tenth step, the dynamic response parameter that rotor-support-foundation system is solved using Finite Element, in conjunction with section for assembling contact surface between rotor
The cross sectional moment of inertia I that contact surface is assembled between area S and rotor obtains dynamic response parameter and rotor interfaces at different levels and beats and not
The relationship of aequum, and then obtain dynamic response parameter objective function；
11st step sets the rotor speed in the dynamic response parameter objective function to maximum (top) speed, obtains vibration width
Value parameter assembles phase by adjusting rotors at different levels, and high-speed response vibration amplitude parameter is optimal after assembling multi-stage rotor, realizes
Optimization to aero-engine multi-stage rotor high-speed response.
2. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that second step institute
It states and obtains the detailed process of equation of locus in the alpha disk inside and outside circle center of circle and include:
Step 1: taking any point P in the 2-d spatial coordinate point set S of circle contour sampled point1, will be with point P1For starting point, with P1
Point of the distance less than 2 α constitutes subset S1, wherein α is alpha disc radius；
Step 2: in subset S1In take any point P2, then the alpha disk that two radiuses are α is formed；Described two radiuses are α
Alpha disk respectively cross P1And P2Two o'clock,
Step 3: the equation of locus in the alpha disk inside and outside circle center of circle is determined using the alpha disk that two radiuses are α, it is described
The equation of locus in the alpha disk inside and outside circle center of circle are as follows:
Or
Wherein,
ρ0、ρ0'、ρ1、ρ2、Respectively point P0、P0'、P1、P2Polar diameter and polar angle under polar coordinates.
3. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that third step institute
State the relationship between alpha envelope boundary and sampled point polar coordinates are as follows:
Wherein, n is circle contour sampling number, and F is the unequal interval Morphologic filters design method based on alpha shape theory
Then；
ρi、Respectively point PiPolar diameter and polar angle under polar coordinates.
4. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that the 4th step institute
State n-th grade of rotor unbalance value as caused by rotor fixed positions at different levels and orientation error are as follows:
Wherein, Ux0-nFor the amount of unbalance of n-th grade of rotor measurement face in the X-axis direction after assembly；Uy0-nTurn for n-th grade after assembly
The amount of unbalance of sub- measuring surface in the Y-axis direction；m0-nFor the quality of n-th grade of rotor after assembly；piFor the survey of i-stage rotor radial
The ideal position vector in the amount face center of circle；dpiFor the mismachining tolerance vector of i-stage rotor radial measuring surface center location；SriIt is i-th
Grade rotor rotates θ about the z axisriThe spin matrix of angle；Sr1For unit matrix；Sxj-1Turn stator datum plane around X-axis for -1 grade of jth
Rotate θxj-1The spin matrix of angle；Syj-1Turn stator datum plane for -1 grade of jth and rotates θ around Y-axisyj-1The spin matrix of angle；
Srj-1Turn stator for -1 grade of jth and rotates θ about the z axisrj-1The spin matrix of angle.
5. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that the 7th step institute
It states and assembles the cross sectional moment of inertia I of contact surface between the sectional area S and rotor that assemble contact surface between son and respectively indicate are as follows:
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityEccentric angle d θ
=arctan (dy0-n/dx0-n), extensional rigidity ES, E are the elasticity modulus of material；
Wherein, R is contact surface overall diameter, and r is contact surface interior diameter, eccentricityEccentric angle d θ
=arctan (dy0-n/dx0-n), bending stiffness EI, wherein E is the elasticity modulus of material.
6. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that the 8th step institute
State the equation of motion of the armature spindle element under fixed coordinate system are as follows:
Wherein,Indicate mass matrix,Indicating that inertial matrix, G are gyroscopic effect matrix, Ω is rotor spin velocity,
Q is generalized displacement vector, KeFor stiffness matrix；QeExternal force suffered by expression system；Subscript e indicates axis element.
7. multistage components assembly method is equipped in large high-speed revolution according to claim 1, which is characterized in that the tenth step institute
State 85% that maximum (top) speed is specified maximum (top) speed --- 100%.
8. the large high-speed revolution based on BP neural network equips multistage components and assembles device, which is characterized in that the large size
It includes that air floating shaft system (2) is nested on pedestal (1) center that revolution at a high speed, which equips multistage components assembly device, and aligning tune inclines
Workbench (3) configures on air floating shaft system (2) center, and three precision force transducers (4a, 4b, 4c) are uniformly configured in aligning
Tune inclines on workbench (3)；Static balance measuring table (5) is on three precision force transducers (4a, 4b, 4c)；Left column (6) and the right side
Column (7) is symmetrically distributed in the two sides of air floating shaft system (2) and is packed on pedestal (1)；On left column (6) from top to bottom successively
Removable adjustably suit upper left transverse direction measuring staff (10) and lower-left transverse direction measuring staff (8), the telescopic inductance sensor in upper left (11) and
Upper left transverse direction measuring staff (10) is connected；The telescopic inductance sensor in lower-left (9) and lower-left transverse direction measuring staff (8) are connected；In right column (7)
On successively move adjustably suit upper right transverse direction measuring staff (14) and bottom right transverse direction measuring staff (12) from top to bottom, upper right lever is electric
Propagated sensation sensor (15) and upper right transverse direction measuring staff (14) are connected；Bottom right lever inductance sensor (13) and bottom right transverse direction measuring staff (12)
It is connected；Gate crossbeam (16) both ends and left column (6) upper end and right column (7) upper end are connected；It is removable on gate crossbeam (16)
Dynamic to be adjustably set with longitudinal measuring staff (17), the middle telescopic inductance sensor in position (18) and longitudinal measuring staff (17) are connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910217522.XA CN110153664B (en) | 2019-03-21 | 2019-03-21 | Method and device for assembling multistage parts of large-scale high-speed rotation equipment based on BP neural network |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910217522.XA CN110153664B (en) | 2019-03-21 | 2019-03-21 | Method and device for assembling multistage parts of large-scale high-speed rotation equipment based on BP neural network |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110153664A true CN110153664A (en) | 2019-08-23 |
| CN110153664B CN110153664B (en) | 2020-04-24 |
Family
ID=67638902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910217522.XA Active CN110153664B (en) | 2019-03-21 | 2019-03-21 | Method and device for assembling multistage parts of large-scale high-speed rotation equipment based on BP neural network |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110153664B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877751A (en) * | 2019-12-04 | 2020-03-13 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment rotational inertia stacking method based on vector projection |
| CN110906862A (en) * | 2019-12-02 | 2020-03-24 | 哈尔滨工业大学 | Geometric morphology and quality characteristic integrated measuring device for large-scale high-speed rotation equipment |
| CN111178506A (en) * | 2019-12-26 | 2020-05-19 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment deflection and inclination eliminating method based on deep belief neural network |
| CN111982402A (en) * | 2020-04-09 | 2020-11-24 | 西北工业大学 | Aircraft engine rotor part matching optimization method considering initial unbalance amount |
| CN115077920A (en) * | 2022-06-21 | 2022-09-20 | 大连理工大学 | Multistage turbine part assembly deformation test equipment |
| CN116441924A (en) * | 2023-06-19 | 2023-07-18 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4190431B2 (en) * | 2004-01-23 | 2008-12-03 | 本田技研工業株式会社 | Measuring device for static balance of rotating body |
| JP4878175B2 (en) * | 2006-02-24 | 2012-02-15 | Ｊｆｅメカニカル株式会社 | Balance inspection device |
| CN103790647A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Hydraulic capturing and clamping type aircraft engine rotor assembling method and device based on inductance sensing |
| CN105423876A (en) * | 2015-10-15 | 2016-03-23 | 哈尔滨工业大学 | Assembling measuring method and apparatus of large-scale high-speed revolution equipment based on tolerance regulation and control |
| CN206891656U (en) * | 2017-05-26 | 2018-01-16 | 广州市番禺远航螺旋桨制造有限公司 | Adjustable pitch propeller static balance measurement apparatus |
-
2019
- 2019-03-21 CN CN201910217522.XA patent/CN110153664B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4190431B2 (en) * | 2004-01-23 | 2008-12-03 | 本田技研工業株式会社 | Measuring device for static balance of rotating body |
| JP4878175B2 (en) * | 2006-02-24 | 2012-02-15 | Ｊｆｅメカニカル株式会社 | Balance inspection device |
| CN103790647A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Hydraulic capturing and clamping type aircraft engine rotor assembling method and device based on inductance sensing |
| CN105423876A (en) * | 2015-10-15 | 2016-03-23 | 哈尔滨工业大学 | Assembling measuring method and apparatus of large-scale high-speed revolution equipment based on tolerance regulation and control |
| CN206891656U (en) * | 2017-05-26 | 2018-01-16 | 广州市番禺远航螺旋桨制造有限公司 | Adjustable pitch propeller static balance measurement apparatus |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110906862A (en) * | 2019-12-02 | 2020-03-24 | 哈尔滨工业大学 | Geometric morphology and quality characteristic integrated measuring device for large-scale high-speed rotation equipment |
| CN110906862B (en) * | 2019-12-02 | 2022-01-25 | 哈尔滨工业大学 | Geometric morphology and quality characteristic integrated measuring device for large-scale high-speed rotation equipment |
| CN110877751A (en) * | 2019-12-04 | 2020-03-13 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment rotational inertia stacking method based on vector projection |
| CN110877751B (en) * | 2019-12-04 | 2021-04-30 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment rotational inertia stacking method based on vector projection |
| CN111178506A (en) * | 2019-12-26 | 2020-05-19 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment deflection and inclination eliminating method based on deep belief neural network |
| CN111982402A (en) * | 2020-04-09 | 2020-11-24 | 西北工业大学 | Aircraft engine rotor part matching optimization method considering initial unbalance amount |
| CN111982402B (en) * | 2020-04-09 | 2021-11-05 | 西北工业大学 | Aircraft engine rotor part matching optimization method considering initial unbalance amount |
| CN115077920A (en) * | 2022-06-21 | 2022-09-20 | 大连理工大学 | Multistage turbine part assembly deformation test equipment |
| CN116441924A (en) * | 2023-06-19 | 2023-07-18 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
| CN116441924B (en) * | 2023-06-19 | 2023-08-22 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110153664B (en) | 2020-04-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110153664A (en) | Multistage components assembly method and device are equipped in large high-speed revolution based on BP neural network | |
| CN110595690B (en) | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization | |
| US10794790B2 (en) | Large-scale high-speed rotary equipment measuring and neural network learning regulation and control method and device based on rigidity vector space projection maximization | |
| CN111475903B (en) | Multistage part dynamic characteristic step-by-step measuring and distributing method for large-scale high-speed rotary equipment based on multi-bias error synchronous compensation | |
| IT9020765A1 (en) | BALANCING METHOD OF GAS TURBOMOTOR ROTORS AND COS ~ PRODUCTS | |
| Huang et al. | The application of ball-type balancers for radial vibration reduction of high-speed optic disk drives | |
| CN111413031B (en) | Deep learning regulation and assembly method and device for large-scale high-speed rotation equipment based on dynamic vibration response characteristics | |
| CN109871947A (en) | Multistage components initial unbalance, stacking method and device step by step are equipped in large high-speed revolution based on convolutional neural networks | |
| CN109800512A (en) | Rotating cylindrical shell-variable cross-section disk-pretwist blade system dynamic modeling method | |
| CN110231133B (en) | Method for measuring current rigidity and displacement rigidity of magnetic suspension bearing | |
| CN104166758A (en) | Determination method for inherent frequency of rotor-blade coupled system | |
| CN105021352A (en) | Main shaft built-in mechanical on-line dynamic balancing system | |
| CN107133387A (en) | The imbalance compensation algorithm of rotor unbalance coefficient variable step polygon iterated search | |
| CN110457740B (en) | Response characteristic analysis method of mechanical structure under basic excitation | |
| CN105043737A (en) | Bearing retainer trajectory measurement method based on error separation technology | |
| CN103234729A (en) | Video measuring method of pneumatic rigidity and pneumatic damping in conventional wind tunnel force test | |
| WO2020019377A1 (en) | Dynamic design method for high-speed duplex rolling bearing electric spindle rotor system | |
| CN105478245B (en) | The double freedom precision centrifuge countershaft unbalancing value discrimination method detected based on spindle vibration | |
| CN102175394A (en) | Permanent calibration method in soft bearing dynamic unbalance test of rigid rotor | |
| CN102778333A (en) | Method for performing dynamic balance test on large rotating part | |
| CN117521244A (en) | Vibration response analysis method and system for elastic supporting structure in maneuvering flight state | |
| CN107448546A (en) | A kind of V8 diesel engines double-shaft balance design method | |
| CN109960870A (en) | Multistage components Stiffness Prediction method is equipped in the large high-speed revolution surveyed and adjusted that maximized based on contact area | |
| WO2023216451A1 (en) | Long-term method for monitoring dynamic balance of hypergravity centrifuge | |
| Kang et al. | Development and modification of a unified balancing method for unsymmetrical rotor-bearing systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |