CN109883380A - A kind of rotor blade displacement field measurement method and its system based on blade tip-timing - Google Patents
A kind of rotor blade displacement field measurement method and its system based on blade tip-timing Download PDFInfo
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Abstract
The invention discloses a kind of rotor blade displacement field measurement method and its system based on blade tip-timing, the described method comprises the following steps: establishing the three-dimensional finite element model of rotor blade to be measured, extract the modal parameter of the three-dimensional finite element model；Determine tip-timing sensor number and circumferential installation site；Establish the mapping relations of blade single-point displacement and whole audience displacement；Rotor blade end of blade single-point displacement is obtained based on the tip-timing sensor, the single-point displacement obtains the displacement of the rotor blade any position and any direction based on the mapping relations.Method provided by the invention can realize the reconstruct of rotor blade global displacement field merely with end of blade limited measure node, can realize the measurement of multiple modal vibrations lower rotor part blade surface and internal all modal displacements, calculating process is simple, is easy to on-line measurement.
Description
Technical field
The invention belongs to the contactless vibration test technology fields of aeroengine rotor blade, especially a kind of to be based on leaf
Hold the rotor blade displacement field measurement method and its system of timing.
Background technique
The integrality of blade directly affects the integrally-built safe operation of aero-engine, the harsh, load by working environment
The influence of the factors such as strong alternation, easily generates vibrating fatigue crackle during military service and leads to major accident.Blade vibration
High cycle fatigue caused by excessive is blade of aviation engine dominant failure mode.Rotor blade high cycle fatigue is mainly by various pneumatic
Dynamic stress caused by load, mechanical load causes, and can add up largely to recycle generation fatigue crack in a short time, especially work as
Dynamic stress easily causes blade fatigue to fail when blade resonates.In aero-engine development, production process, in order to grasp
Blade vibration characteristic needs to measure blade vibration.For a long time, blade of aviation engine is by rotor blade table
The mode that foil gauge is pasted in face realizes dynamic strain measure, this, which is only capable of measuring limited blade, an extreme position dynamic strain, reliability and
Continuous working period is lower, arranges that a large amount of foil gauges are typically only seldom foil gauge in turbo blade especially under hot environment
Available effective information, survival rate are extremely low.The characteristics of due to blade of aviation engine high speed rotation, based on the non-of blade tip-timing
Contact type measurement becomes the developing direction of blade vibration testing field research.Utilize the sensor sense being arranged close on the inside of casing
Know blade tip vibration information, referred to as " blade tip-timing ".Current blade tip-timing technology is aero-engine manufacture, test giant's concern
Hot spot, such as United States Air Force Arnold engineering developme center (AEDC) are proposed blade non-intrusion type stress test system (Non-
Intrusive Stress Measurement System, NSMS).
Disclosed above- mentioned information are used only for enhancing the understanding to background of the present invention in the background section, it is thus possible to
Information comprising not constituting the prior art known to a person of ordinary skill in the art in home.
Summary of the invention
Aiming at the problems existing in the prior art, the present invention proposes that a kind of rotor blade displacement field based on blade tip-timing is surveyed
Amount method and its system solve rotor blade blade tip-timing non-contact measuring technology and are only applicable to moving under single mode vibration
Strain estimation, and have while reconstructing the advantage of rotor blade surface and internal all modal displacement fields.
Non-contact measurement based on blade tip-timing (Blade Tip Timing, BTT) becomes contact strain measurement most
Promising alternative, blade tip-timing can measure the vaned vibration information of institute for example vibration frequency, amplitude, excitation order,
Resonance zone etc..However, blade tip-timing is only capable of surveying using the sensor perception blade tip vibration information being arranged close on the inside of casing
Amount end of blade has extreme position vibration, cannot achieve the displacement field reconstruct under any time multiple modal vibrations.Current blade tip-timing is surveyed
Method of slight is only applicable to the blade single-point displacement measurement under single mode vibration, cannot achieve the position under any time multiple modal vibrations
Move variable field reconstruct.It is of great significance for this purpose, the present invention vibrates inverting reconstruct rotor blade global displacement field by end of blade single-point.
The purpose of the present invention is being achieved by the following technical programs, a kind of rotor blade displacement based on blade tip-timing
Field measurement method the following steps are included:
In first step, the three-dimensional finite element model of rotor blade to be measured is established, extracts the three-dimensional finite element model
Modal parameter；
In second step, tip-timing sensor number and circumferential installation site are determined；
In third step, the mapping relations of blade single-point displacement and whole audience displacement are established；
In four steps, rotor blade end of blade single-point displacement is obtained based on the tip-timing sensor,
In 5th step, the single-point displacement is based on the mapping relations and obtains the rotor blade any position and any
The displacement in direction.
In the method, in first step, n before the three-dimensional finite element model is extracted by model analysismRank mode
Parameter, modal frequency fiIt is n with sizedof× 1 displacement modes vibration shape φi, construct rotor blade whole audience displacement modes vibration shape square
Battle arraySize is ndof×nm, wherein nmIt indicates to vibrate multi-modal number, i indicates mode order, ndof
Indicate the number of degrees of freedom of rotor blade finite element model, ndof=3nn, nnIndicate rotor blade finite element model interstitial content.
In the method, in second step, rotor blade casing circumferentially installs tip-timing sensor number nbttWith vibration
Move multi-modal number nmRelationship are as follows: nbtt≥2nm+1。
In the method, in second step, construct what tip-timing sensor casing under multi-modal excitation was circumferentially laid out
Measuring point selection matrix Sbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1), nbttExpression jth (j=1 ... nbtt) a end of blade
Timing circumferentially total number, EOiPay close attention to excitation order (i=1 ... nm), θjExpression jth (j=1 ... nbtt) a
Setting angle of the tip-timing sensor in casing circumferential direction；Using speed probe position as 0 ° of benchmark, and exclude casing
Setting angle range is limited, circumferentially randomly chooses n in casingbttA angle is as tip-timing sensor installation site；Calculate leaf
Hold timing measuring point selection matrix SbttConditional number κ, random process repeat R times and therefrom selection matrix conditional number κ minimum when measuring point
Arrangement.
In the method, in third step, the transition matrix of construction blade single-point displacement and the displacement of the blade whole audienceSize is ndof×nm；Wherein, φBtt, iIndicate blade blade tip-timing measuring point
The i-th rank displacement modes vibration shape.
In the method, in four steps, n is utilizedbttA tip-timing sensor obtains the leaf that rotor blade N turns
Hold multiple modal vibrations signal ubtt(t), and then using circumferential Fourier's fitting algorithm n is obtainedmRank vibration parameters:
Wherein,Amplitude Ai, modal frequency fi、
Initial phaseSubscriptRepresenting matrix it is inverse；The transposition of subscript T expression vector；Further, reconstruct obtains end of blade single-point multimode
State vibration signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade, ωiIndicate blade
Multiple modal vibrations circular frequency, t indicate the blade vibration moment.
In the method, in the 5th step, the multiple modal vibrations signal u based on transition matrix T and decouplingBtt, i(t), it counts
The each displacement field for turning blade surface and internal all node any directions of rotor blade is calculated, via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node；Wherein, uI, x(t) blade finite element model the is indicated
The displacement in the i direction node t moment x, uI, y(t) displacement in i-th of direction node t moment y of blade finite element model, u are indicatedI, z
(t) displacement in i-th of direction node t moment z of blade finite element model is indicated.
According to another aspect of the present invention, it is a kind of implement the method measuring system include,
Multiple tip-timing sensors, are arranged on the casing of rotor blade；
It is multi-modal to measure rotor blade circumferential direction end of blade to connect the tip-timing sensor for blade tip-timing vibration measuring module
Vibration signal；
Computing unit connects the blade tip-timing vibration measuring module, and the computing unit includes,
Model analysis module, be configured to three-dimensional finite element model based on rotor blade to be measured carry out model analysis with
N before acquisition rotor blademRank modal frequency fiDisplacement modes vibration shape φiAnd construction rotor blade whole audience displacement modes vibration
Type matrix
Measuring point preferred module is configured to the measuring point number of tip-timing sensor of the preferred arrangement on the rotor blade
Mesh, wherein construct the measuring point selection matrix S that tip-timing sensor casing under multi-modal excitation is circumferentially laid outbtt, revolving speed is passed
Sensor position excludes casing and limits setting angle range as 0 ° of benchmark, circumferentially randomly chooses n in casingbttA angle
As tip-timing sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ, random process repeat R times
And therefrom selection matrix conditional number κ minimum when point layout,
Transform matrix calculations module is configured to the transition matrix of construction blade single-point displacement and whole audience displacement,
Displacement field reconstructed module is configured to calculate each displacement for turning blade surface and internal any direction of rotor blade
, via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node；Wherein, uI, x(t) blade finite element model the is indicated
The displacement in the i direction node t moment x, uI, y(t) displacement in i-th of direction node t moment y of blade finite element model, u are indicatedI, z
(t) displacement in i-th of direction node t moment z of blade finite element model is indicated.
In the measuring system, blade tip-timing vibration measuring module includes several tip-timing sensors, a revolution speed sensing
Device, when m- displacement conversion module and signal conditioning module, wherein tip-timing sensor measurement blade reaches pulse signal；Turn
Fast sensor measurement blade rotation speed；When the pulse signal combination that tip-timing sensor measure of m- displacement conversion module
Tach signal obtains blade end of blade vibration displacement；Signal conditioning module is used to extract vibration frequency of blade and width from vibration displacement
Value parameter.
In the measuring system, measuring system further includes display unit and wireless telecom equipment, wireless telecom equipment packet
Include 4G/GPRS or the Internet communication module.
Beneficial effect
Rotor blade displacement field measurement method provided by the invention based on blade tip-timing is vibrated just merely with blade single-point
The measurement of global displacement field under rotor blade multiple modal vibrations can be achieved.It can not only realize blade surface displacement under multiple modal vibrations
The measurement of field, can also realize the measurement of blade interior modal displacement field.Breach blade tip-timing non-contact measuring technology only
Energy approximate reconstruction single mode vibrates the limitation of lower blade point displacement.It is simple to invent the method calculating process provided, is easy to online
Measurement.Multiple modal vibrations coupling and decoupling are considered, measurement accuracy is high, and rotor blade displacement field reconfiguration system process is simple, easily
In realization Detailed description of the invention
By reading the detailed description in hereafter preferred embodiment, various other advantages and benefits of the present invention
It will become apparent to those of ordinary skill in the art.Figure of description only for the purpose of illustrating preferred embodiments,
And it is not to be construed as limiting the invention.It should be evident that drawings discussed below is only some embodiments of the present invention,
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings
Other attached drawings.And throughout the drawings, identical component is presented with like reference characters.
In the accompanying drawings:
Fig. 1 is a kind of stream of rotor blade displacement field measurement method preferred embodiment based on blade tip-timing provided by the invention
Journey schematic diagram；
Fig. 2 (a) to Fig. 2 (b) is a kind of rotor blade displacement field measuring system based on blade tip-timing provided by the invention
Structural schematic diagram, wherein Fig. 2 (a) rotor blade displacement field reconfiguration system form；Fig. 2 (b) blade tip-timing vibration measuring module and leaf
Hold Time Pick-off Units circumferential direction scheme of installation；
Fig. 3 is that model rotor dynamic loads on blade energized position shows with tip-timing sensor point position in one embodiment
It is intended to；
Fig. 4 (a) to Fig. 4 (c) is the displacement modes vibration shape of rotor blade in one embodiment, wherein Fig. 4 (a) bending vibration
Type, Fig. 4 (b) torsional oscillation type；Two bending vibration type of Fig. 4 (c)；
Fig. 5 is circumferential 7 tip-timing sensors (BTT) actual measurement end of blade displacement vibration letter of rotor blade in one embodiment
Number；
Fig. 6 is the multi-modal decoupling result of rotor blade displacement signal in one embodiment；
Fig. 7 is the displacement component of node three of blade 748 and true in the rotor blade displacement field reconstructed in one embodiment
Real displacement comparison result；
Fig. 8 is three displacement components of neighbouring No. 345 nodes of blade root in the rotor blade displacement field reconstructed in one embodiment
With real displacement comparison result.
Below in conjunction with drawings and examples, the present invention will be further explained.
Specific embodiment
1 to Fig. 8 specific embodiment that the present invention will be described in more detail below with reference to accompanying drawings.Although showing this in attached drawing
The specific embodiment of invention, it being understood, however, that may be realized in various forms the implementation of the invention without that should be illustrated here
Example is limited.It is to be able to thoroughly understand the present invention on the contrary, providing these embodiments, and can be by model of the invention
It encloses and is fully disclosed to those skilled in the art.
It should be noted that having used some vocabulary in the specification and claims to censure specific components.Ability
Field technique personnel it would be appreciated that, technical staff may call the same component with different nouns.This specification and right
It is required that not in such a way that the difference of noun is as component is distinguished, but with the difference of component functionally as differentiation
Criterion."comprising" or " comprising " as mentioned throughout the specification and claims are an open language, therefore should be solved
It is interpreted into " including but not limited to ".Specification subsequent descriptions are to implement better embodiment of the invention, so the description be with
For the purpose of the rule of specification, the range that is not intended to limit the invention.Protection scope of the present invention is when the appended right of view
It is required that subject to institute's defender.
In order to facilitate understanding of embodiments of the present invention, further by taking specific embodiment as an example below in conjunction with attached drawing to be solved
Explanation is released, and each attached drawing does not constitute the restriction to the embodiment of the present invention.
In order to better understand, Fig. 1 is a rotor blade displacement field measurement method workflow based on blade tip-timing
Figure, as shown in Figure 1, a kind of rotor blade displacement field measurement method based on blade tip-timing the following steps are included:
In first step S1, the three-dimensional finite element model of rotor blade to be measured is established, extracts the three-dimensional finite element mould
The modal parameter of type；
In second step S2, tip-timing sensor number and circumferential installation site are determined；
In third step S3, the mapping relations of blade single-point displacement and whole audience displacement are established；
In four steps S4, rotor blade end of blade single-point displacement is obtained based on the tip-timing sensor,
In 5th step S5, the single-point displacement is based on the mapping relations and obtains the rotor blade any position and appoint
The displacement measurement in meaning direction.
In described one embodiment of method, in first step S1, the three-dimensional finite element is extracted by model analysis
N before modelmRank modal parameter, modal frequency fiIt is n with sizedof× 1 displacement modes vibration shape φi, construct the rotor blade whole audience
Displacement modes vibration shape matrixSize is ndof×nm, wherein nmIt indicates to vibrate multi-modal number, i
Indicate mode order, ndofIndicate the number of degrees of freedom of rotor blade finite element model, ndof=3nn, nnIndicate that rotor blade is limited
Meta-model interstitial content.
In described one embodiment of method, in second step S2, circumferentially installation blade tip-timing passes rotor blade casing
Sensor number nbttWith the multi-modal number n of vibrationmRelationship are as follows: nbtt≥2nm+1。
In described one embodiment of method, in second step S2, tip-timing sensor under multi-modal excitation is constructed
The measuring point selection matrix S that casing is circumferentially laid outbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1), EOiThe excitation order paid close attention to, θjIndicate jth
Setting angle of a tip-timing sensor in casing circumferential direction；Using speed probe position as 0 ° of benchmark, and exclude machine
Casket limits setting angle range, circumferentially randomly chooses n in casingbttA angle is as tip-timing sensor installation site；It calculates
Blade tip-timing measuring point selection matrix SbttConditional number κ, random process repeat R times and therefrom selection matrix conditional number κ minimum when survey
Point arrangement.
In described one embodiment of method, in third step S3, construction blade single-point displacement and the blade whole audience are displaced
Transition matrixSize is ndof×nm；Wherein, φBtt, iIndicate leaf
Piece blade tip-timing measuring point the i-th rank displacement modes vibration shape.
In described one embodiment of method, in four steps S4, n is utilizedbttA tip-timing sensor obtains rotor
The end of blade multiple modal vibrations signal u that blade N turnsbtt(t), and then using circumferential Fourier's fitting algorithm n is obtainedmRank vibration ginseng
Number:
Wherein,Amplitude Ai, modal frequency fi、
Initial phaseFurther, reconstruct obtains end of blade single-point multiple modal vibrations signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade.
In described one embodiment of method, in the 5th step S5, each blade surface and interior of turning of rotor blade is calculated
The displacement field of all node any directions in portion, via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node.
For a further understanding of the present invention, with reference to the accompanying drawing 1 to Fig. 8 and specific embodiment the present invention is further retouched
It states, it should be emphasised that, following the description is only exemplary, and application of the invention does not limit to following examples.
In one embodiment, specifically includes the following steps:
Fig. 1 is a kind of process signal for rotor blade displacement field measurement method based on blade tip-timing that the present invention completes
Figure, this method are measured end of blade single-point by the tip-timing sensor circumferentially installed using casing and vibrated, and circumferential Fourier is utilized
Approximating method realizes that multiple modal vibrations decoupling, the conversion of construction rotor blade end of blade displacement measuring points and all modal displacements of the whole audience are closed
System realizes the reconstruct of blade displacement field；Fig. 2 (a) to Fig. 2 (b) is a kind of rotor blade based on blade tip-timing provided by the invention
The structural schematic diagram of displacement field measuring system, wherein 1- tip-timing sensor；2- casing；3- rotor blade；4- wheel disc；5-
Rotor；6- speed probe.Specific step is as follows for method:
1) it extracts the modal parameter of blade three-dimensional finite element model: referring to Fig. 3, being built using ANSYS finite element analysis software
The three-dimensional finite element model of vertical model rotor straight blade, wherein material is aluminium, density 2700kg/m3, Poisson's ratio 0.33, bullet
Property modulus 72000MPa；The long 48mm of blade, thickness 1mm, wide 20mm；Finite element unit type is solid element SOLID185, section
Point sum is 3153；Blade root two sides fixed constraint, model rotor blade actual working state；
Utilize 3 rank modal parameters before ANSYS model analysis Frequency extraction, i.e. nm=3: modal frequency fi, size ndof×1
Displacement modes vibration shape φi, wherein first three rank modal frequency is respectively f1=333.08Hz, f2=1806.03Hz, f3=
2076.52Hz；Construct rotor blade whole audience displacement modes vibration shape matrixSize is ndof×nm, position
Moving Mode Shape sees Fig. 4 (a) to Fig. 4 (c)；I indicates mode order, ndof=9459 indicate the freedom degree of blade finite element model
Number, the displacement of each node include three displacement components usx、uy、uzComponent, i.e., each node have 3 displacement modes vibration shapes, then ndof
=3nn, nn=3153 indicate the number of blade finite element model node.
2) determine tip-timing sensor number and circumferential installation site: circumferentially installation blade tip-timing passes rotor blade casing
Sensor number nbttWith the multi-modal number n of vibrationmRelationship are as follows: nbtt≥2nm+1；In present case, concern model rotor blade first three
Rank mode of oscillation, takes nm=3；Casing circumferential direction tip-timing sensor number is at least nbtt=7；
Construct the measuring point selection matrix S that tip-timing sensor casing under multi-modal excitation is circumferentially laid outbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1)=7 × 7, EOiThe excitation order paid close attention to, θj
Indicate j-th of tip-timing sensor in the setting angle of casing circumferential direction；Three excitation orders of present case concern are respectively 4,
18 and 23, motivate first three rank mode of oscillation of rotor blade simultaneously under same rotating speed；Using speed probe position as base
It is 0 ° quasi-, and exclude casing and limit setting angle range, n is circumferentially randomly choosed in casingbtt=7 angles are passed as blade tip-timing
Sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ；This random process repeats R=500 times, and selects
Select measuring point position scheme when conditional number κ minimum.The 7 tip-timing sensor circumferential direction setting angles chosen be 3.12 °,
117.33 °, 183.42 °, 189.58 °, 303.71 °, 315.14 °, 351.08 °, corresponding measuring point selection matrix SbttConditional number
It is 3.4694.
3) establish the mapping relations of blade single-point displacement and whole audience displacement: construction blade single-point displacement turns with whole audience displacement
Change matrixSize is ndof×nm=9459 × 3；Wherein, φBtt, iTable
Show blade blade tip-timing measuring point the i-th rank displacement modes vibration shape.
4) rotor blade end of blade single-point displacement is obtained using tip-timing sensor: to mould in ANSYS finite element software
Quasi- rotor blade carries out transient analysis, and Tuned mass damper coefficient is set as α=12.1380, stiffness and damping coefficient be set as β=
8.1986×10-8, revolving speed 15000RPM, Simulated Aerodynamic Loads are to the multiple modal vibrations of rotor blade, to rotor blade end of blade
No. 1117 nodes X directions apply multifrequency harmonic excitation f (t)=cos (2 π f1t)+10cos(2πf2t)+20cos(2πf3T), it and takes
Reference of the displacement field as reconstruction result after transient analysis is stable；Utilize nbtt=7 tip-timing sensors obtain rotor leaf
The end of blade multiple modal vibrations signal u that piece N turnsbtt(t), referring to Fig. 5；Wherein, rotor blade often rotates a circle, and blade tip-timing passes
Sensor samples No. 1122 nodes Xs of end of blade and amounts to 25 175 data of circle of acquisition to 7 data of vibration signal, therefore blade tip-timing is believed
It number is serious lack sampling；Meanwhile Fig. 5 gives sample frequency fsNo. 1122 nodes Xs of end of blade are to vibration signal under=25000Hz
Data length be N=2500, sampling time t=N/fs=0.1s.
And then n is obtained using circumferential Fourier's fitting algorithmmRank vibration parameters:
Wherein,Amplitude Ai, modal frequency
fi, initial phaseFurther, reconstruct obtains end of blade single-point multiple modal vibrations signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade.Fig. 6 gives reality
It applies first three rank mode of oscillation of rotor blade displacement signal in example and decouples result.
5) it realizes the displacement measurement of rotor blade any position and direction: calculating each blade surface and interior of turning of rotor blade
The displacement field of all node any directions in portion:
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node.
Take typical generation of No. 345 nodes as displacement field High precision reconstruction near No. 748 nodes of rotor blade body and blade root
Table (see Fig. 3), conclusion are equally applicable to other nodes, for quantitative assessment rotor blade contactless displacement field weight of the invention
The performance of structure method, the blade 748 in the relative error of t ∈ [0,0.1] s interval computation reconstruction signal and real displacement, Fig. 7
Node ux、uy、uzThe displacement relative error in three directions is only 5.77%, 6.22% and 7.49% respectively.In Fig. 8 near blade root
No. 345 node ux、uy、uzThe displacement relative error in three directions is only 7.68%, 7.45% and 7.19% respectively.Therefore, this hair
A kind of rotor blade displacement field measurement method based on blade tip-timing of bright offer, can accurately reconstruct blade displacement field.
Method provided by the invention can realize the reconstruct of rotor blade global displacement field merely with end of blade limited measure node, can be real
The measurement of existing multiple modal vibrations lower rotor part blade surface and internal all modal displacements, calculating process is simple, is easy to on-line measurement.
The foregoing is merely illustrative of the preferred embodiments of the present invention, can be applicable to the whirlers such as aero-engine, gas turbine, steam turbine
In the fan/compressor of tool/turbine blade vibration test, it is not intended to limit the invention.
In another embodiment, method the following steps are included:
1) modal parameter of blade three-dimensional finite element model is extracted；
2) tip-timing sensor number and circumferential installation site are determined；
3) mapping relations of blade single-point displacement and whole audience displacement are established；
4) rotor blade end of blade single-point displacement is obtained using tip-timing sensor；
5) displacement measurement of rotor blade any position and direction is realized.
Further, step 1) establishes the three-dimensional finite element model of rotor blade, n before being extracted by model analysismRank mould
State parameter: modal frequency fi, size ndof× 1 displacement modes vibration shape φi；Construct rotor blade whole audience displacement modes vibration shape square
Battle arraySize is ndof×nm；I indicates mode order, ndofIndicate the freedom degree of blade finite element model
Number；The displacement of each node includes 3 displacement components usx、uy、uzComponent, i.e., each node have 3 displacement modes vibration shapes, then ndof=
3nn, nnIndicate the number of blade finite element model node.
Further, step 2) rotor blade casing circumferentially installs tip-timing sensor number nbttIt is multi-modal with vibrating
Number nmRelationship are as follows: nbtt≥2nm+1；Construct the measuring point selection that tip-timing sensor casing is circumferentially laid out under multi-modal excitation
Matrix Sbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1), EOiThe excitation order paid close attention to；Revolving speed is passed
Sensor position excludes casing and limits setting angle range as 0 ° of benchmark, circumferentially randomly chooses n in casingbttA angle
As tip-timing sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ；This random process weight
It is R times multiple, and measuring point position scheme when selector bar number of packages κ minimum.
Further, the transition matrix of step 3) construction blade single-point displacement and whole audience displacementSize is ndof×nd；Wherein, φBtt, iIndicate that blade blade tip-timing is surveyed
The i-th rank displacement modes vibration shape of point.
Further, step 4) utilizes nbttA tip-timing sensor obtains the multi-modal vibration of end of blade that rotor blade N turns
Dynamic signal ubtt(t), and then using circumferential Fourier's fitting algorithm n is obtainedmRank vibration parameters:
Wherein,Amplitude Ai, mode frequency
Rate fi, initial phaseFurther, reconstruct obtains end of blade single-point multiple modal vibrations signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade.
Further, step 5) calculates each displacement for turning blade surface and internal all node any directions of rotor blade
, via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node.
On the other hand, it is a kind of implement to state the measuring system of method include,
Multiple tip-timing sensors, are arranged on the casing of rotor blade；
It is multi-modal to measure rotor blade circumferential direction end of blade to connect the tip-timing sensor for blade tip-timing vibration measuring module
Vibration signal；
Computing unit connects the blade tip-timing vibration measuring module, and the computing unit includes,
Model analysis module, be configured to three-dimensional finite element model based on rotor blade to be measured carry out model analysis with
N before acquisition rotor blademRank modal frequency fiDisplacement modes vibration shape φiAnd construction rotor blade whole audience displacement modes vibration
Type matrix
Measuring point preferred module is configured to the measuring point number of tip-timing sensor of the preferred arrangement on the rotor blade
Mesh, wherein construct the measuring point selection matrix S that tip-timing sensor casing under multi-modal excitation is circumferentially laid outbtt, revolving speed is passed
Sensor position excludes casing and limits setting angle range as 0 ° of benchmark, circumferentially randomly chooses n in casingbttA angle
As tip-timing sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ, random process repeat R times
And therefrom selection matrix conditional number κ minimum when point layout,
Transform matrix calculations module is configured to the transition matrix of construction blade single-point displacement and whole audience displacement,
Displacement field reconstructed module is configured to calculate each displacement for turning blade surface and internal any direction of rotor blade
, via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node.
In one embodiment of the measuring system, blade tip-timing vibration measuring module include at least one speed probe,
Signal conditioning module and when m- displacement conversion module.
In one embodiment, measuring system further includes display unit and wireless telecom equipment, and wireless telecom equipment includes
4G/GPRS or the Internet communication module.
In one embodiment, model analysis module, measuring point preferred module, transform matrix calculations module or displacement field reconstruct
Module be general processor, digital signal processor, application-specific integrated circuit ASIC or on-site programmable gate array FPGA,
Model analysis module, measuring point preferred module, transform matrix calculations module or displacement field reconstruct in one embodiment
Module includes memory, and the memory includes one or more read only memory ROM, random access memory ram, flash memory
Reservoir or Electrical Erasable programmable read only memory EEPROM.
Another aspect of the present invention additionally provides a kind of such as a kind of above-mentioned rotor blade displacement field based on blade tip-timing
Measurement method includes: with system
Model analysis module: for establishing the three-dimensional finite element model of rotor blade, n before being extracted by model analysismRank
Modal parameter: modal frequency fi, size 2ndof× 1 displacement modes vibration shape φi；Construct the vibration of rotor blade whole audience displacement modes
Type matrixSize is ndof×nm；I indicates mode order, ndofIndicate blade finite element model
Number of degrees of freedom；The displacement of each node includes 3 displacement components usx、uy、uzComponent, i.e., each node have 3 displacement modes vibration shapes,
Then ndof=3nn, nnIndicate the number of blade finite element model node.
Measuring point preferred module: rotor blade casing circumferentially installs tip-timing sensor number nbttWith the multi-modal number of vibration
Mesh nmRelationship are as follows: nbtt≥2nm+1；Construct the measuring point selection square that tip-timing sensor casing is circumferentially laid out under multi-modal excitation
Battle array Sbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1), EOiThe excitation order paid close attention to；Revolving speed is passed
Sensor position excludes casing and limits setting angle range as 0 ° of benchmark, circumferentially randomly chooses n in casingbttA angle
As tip-timing sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ；This random process weight
It is R times multiple, and measuring point position scheme when selector bar number of packages κ minimum.
Transform matrix calculations module: the transition matrix of blade single-point displacement and whole audience displacement is madeSize is ndof×nm；Wherein, φBtt, iIndicate blade blade tip-timing
Measuring point the i-th rank displacement modes vibration shape.
Blade tip-timing vibration measuring module: including several tip-timing sensors, at least one speed probe, signal condition mould
Block, when m- displacement conversion module；Utilize nbttA tip-timing sensor obtains the end of blade multiple modal vibrations that rotor blade N turns
Signal ubtt(t), and then using circumferential Fourier's fitting algorithm n is obtainedmRank vibration parameters:
Wherein,Amplitude Ai, mode frequency
Rate fi, initial phaseFurther, reconstruct obtains end of blade single-point multiple modal vibrations signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade.
Displacement field reconstructed module: each displacement for turning blade surface and internal all node any directions of rotor blade is calculated
, via formula
It is calculated,
Wherein,
Table
Show the displacement of t moment blade surface and internal all three directions of node.
Although embodiment of the present invention is described in conjunction with attached drawing above, the invention is not limited to above-mentioned
Specific embodiments and applications field, above-mentioned specific embodiment are only schematical, directiveness, rather than restricted
's.Those skilled in the art are under the enlightenment of this specification and in the range for not departing from the claims in the present invention and being protected
In the case where, a variety of forms can also be made, these belong to the column of protection of the invention.
Claims (10)
1. a kind of rotor blade displacement field measurement method based on blade tip-timing, the described method comprises the following steps:
In first step (S1), the three-dimensional finite element model of rotor blade to be measured is established, extracts the three-dimensional finite element model
Modal parameter；
In second step (S2), tip-timing sensor number and circumferential installation site are determined；
In third step (S3), the mapping relations of blade single-point displacement and whole audience displacement are established；
In four steps (S4), rotor blade end of blade single-point displacement is obtained based on the tip-timing sensor；
In 5th step (S5), the single-point displacement is based on the mapping relations and obtains the rotor blade any position and any
The displacement in direction.
2. according to the method described in claim 1, wherein, it is preferred that in first step (S1), extracted by model analysis described in
N before three-dimensional finite element modelmRank modal parameter, modal frequency fiIt is n with sizedof× 1 displacement modes vibration shape φi, construction turn
Blades whole audience displacement modes vibration shape matrixSize is ndof×nm, wherein nmIndicate that vibration is more
Mode number, i indicate mode order, ndofIndicate the number of degrees of freedom of rotor blade finite element model, ndof=3nn, nnIt indicates to turn
Blades finite element model interstitial content.
3. according to the method described in claim 1, wherein, in second step (S2), circumferentially installation end of blade is fixed for rotor blade casing
When number of sensors nbttWith the multi-modal number n of vibrationmRelationship are as follows: nbtt≥2nm+1。
4. according to the method described in claim 1, wherein, in second step (S2), constructing blade tip-timing under multi-modal excitation and passing
The measuring point selection matrix S that sensor casing is circumferentially laid outbtt:
Wherein, measuring point selection matrix SbttSize is nbtt×(2nm+ 1), nbttExpression jth (j=1 ... nbtt) a blade tip-timing week
To arrangement total number, EOiPay close attention to excitation order (i=1 ... nm), θjExpression jth (j=1 ... nbtt) a end of blade is fixed
When sensor casing circumferential direction setting angle；Using speed probe position as 0 ° of benchmark, and exclude casing limitation peace
Angular range is filled, circumferentially randomly chooses n in casingbttA angle is as tip-timing sensor installation site；Calculate blade tip-timing
Measuring point selection matrix SbttConditional number κ, random process repeat R times and therefrom selection matrix conditional number κ minimum when point layout.
5. according to the method described in claim 2, wherein, in third step (S3), constructing blade single-point displacement and the blade whole audience
The transition matrix of displacementSize is ndof×nm；Wherein, φBtt, iIt indicates
Blade blade tip-timing measuring point the i-th rank displacement modes vibration shape.
6. according to the method described in claim 5, wherein, in four steps (S4), utilizing nbttA tip-timing sensor obtains
The end of blade multiple modal vibrations signal u that rotor blade N turnsbtt(t), and then using circumferential Fourier's fitting algorithm n is obtainedmRank vibration
Dynamic parameter:
Wherein,Amplitude Ai, modal frequency fi、
Initial phaseSubscriptRepresenting matrix it is inverse；The transposition of subscript T expression vector；Further, reconstruct obtains end of blade single-point multimode
State vibration signal:
Wherein, uBtt, i(t) indicate that the i-th rank modal vibration signal after decoupling, c indicate the quiet deformation of blade, ωiIndicate blade multimode
State vibrates circular frequency, and t indicates the blade vibration moment.
It is multi-modal based on transition matrix T and decoupling in the 5th step (S5) 7. according to the method described in claim 6, wherein
Vibration signal uBtt, i(t), each displacement field for turning blade surface and internal all node any directions of rotor blade, warp are calculated
By formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node；Wherein, uI, x(t) blade finite element mould is indicated
The displacement in i-th of direction node t moment x of type, uI, y(t) position in i-th of direction node t moment y of blade finite element model is indicated
It moves, uI, z(t) displacement in i-th of direction node t moment z of blade finite element model is indicated.
8. a kind of measuring system for implementing any one of claim 1-7 the method, the measuring system include,
Multiple tip-timing sensors, are arranged on the casing of rotor blade；
Blade tip-timing vibration measuring module connects the tip-timing sensor to measure rotor blade circumferential direction end of blade multiple modal vibrations
Signal；
Computing unit connects the blade tip-timing vibration measuring module, and the computing unit includes,
Model analysis module is configured to the three-dimensional finite element model based on rotor blade to be measured and carries out model analysis to obtain
N before rotor blademRank modal frequency fiDisplacement modes vibration shape φiAnd construction rotor blade whole audience displacement modes vibration shape square
Battle array
Measuring point preferred module, tool are configured to the measure-point amount of tip-timing sensor of the preferred arrangement on gone back rotor blade,
Wherein, the measuring point selection matrix S that tip-timing sensor casing under multi-modal excitation is circumferentially laid out is constructedbtt, by speed probe
Position excludes casing and limits setting angle range as 0 ° of benchmark, circumferentially randomly chooses n in casingbttA angle conduct
Tip-timing sensor installation site；Calculate blade tip-timing measuring point selection matrix SbttConditional number κ, random process repeat R times and from
Point layout when middle selection matrix conditional number κ minimum,
Transform matrix calculations module is configured to the transition matrix of construction blade single-point displacement and whole audience displacement,
Displacement field reconstructed module is configured to calculate each displacement field for turning blade surface and internal any direction of rotor blade,
It is via formula
It is calculated,
Wherein,
Indicate the displacement of t moment blade surface and internal all three directions of node；Wherein, uI, x(t) blade finite element mould is indicated
The displacement in i-th of direction node t moment x of type, uI, y(t) position in i-th of direction node t moment y of blade finite element model is indicated
It moves, uI, z(t) displacement in i-th of direction node t moment z of blade finite element model is indicated.
9. measuring system according to claim 8, wherein blade tip-timing vibration measuring module includes several blade tip-timing sensings
Device, a speed probe, when m- displacement conversion module and signal conditioning module, wherein tip-timing sensor measures blade
Reach pulse signal；Speed probe measures blade rotation speed；When m- displacement conversion module tip-timing sensor is measured
Pulse signal combination tach signal obtain blade end of blade vibration displacement；Signal conditioning module from vibration displacement for extracting leaf
Piece vibration frequency and magnitude parameters.
10. measuring system according to claim 8, wherein measuring system further includes display unit and wireless telecom equipment,
Wireless telecom equipment includes 4G/GPRS or the Internet communication module.
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