CN106124615B - A kind of aero-engine low-pressure turbine reel fastening force detection method and device based on current vortex sensor group - Google Patents
A kind of aero-engine low-pressure turbine reel fastening force detection method and device based on current vortex sensor group Download PDFInfo
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- CN106124615B CN106124615B CN201610819203.2A CN201610819203A CN106124615B CN 106124615 B CN106124615 B CN 106124615B CN 201610819203 A CN201610819203 A CN 201610819203A CN 106124615 B CN106124615 B CN 106124615B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
- G01N27/72—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables
- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
- G01N27/9046—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents by analysing electrical signals
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/24—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for determining value of torque or twisting moment for tightening a nut or other member which is similarly stressed
Abstract
The aero-engine low-pressure turbine reel fastening force detection method and device based on current vortex sensor group that the invention discloses a kind of, the detection method have following steps: obtaining low-pressure turbine bolt pretightening and upper and lower disk relative displacement size, the relationship of distribution；Low-pressure turbine shaft dish structure disk relative displacement up and down during test set-up or after assembly；Judge each bolt to be measured or adjacent bolt with the presence or absence of pretightning force deficiency or phenomenon bigger than normal；Determine the unreasonable bolt of pretightning force and pretightning force deviation.The present invention passes through measurement aero-engine low-pressure turbine reel upper lower burrs face relative displacement, quickly, accurate judgement tools for bolts ' pretension state, it does not need to destroy bolt arrangement in measurement process, precision is higher than the current mode for directly measuring lag bolt length, measure disk relative displacement up and down, and the disk relative displacement deviation that pretightning force deviation is acted on relative to desired value, avoid influence of the disk base coordinate offset to measurement data during pre-tightening.
Description
Technical field
The invention belongs to aero-engine mounting technologies, and in particular to a kind of aeroplane engine based on current vortex sensor group
Machine low-pressure turbine reel fastening force detection method and device.
Background technique
Aero-engine low-pressure turbine is a kind of structure that the power of low-pressure turbine disk is passed to fan, its work turns
Fast high, transmitting torque value is big.The assembly work of low-pressure turbine reel is mainly tightened operation by bolt and is formed, and screwing force size is twisted
Tight sequence, the fastening procedures parameter such as tighten number can the pretightning force size to bolt have an impact, boundary then is connected for axis-disk
Face contact stress, disk deform and the generations such as low-pressure turbine shaft concentricity, low-pressure turbine reel dynamic stiffness and dynamic stability
It significantly affects, unreasonable fastening procedure will reduce aero-engine low-pressure turbine shaft operational reliability.
Erecting yard is torque value when tightening bolt by monitoring to control the size of the pretightning force of bolt at present, it is difficult to
Accurately guarantee the consistency of each Axial stress in bolt.During tools for bolts ' pretension, input energy only has about 10% to be converted into bolt
Pretightning force, other about 90% are converted into bolt-connected piece contact face and screw thread facing frictional dissipation, end face and facing friction
The minor fluctuations of coefficient will lead to the inconsistency of Axial stress in bolt；Applying torque during pre-tightening often makes bolt reach elasticity-
Plasticity critical state, torque and pretightning force are no longer complies with linear relationship, more accurately control pretightning force and propose problem；Even if adopting
Meet control strategy with torque-corner, end face coefficient of friction between different bolts, facing coefficient of friction otherness also lead to spiral shell
There is randomness in bolt axial force；Aero-engine low-pressure turbine reel connecting bolt number reaches dozens of, mainly uses people at present
Work tightening way, certain bolts, which are also easy to happen, tightens hypodynamic problem.
Test one of the method that bolt elongate amount during pre-tightening is accurate control pretightning force, but aero-engine low pressure whirlpool
Hub discs bolt belongs to lag bolt, it is contemplated that the error of test equipment is also difficult to accurately survey using equipment such as ultrasonic horizontal metroscopes
Such fixed bolt pretightening.
The connection of aero-engine low-pressure turbine reel pre-tightens force test method and has no pertinent literature.The prior art has following several
Kind method:
1) CN 105241598 discloses " a kind of engine rotor pre-tightens force measuring method and system ", in engine rotor
Center pull rod on choose the cross section that will not interfere with other parts as measurement section, on the circumference outer at measurement interface
Fiber Bragg grating strain sensor is set, and transmitting optical signal is to fiber Bragg grating strain sensor and reception optical fiber grating strain transducer
The light beam of reflection, the center wavelength shift for the light beam that fiber Bragg grating strain sensor reflects based on the received obtain fiber grating and answer
Become the strain value of sensor, and then obtains the axial pre tightening force of center pull rod.But it is drawn centered on the engine rotor connection structure
Bar, it is different with low-pressure turbine shaft disk bolt connecting mode, it is arranged for low-pressure turbine reel connection structure dozens of bolt
Fiber-optic grating sensor is difficult, and is difficult to ensure that each bolt of low-pressure turbine shaft is not interfered with connected piece.
2) 102519652 B of CN discloses " a kind of device and its control method for testing bolt pretightening ", by spiral shell
Measurement servicing unit is installed on bolt and realizes that pretightning force measures indirectly；103439035 B of CN discloses that " a kind of threaded fastener is pre-
Clamp force measurement method and its measuring device ", by being pre-tightened in fastener and by a threaded fastener is installed between securing objects
Force measuring device realizes measurement；103616118 B of CN discloses " detection system of bolt and its pretightning force, control method ", leads to
It crosses on the outer surface in bolt light rod section and attaches foil gauge, first through hole is opened up on bolt head, conducting wire passes through first through hole, will
Foil gauge and measuring mechanism, which are attached, realizes pretightning force measurement；CN 103884463 discloses that " composite material connection structure is pre-
Clamp force on-line monitoring method ", strain transducer is embedded in metal bolts, the Measurement channel phase of strain transducer and deformeter
Even, the pretightning force that test bolt is born；CN204493395U discloses " a kind of intelligent bolt ", offers through-hole including inside
Bolt body, fiber-optic grating sensor ontology are fixed in the through-hole of bolt body by fixed plug screw.But aviation is sent out
In motivation low-pressure turbine reel assembling process, do not allow that pressure sensor is installed between fastener and connected piece, because of peace
On the one hand dress pressure sensor will affect connector, connected piece rigidity ratio, while also influencing that surface pressure is combined to be distributed and use
The reliability of process；Low-pressure turbine reel connection bolt does not allow in the positions drilling such as bolt head yet, and is placed in bolt
Sensor, to avoid bolt use reliability is influenced；The densely arranged of bolt also determines hardly possible in low-pressure turbine reel connection structure
To connect attachment device test Axial stress in bolt.
3) CN 104791351 is disclosed " optical measurement of fastener pretightning force ", which includes head, bar, and
With outer surface and axially extending channel in the outer surface, the Strain sensing material of optical transmission fills the channel,
Torque is applied to the fastener simultaneously by transmitting light to the feeder connection being filled, measurement is filled the exit in channel
Photoelectricity frequency, determine pretightning force on the fastener according to frequency is measured；6,829,944 B1 of US discloses a kind of fastening
Part tension measuring system is measured tight by measurement fastener head deformation according to the functional relation of the deflection and fastening force
Gu power, optical measurement, capacitance type sensor, optical imagery, pneumatic gauging and compression electricity is can be used in fastener head deformation measurement
Resistive measurement method；Sayed A.Nassar, Aidong Meng etc. is proposed using speckle interference technology, is connected by monitoring
The method of fitting displacement monitoring bolt clipping forcee.But aero-engine low-pressure turbine reel connection bolt does not allow at it
Surface makes axially extending passage；On the other hand, densely arranged tens of in flange arrangement in aero-engine reel connection structure
A bolt, pitch of bolts are only several millimeters, and connected piece stress, deformation state are presented as that more bolts and the comprehensive of connected piece are made
With, it is constrained each other between different bolts, connected piece deformation mechanism, deformation distributional pattern etc. and Sayed A.Nassar,
Single bolt arrangement of the researchs such as Aidong Meng is different.
Aero-engine low-pressure turbine reel connection structure is with a thickness of several millimeters, in assembling process, the lower boat of pretightning force effect
Micro-strain will occur for empty engine low-pressure turbine reel disk, but low-pressure turbine reel connection structure is more bolted-on attachments
Structure influences each other between more bolts, and adjacent bolt spacing is only several millimeters, and disk deformation is comprehensive to be presented as that load effect is lower and become
The transmitting of shape amount and effect of contraction.On the other hand, it is hundreds of that aero-engine low-pressure turbine reel connection structure, which is outside diameter,
How fastly the flange face of millimeter, is attached using tens of bolts, low for entire disk progress displacement testing efficiency,
Speed accurately determines that each tools for bolts ' pretension state is also problem to be solved in practical application.
Summary of the invention
The shortcomings that being applied to aero-engine low-pressure turbine reel connection bolt pretightening test aspect in view of the prior art
And deficiency, lower thin-wall part deformation rule is intensively acted in conjunction with more bolts, invent it is a kind of quickly, it is accurate, based on current vortex sensor
The aero-engine low-pressure turbine reel fastening force detection method and device of group.The technological means that the present invention uses is as follows:
A kind of aero-engine low-pressure turbine reel fastening force detection method based on current vortex sensor group has as follows
Step:
S1, low-pressure turbine bolt pretightening and upper and lower disk relative displacement size, the relationship of distribution are obtained:
S11, each bolt on low-pressure turbine reel is tightened, select end face coefficient of friction, facing coefficient of friction and
The consistent bolt of axial force, and record its position on low-pressure turbine reel；
S12, production low-pressure turbine reel test specimen identical with the low-pressure turbine reel, by crossing method on test specimen
Bolt tightened, and bolt corresponding with position described in step S11 is numbered, is denoted as 1,2 ... nmax-1、
nmax；
S13, in 3~n of numbermaxThree bolts are successively chosen in the range of -2, and are individually identified as n1、n2、n3；
S14, pretightning force is applied by following four operating condition to three bolts of selection:
A) three bolt pretightenings are desired value；
B) bolt pretightening is insufficient or bolt pretightening bigger than normal, other is desired value；
C) adjacent two bolt pretightenings are insufficient or bolt pretightening bigger than normal, other is desired value；
D) two bolt pretightenings for being spaced a bolt are insufficient or bolt pretightening bigger than normal, other is desired value；
S15, n under different operating conditions is obtained1-n2、n2-n3The phase of intermediate region low-pressure turbine reel upper lower burrs face position (x, y)
To shift value u (x, y)=ua(x,y)-ul(x, y), wherein ua(x,y)、ul(x, y) is respectively the upper and lower disk position in the position (x, y)
Shifting value, it is contemplated that the relative displacement under value effect is identified as un(x, y) then uses Δ u (x, y)=u (x, y)-un(x, y) mark
The disk relative displacement variation of position (x, y) under bolt pretightening is insufficient or state bigger than normal, according to test result establish Δ u (x,
Y) relationship between pretightning force size:
Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y),
Wherein Fn1To be applied to n1On pretightning force, Fn2To be applied to n2On pretightning force, Fn3To be applied to n3On it is pre-
Clamp force；
S16, for the n under different working conditions, the effect of different pretightning force1-n2、n2-n3The each position Δ u in intermediate region
(x, y) is tested, is analyzed, the Axial stress in bolt deviation in conjunction with caused by facing coefficient of friction, end face coefficient of friction deviation and low
The requirement of turbine reel fastening performance is pressed, determines and determines bolt pretightening deficiency or threshold value bigger than normal:
Δuc(x, y)=f (Fe, x, y),
Wherein FeFor the desired value pretightning force of each bolt；
Low-pressure turbine shaft dish structure disk relative displacement up and down during S2, test set-up or after assembly:
S21, the vertical center line ab for doing bolt to be measured Yu adjacent bolt line, wherein a, b two o'clock are respectively test set-up
The flange arrangement edge of low-pressure turbine shaft dish structure in the process or after assembly, if c is the midpoint ab, d, e, f, g are the ginseng on ab
Examination point remembers that bolt number to be measured is nc；
S22, current vortex sensor group is moved along ab, respectively at uniformly acquiring 3~5 positions within the scope of a-d, f-g, e-b
The disk relative displacement u (x of pointci,yci)=ua(xci,yci)-ul(xci,yci), wherein ua(xci,yci)、ul(xci,yci) respectively
For (xci,yci) the upper and lower disk shift value in position, the set U of each acquisition position point relative displacementcIt is pre- to constitute description bolt to be measured
The characteristic quantity of clamp force, Uc={ u (xc1,yc1),u(xc2,yc2),...,u(xcn,ycn)}；
It S23, is to judge all tools for bolts ' pretension states in low-pressure turbine shaft dish structure, successively obtaining number is 1,3,5 ...
nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point relative displacement set；
S3, judge each bolt to be measured or adjacent bolt with the presence or absence of pretightning force deficiency or phenomenon bigger than normal:
Number according to acquisition is 1,3,5 ... nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point it is opposite
The set of shift value, it is unified in a figure to draw corresponding " position-relative displacement " curve of each bolt, curve co-insides region
Identifying corresponding bolt pretightening is desired value, and it is insufficient or bigger than normal that curve deflected areas identifies corresponding bolt pretightening, and obtains
To the relative displacement deviation collection of bolt to be measured
Wherein
Δu(xci,yci) it is (xci,yci) the upper and lower disk relative displacement in position and desired value act on lower relative displacement
Difference, un(xci,yci) be desired value effect under relative displacement；ΔUcIf there are Δ u (x for 50% or more location point inci,
yci) > Δ uc(xci,yci), then can determine that bolt or adjacent bolt to be measured there are pretightning force is insufficient or the excessive phenomenon of pretightning force,
In, Δ uc(xci,yci)=Δ uc(x, y)=g (Fn1,Fn2,Fn3,x,y)；
S4, the unreasonable bolt of pretightning force and pretightning force deviation are determined:
If pq is ab vertical center line, o point is the intersection point of pq and ab, and w, v point are respectively the midpoint po, oq, move electricity along pq
Eddy current sensor group successively measures the corresponding disk relative displacement of p, w, o, v, q each point, obtains the corresponding phase of pretightning force deviation
To displacement feature set Ud={ u (xp,yp),u(xw,yw),u(xo,yo),u(xv,yv),u(xq,yq),
It and with adjacent bolt is compared with desired value acts on lower disk relative shift, to obtain the corresponding disk of pretightning force deviation
Face displacement variable
Excluding Axial stress in bolt random error influences, if it exists Δ u (xp,yp) it is greater than Δ u (xq,yq), and Δ u (xw,
yw) it is greater than Δ u (xv,yv), then it is insufficient or bigger than normal close to p point bolt pretightening, if Δ u (xq,yq) it is greater than Δ u (xp,yp), and Δ
u(xv,yv) it is greater than Δ u (xw,yw), then it is insufficient or bigger than normal close to q point bolt pretightening, and then according to deviation and pretightning force
Mapping relations Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y), it is specific to determine bolt pretightening deviation.
It tightens and is referred to using Axial stress in bolt test macro to the progress of each bolt 3 times or more described in the step S11
It tightens.
Made in the step S12 identical with low-pressure turbine reel low-pressure turbine reel test specimen refer to production and
The same material of the low-pressure turbine reel, same flange internal-and external diameter, same flange thickness, same pitch of bolts, faying face precision
1/4 low-pressure turbine reel test specimen.
The desired value is to tighten torque value needed for bolt.
D is located on ac line away from b point 5mm, f away from a point 5mm, e, is located on bc line, away from c point 3mm, g away from c in the S21
Point 3mm.
P, q point are respectively away from o point 2mm in the step S4.
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor, two current vortex sensors are coaxial, and spacing is fixed.
The aero-engine low-pressure turbine reel fastening force inspection based on current vortex sensor group that the invention also discloses a kind of
Test device is surveyed, including base station, current vortex sensor feed arrangement and the V shape iron I being arranged successively along straight line, V shape iron II and V-arrangement
Iron III, the V shape iron I are connect by pedestal with the base station, and the V shape iron II passes sequentially through horizontal feed platform I and lifting
Platform I is connect with the base station, and the V shape iron III passes sequentially through horizontal feed platform II and hoistable platform II and the base station connects
It connects, is equipped with pressing plate on the V shape iron I, the V shape iron II and the V shape iron III,
The current vortex sensor feed arrangement includes sequentially connected current vortex sensor group, sensor collet, radial direction
Micrometer feed platform, angle position platform, vertical feeding platform and horizontal feed platform III, the horizontal feed platform I, it is described it is horizontal into
It is each perpendicular to the straight line to the direction of feed of platform II and the horizontal feed platform III,
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor, two current vortex sensors are coaxial, and spacing is fixed.
The invention has the following advantages that
1, by measurement the face relative displacement of aero-engine low-pressure turbine reel upper lower burrs, quickly, accurate judgement bolt it is pre-
Tight state does not need in measurement process to destroy bolt arrangement, and precision is higher than the mode of current directly measurement lag bolt length；
2, it is inclined to measure the disk relative displacement that disk relative displacement and pretightning force deviation are acted on relative to desired value up and down
Difference avoids influence of the disk base coordinate offset to measurement data during pre-tightening；
3, the measuring device based on current vortex sensor group improves detection efficiency and detection accuracy, and it is automatic to be conducive to assembly
The realization of change.
The present invention can be widely popularized in fields such as aero-engine mounting technologies based on the above reasons.
Detailed description of the invention
The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.
Fig. 1 is to be vertical center line ab on bolt to be measured and adjacent bolt line in a specific embodiment of the invention
Schematic diagram.
Fig. 2 is the relative displacement bias trend curve of disk up and down in a specific embodiment of the invention along ab by a to b
Figure.
Fig. 3 is the vertical center line pq for being ab in a specific embodiment of the invention between bolt to be measured and adjacent bolt
Schematic diagram.
Fig. 4 is the relative displacement bias trend of disk up and down in the specific embodiment of invention along pq by p to q
Curve graph.
Fig. 5 is a kind of aero-engine low-pressure turbine based on current vortex sensor group in a specific embodiment of the invention
The structural schematic diagram of reel fastening force detection test device.
Fig. 6 is the structural schematic diagram of current vortex sensor feed arrangement in a specific embodiment of the invention.
Fig. 7 is that two current vortex sensors and low-pressure turbine reel positional relationship are illustrated in a specific embodiment of the invention
Figure.
Specific embodiment
A kind of aero-engine low-pressure turbine reel fastening force detection method based on current vortex sensor group has as follows
Step:
S1, low-pressure turbine bolt pretightening and upper and lower disk relative displacement size, the relationship of distribution are obtained:
S11, each bolt on low-pressure turbine reel is tightened, select end face coefficient of friction, facing coefficient of friction and
The consistent bolt of axial force, and record its position on low-pressure turbine reel；
S12, production low-pressure turbine reel test specimen identical with the low-pressure turbine reel, by crossing method on test specimen
Bolt tightened, and bolt corresponding with position described in step S11 is numbered, is denoted as 1,2 ... nmax-1、
nmax；
S13, in 3~n of numbermaxThree bolts are successively chosen in the range of -2, and are individually identified as n1、n2、n3, nmaxFor
Maximum bolt number；
S14, pretightning force is applied by following four operating condition to three bolts of selection:
A) three bolt pretightenings are desired value；
B) bolt pretightening is insufficient or bolt pretightening bigger than normal, other is desired value；
C) adjacent two bolt pretightenings are insufficient or bolt pretightening bigger than normal, other is desired value；
D) two bolt pretightenings for being spaced a bolt are insufficient or bolt pretightening bigger than normal, other is desired value；
S15, n under different operating conditions is obtained1-n2、n2-n3The phase of intermediate region low-pressure turbine reel upper lower burrs face position (x, y)
To shift value u (x, y)=ua(x,y)-ul(x, y), wherein ua(x,y)、ul(x, y) is respectively the upper and lower disk position in the position (x, y)
Shifting value, it is contemplated that the relative displacement under value effect is identified as un(x, y) then uses Δ u (x, y)=u (x, y)-un(x, y) mark
The disk relative displacement variation of position (x, y) under bolt pretightening is insufficient or state bigger than normal, according to test result establish Δ u (x,
Y) relationship between pretightning force size:
Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y),
Wherein Fn1To be applied to n1On pretightning force, Fn2To be applied to n2On pretightning force, Fn3To be applied to n3On it is pre-
Clamp force；
S16, for the n under different working conditions, the effect of different pretightning force1-n2、n2-n3The each position Δ u in intermediate region
(x, y) is tested, is analyzed, the Axial stress in bolt deviation in conjunction with caused by facing coefficient of friction, end face coefficient of friction deviation and low
The requirement of turbine reel fastening performance is pressed, determines and determines bolt pretightening deficiency or threshold value bigger than normal:
Δuc(x, y)=f (Fe, x, y),
Wherein FeFor the desired value pretightning force of each bolt；
Low-pressure turbine shaft dish structure disk relative displacement up and down during S2, test set-up or after assembly:
S21, the vertical center line ab for doing bolt to be measured Yu adjacent bolt line, wherein a, b two o'clock are respectively test set-up
The flange arrangement edge of low-pressure turbine shaft dish structure in the process or after assembly, if c is the midpoint ab, d, e, f, g are the ginseng on ab
Examination point remembers that bolt number to be measured is nc；
S22, current vortex sensor group is moved along ab, respectively at uniformly acquiring 3~5 positions within the scope of a-d, f-g, e-b
The disk relative displacement u (x of pointci,yci)=ua(xci,yci)-ul(xci,yci), wherein ua(xci,yci)、ul(xci,yci) respectively
For (xci,yci) the upper and lower disk shift value in position, the set U of each acquisition position point relative displacementcIt is pre- to constitute description bolt to be measured
The characteristic quantity of clamp force, Uc={ u (xc1,yc1),u(xc2,yc2),...,u(xcn,ycn)}；
It S23, is to judge all tools for bolts ' pretension states in low-pressure turbine shaft dish structure, successively obtaining number is 1,3,5 ...
nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point relative displacement set；
S3, judge each bolt to be measured or adjacent bolt with the presence or absence of pretightning force deficiency or phenomenon bigger than normal:
Number according to acquisition is 1,3,5 ... nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point it is opposite
The set of shift value, it is unified in a figure to draw corresponding " position-relative displacement " curve of each bolt, curve co-insides region
Identifying corresponding bolt pretightening is desired value, and it is insufficient or bigger than normal that curve deflected areas identifies corresponding bolt pretightening, and obtains
To the relative displacement deviation collection of bolt to be measured
Wherein
Δu(xci,yci) it is (xci,yci) the upper and lower disk relative displacement in position and desired value act on lower relative displacement
Difference, un(xci,yci) be desired value effect under relative displacement；ΔUcIf there are Δ u (x for 50% or more location point inci,
yci) > Δ uc(xci,yci), then can determine that bolt or adjacent bolt to be measured there are pretightning force is insufficient or the excessive phenomenon of pretightning force,
In, Δ uc(xci,yci)=Δ uc(x, y)=g (Fn1,Fn2,Fn3,x,y)；
S4, the unreasonable bolt of pretightning force and pretightning force deviation are determined:
If pq is ab vertical center line, o point is the intersection point of pq and ab, and w, v point are respectively the midpoint po, oq, move electricity along pq
Eddy current sensor group successively measures the corresponding disk relative displacement of p, w, o, v, q each point, obtains the corresponding phase of pretightning force deviation
To displacement feature set Ud={ u (xp,yp),u(xw,yw),u(xo,yo),u(xv,yv),u(xq,yq),
It and with adjacent bolt is compared with desired value acts on lower disk relative shift, to obtain the corresponding disk of pretightning force deviation
Face displacement variable
Excluding Axial stress in bolt random error influences, if it exists Δ u (xp,yp) it is greater than Δ u (xq,yq), and Δ u (xw,
yw) it is greater than Δ u (xv,yv), then it is insufficient or bigger than normal close to p point bolt pretightening, if Δ u (xq,yq) it is greater than Δ u (xp,yp), and Δ
u(xv,yv) it is greater than Δ u (xw,yw), then it is insufficient or bigger than normal close to q point bolt pretightening, and then according to deviation and pretightning force
Mapping relations Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y), it is specific to determine bolt pretightening deviation.
It tightens and is referred to using Axial stress in bolt test macro to the progress of each bolt 3 times or more described in the step S11
It tightens.
Made in the step S12 identical with low-pressure turbine reel low-pressure turbine reel test specimen refer to production and
The same material of the low-pressure turbine reel, same flange internal-and external diameter, same flange thickness, same pitch of bolts, faying face precision
1/4 low-pressure turbine reel test specimen.
The desired value is to tighten torque value needed for bolt.
D is located on ac line away from b point 5mm, f away from a point 5mm, e, is located on bc line, away from c point 3mm, g away from c in the S21
Point 3mm.
P, q point are respectively away from o point 2mm in the step S4.
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor, two current vortex sensors are coaxial, and spacing is fixed.
A kind of aero-engine low-pressure turbine reel fastening force detection test device based on current vortex sensor group, including
Base station, current vortex sensor feed arrangement and the V shape iron I being arranged successively along straight line, V shape iron II and V shape iron III, the V shape iron I
It is connect by pedestal with the base station, the V shape iron II passes sequentially through horizontal feed platform I and hoistable platform I and the base station
Connection, the V shape iron III passes sequentially through horizontal feed platform II and hoistable platform II is connect with the base station, the V shape iron I,
It is equipped with pressing plate on the V shape iron II and the V shape iron III,
The current vortex sensor feed arrangement includes sequentially connected current vortex sensor group, sensor collet, radial direction
Micrometer feed platform, angle position platform, vertical feeding platform and horizontal feed platform III, the horizontal feed platform I, it is described it is horizontal into
It is each perpendicular to the straight line to the direction of feed of platform II and the horizontal feed platform III,
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor, two current vortex sensors are coaxial, and spacing is fixed.
Embodiment 1
A kind of aero-engine low-pressure turbine reel fastening force detection method based on current vortex sensor group has as follows
Step:
S1, low-pressure turbine bolt pretightening and upper and lower disk relative displacement size, the relationship of distribution are obtained:
S11, using Axial stress in bolt test macro to each bolt carry out 3 times more than tighten, record tighten 3 times after torque and
Relationship between axial force selects end face coefficient of friction, facing coefficient of friction and the consistent bolt of axial force, and records it low
Press the position on turbine reel；
S12, production low-pressure turbine reel test specimen identical with the low-pressure turbine reel refer to production and the low pressure
The same material of turbine reel, same flange internal-and external diameter, same flange thickness, same pitch of bolts, faying face precision 1/4
The low-pressure turbine reel test specimen of (90 °) tightens the bolt on test specimen by crossing method, and with described in step S11
The corresponding bolt in position is numbered, and is denoted as 1,2 ... nmax-1、nmax；
S13, in 3~n of numbermaxThree bolts are successively chosen in the range of -2, and are individually identified as n1、n2、n3；
S14, pretightning force is applied by following four operating condition to three bolts of selection:
A) three bolt pretightenings are desired value；
B) bolt pretightening is insufficient or bolt pretightening bigger than normal, other is desired value；
C) adjacent two bolt pretightenings are insufficient or bolt pretightening bigger than normal, other is desired value；
D) two bolt pretightenings for being spaced a bolt are insufficient or bolt pretightening bigger than normal, other is desired value；
S15, n under different operating conditions is obtained by current vortex sensor group1-n2、n2-n3On the low-pressure turbine reel of intermediate region
Relative displacement u (x, y)=u of lower disk position (x, y)a(x,y)-ul(x, y), wherein ua(x,y)、ul(x, y) is respectively
The upper and lower disk shift value in the position (x, y), it is contemplated that the relative displacement under value effect is identified as un(x, y) then uses Δ u (x, y)
=u (x, y)-un(x, y) identifies the disk relative displacement variation of position (x, y) under bolt pretightening deficiency or state bigger than normal, root
The relationship between Δ u (x, y) and pretightning force size is established according to test result:
Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y),
Wherein Fn1To be applied to n1On pretightning force, Fn2To be applied to n2On pretightning force, Fn3To be applied to n3On it is pre-
Clamp force；
S16, for the n under different working conditions, the effect of different pretightning force1-n2、n2-n3The each position Δ u in intermediate region
(x, y) is tested, is analyzed, the Axial stress in bolt deviation (about 10 in conjunction with caused by facing coefficient of friction, end face coefficient of friction deviation
~20%) and low-pressure turbine reel fastening performance requires, and determines and determines bolt pretightening deficiency or threshold value bigger than normal:
Δuc(x, y)=f (Fe, x, y),
Wherein FeFor the desired value pretightning force of each bolt；
Low-pressure turbine shaft dish structure disk relative displacement up and down during S2, test set-up or after assembly:
S21, as depicted in figs. 1 and 2, be the vertical center line ab of bolt to be measured Yu adjacent bolt line, wherein a, b two
Point be respectively test set-up during or assembly after low-pressure turbine shaft dish structure flange arrangement edge, if c be the midpoint ab, d,
E, f, g are the reference point on ab, d is located on ac line away from b point 5mm, f away from a point 5mm, e, is located on bc line away from c point 3mm, g,
Away from c point 3mm, remember that bolt number to be measured is nc；
S22, current vortex sensor group is moved along ab, respectively at uniformly acquiring 3~5 positions within the scope of a-d, f-g, e-b
The disk relative displacement u (x of pointci,yci)=ua(xci,yci)-ul(xci,yci), wherein ua(xci,yci)、ul(xci,yci) respectively
For (xci,yci) the upper and lower disk shift value in position, the set U of each acquisition position point relative displacementcIt is pre- to constitute description bolt to be measured
The characteristic quantity of clamp force, Uc={ u (xc1,yc1),u(xc2,yc2),...,u(xcn,ycn)}；
It S23, is to judge all tools for bolts ' pretension states in low-pressure turbine shaft dish structure, successively obtaining number is 1,3,5 ...
nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point relative displacement set；
S3, judge each bolt to be measured or adjacent bolt with the presence or absence of pretightning force deficiency or phenomenon bigger than normal:
Number according to acquisition is 1,3,5 ... nmax- 1 or 2,4,6 ... ..nmaxBolt each acquisition position point it is opposite
The set of shift value, it is unified in a figure to draw corresponding " position-relative displacement " curve of each bolt, curve co-insides region
Identifying corresponding bolt pretightening is desired value, and it is insufficient or bigger than normal that curve deflected areas identifies corresponding bolt pretightening, and obtains
To the relative displacement deviation collection of bolt to be measured
Wherein
Δu(xci,yci) it is (xci,yci) the upper and lower disk relative displacement in position and desired value act on lower relative displacement
Difference, un(xci,yci) be desired value effect under relative displacement；ΔUcIf there are Δ u (x for 50% or more location point inci,
yci) > Δ uc(xci,yci), then can determine that bolt or adjacent bolt to be measured there are pretightning force is insufficient or the excessive phenomenon of pretightning force,
In, Δ uc(xci,yci)=Δ uc(x, y)=g (Fn1,Fn2,Fn3,x,y)；
S4, the unreasonable bolt of pretightning force and pretightning force deviation are determined:
As shown in Figure 3 and Figure 4, if pq is ab vertical center line, o point is the intersection point of pq and ab, and w, v point are respectively po, oq
Midpoint, p, q point away from o point 2mm, move current vortex sensor group along pq respectively, successively measure the corresponding disk of p, w, o, v, q each point
Relative displacement obtains the corresponding relative displacement feature set U of pretightning force deviationd={ u (xp,yp),u(xw,yw),u(xo,yo),u
(xv,yv),u(xq,yq),
It and with adjacent bolt is compared with desired value acts on lower disk relative shift, to obtain the corresponding disk of pretightning force deviation
Face displacement variable
According to Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y), then it can determine that there are the bolt of pretightning force deviation and pretightning force are inclined
Difference.
The desired value is to tighten torque value needed for bolt.
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor, two current vortex sensors are coaxial, and spacing is fixed.
Embodiment 2
As shown in Figure 5-Figure 7, a kind of aero-engine low-pressure turbine reel fastening force inspection based on current vortex sensor group
Test device is surveyed, including base station 1, current vortex sensor feed arrangement 2 and the V shape iron I 3 being arranged successively along straight line, V shape iron II 4
With V shape iron III 5, the V shape iron I 3 is connect by pedestal 6 with the base station 1, and it is flat that the V shape iron II 4 passes sequentially through horizontal feed
Platform I 7 and hoistable platform I 8 are connect with the base station 1, and the V shape iron III 5 passes sequentially through horizontal feed platform II 9 and hoistable platform
II 10 connect with the base station 1, are equipped with pressing plate 11 on the V shape iron I 3, the V shape iron II 4 and the V shape iron III 5,
The current vortex sensor feed arrangement includes sequentially connected current vortex sensor group, sensor collet 12, diameter
To micrometer feed platform 13, angle position platform 14, vertical feeding platform 15 and horizontal feed platform III 16, the horizontal feed platform I
7, the direction of feed of the horizontal feed platform II 9 and the horizontal feed platform III 16 is each perpendicular to the straight line,
The V shape iron I 3, the V shape iron II 4 and the corresponding pressing plate 11 are used to fix low-pressure turbine shaft model 17,
The V shape iron III 5 and the corresponding pressing plate 11 are used to fix low-pressure turbine disk model 18,
The current vortex sensor group includes the electricity of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Eddy current sensor 19, two current vortex sensors 19 are coaxial, and spacing is fixed.
The knob of the radial fretting feeding platform 13 is rotated, the radial fretting feeding platform 13 can drive the electricity
Eddy current sensor group radially does feed motion along low-pressure turbine reel；The configuration of radial fretting feeding platform 13 is in the angle position
On platform 14, pass through the knob of rotation angle position platform 14, thus it is possible to vary the radial fretting feeding platform 13 and horizontal direction it
Between angle, then change the movement routine of the current vortex sensor group；The angle position configuration of platform 14 is in the vertical feeding
On platform 15, by rotating the adjustable current vortex sensor group of handwheel of the vertical feeding platform 15 in vertical direction
Position；The configuration of vertical feeding platform 15 equally, it is flat to rotate the horizontal feed on the horizontal feed platform III 16
The handwheel of platform III 16, can be quick, the adjustment current vortex sensor group of big stroke along low-pressure turbine reel radial position,
To prevent when tightening bolt 20, spanner is interfered with the current vortex sensor group；The horizontal feed platform III 16 is solid
It is scheduled on the base station 1.
When adjusting the horizontal feed platform I 7 and the horizontal feed platform II 9 simultaneously, may be implemented to low-pressure turbine
The rotation and the adjustment of two freedom degrees of translation of y in the horizontal direction around vertical axes Z of shaft model 17；The lifting is adjusted simultaneously
Platform I 8 and the hoistable platform II 10 may be implemented to the translation of z and around y-axis along the vertical direction of low-pressure turbine shaft model 17
Rotation, the translation along x-axis and the rotation around x-axis directly can be operated manually realization to low-pressure turbine shaft model 17.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. a kind of aero-engine low-pressure turbine reel fastening force detection method based on current vortex sensor group, it is characterised in that
With following steps:
S1, low-pressure turbine bolt pretightening and upper and lower disk relative displacement size, the relationship of distribution are obtained:
S11, each bolt on low-pressure turbine reel is tightened, selects end face coefficient of friction, facing coefficient of friction and axial direction
The consistent bolt of power, and record its position on low-pressure turbine reel；
S12, production low-pressure turbine reel test specimen identical with the low-pressure turbine reel, by crossing method to the spiral shell on test specimen
Bolt is tightened, and bolt corresponding with position described in step S11 is numbered, and is denoted as 1,2 ... nmax-1、nmax；
S13, in 3~n of numbermaxThree bolts are successively chosen in the range of -2, and are individually identified as n1、n2、n3；
S14, pretightning force is applied by following four operating condition to three bolts of selection:
A) three bolt pretightenings are desired value；
B) bolt pretightening is insufficient or bolt pretightening bigger than normal, other is desired value；
C) adjacent two bolt pretightenings are insufficient or bolt pretightening bigger than normal, other is desired value；
D) two bolt pretightenings for being spaced a bolt are insufficient or bolt pretightening bigger than normal, other is desired value；
S15, n under different operating conditions is obtained1-n2、n2-n3The opposite position of intermediate region low-pressure turbine reel upper lower burrs face position (x, y)
Shifting value u (x, y)=ua(x,y)-ul(x, y), wherein ua(x,y)、ul(x, y) is respectively the upper and lower disk shift value in the position (x, y),
Relative displacement under desired value effect is identified as un(x, y) then uses Δ u (x, y)=u (x, y)-unIt is pre- that (x, y) identifies bolt
The disk relative displacement variation of position (x, y) under clamp force is insufficient or state bigger than normal establishes Δ u (x, y) and pre- according to test result
Relationship between clamp force size:
Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y),
Wherein Fn1To be applied to n1On pretightning force, Fn2To be applied to n2On pretightning force, Fn3To be applied to n3On pretightning force；
S16, for the n under different working conditions, the effect of different pretightning force1-n2、n2-n3The each position Δ u (x, y) in intermediate region
It tested, analyzed, Axial stress in bolt deviation and low-pressure turbine in conjunction with caused by facing coefficient of friction, end face coefficient of friction deviation
The requirement of reel fastening performance determines and determines bolt pretightening deficiency or threshold value bigger than normal:
Δuc(x, y)=f (Fe, x, y),
Wherein FeFor the desired value pretightning force of each bolt；
Low-pressure turbine shaft dish structure disk relative displacement up and down during S2, test set-up or after assembly:
S21, the vertical center line ab for doing bolt to be measured Yu adjacent bolt line, wherein a, b two o'clock are respectively test set-up process
In or assembly after low-pressure turbine shaft dish structure flange arrangement edge, if c be the midpoint ab, d, e, f, g be ab on reference point,
Remember that bolt number to be measured is nc；
S22, current vortex sensor group is moved along ab, respectively at uniformly acquiring 3~5 location points within the scope of a-d, f-g, e-b
Disk relative displacement, wherein the relative displacement of m-th of sampled point isWhereinRespectively positionUpper and lower disk shift value, the set of each acquisition position point relative displacementIt constitutes and describes tools for bolts ' pretension to be measured
The characteristic quantity of power,Wherein k is the quantity of sample point；
It S23, is to judge all tools for bolts ' pretension states in low-pressure turbine shaft dish structure, successively obtaining number is 1,3,5 ... nmax-
1 or 2,4,6.....nmaxBolt each acquisition position point relative displacement set；
S3, judge each bolt to be measured or adjacent bolt with the presence or absence of pretightning force deficiency or phenomenon bigger than normal:
Number according to acquisition is 1,3,5 ... nmax- 1 or 2,4,6.....nmaxBolt each acquisition position point with respect to position
The set of shifting value, it is unified in a figure to draw corresponding " position-relative displacement " curve of each bolt, curve co-insides region mark
Knowing corresponding bolt pretightening is desired value, and it is insufficient or bigger than normal that curve deflected areas identifies corresponding bolt pretightening, and obtains
The relative displacement deviation collection of bolt to be measured
Wherein Δ u
(xci,yci) it is position (xci,yci) upper and lower disk relative displacement and desired value act on the difference of lower relative displacement, i is to survey
Bolt is numbered at amount, un(xci,yci) be desired value effect under relative displacement；ΔUcIf there are Δs for 50% or more location point in
u(xci,yci) > Δ uc(xci,yci), then it can determine that bolt or adjacent bolt to be measured are insufficient there are pretightning force or pretightning force is excessive existing
As, wherein Δ uc(xci,yci)=Δ uc(x, y)=f (Fe,x,y)；
S4, the unreasonable bolt of pretightning force and pretightning force deviation are determined:
If pq is ab vertical center line, o point is the intersection point of pq and ab, and w, v point are respectively the midpoint po, oq, move current vortex along pq
Sensor group successively measures the corresponding disk relative displacement of p, w, o, v, q each point, obtains the corresponding opposite position of pretightning force deviation
Move feature set Ud={ u (xp,yp),u(xw,yw),u(xo,yo),u(xv,yv),u(xq,yq),
It and with adjacent bolt is compared with desired value acts on lower disk relative shift, to obtain the corresponding disk position of pretightning force deviation
Move variable quantity
Excluding Axial stress in bolt random error influences, if it exists Δ u (xp,yp) it is greater than Δ u (xq,yq), and Δ u (xw,yw) big
In Δ u (xv,yv), then it is insufficient or bigger than normal close to p point bolt pretightening, if Δ u (xq,yq) it is greater than Δ u (xp,yp), and Δ u (xv,
yv) it is greater than Δ u (xw,yw), then it is insufficient or bigger than normal close to q point bolt pretightening, and then closed according to the mapping of deviation and pretightning force
It is Δ u (x, y)=g (Fn1,Fn2,Fn3, x, y), it is specific to determine bolt pretightening deviation.
2. detection method according to claim 1, it is characterised in that: tightened described in the step S11 and refer to applying
Axial stress in bolt test macro tightens the progress of each bolt 3 times or more.
3. detection method according to claim 1, it is characterised in that: production and the low-pressure turbine in the step S12
The identical low-pressure turbine reel test specimen of reel refers to same as the low-pressure turbine reel material of production, inside and outside same flange
Diameter, same flange thickness, same pitch of bolts, faying face precision 1/4 low-pressure turbine reel test specimen.
4. detection method according to claim 1, it is characterised in that: the desired value is to tighten torque value needed for bolt.
5. detection method according to claim 1, it is characterised in that: d is away from a point 5mm, e away from b point 5mm, f in the S21
In be located on bc line on ac line, away from c point 3mm, g, away from c point 3mm.
6. detection method according to claim 1, it is characterised in that: p, q point are respectively away from o point 2mm in the step S4.
7. detection method according to claim 1, it is characterised in that: the current vortex sensor group includes two and sets relatively
The current vortex sensor of relative displacement set, detection low-pressure turbine reel, two current vortex sensors are coaxial, and
Away from fixation.
8. a kind of aero-engine low-pressure turbine reel fastening force based on current vortex sensor group detects test device, feature
It is: including base station, current vortex sensor feed arrangement and the V shape iron I being arranged successively along straight line, V shape iron II and V shape iron III,
The V shape iron I is connect by pedestal with the base station, and the V shape iron II passes sequentially through horizontal feed platform I and hoistable platform I
It is connect with the base station, the V shape iron III passes sequentially through horizontal feed platform II and hoistable platform II is connect with the base station, institute
It states and is equipped with pressing plate on V shape iron I, the V shape iron II and the V shape iron III,
The current vortex sensor feed arrangement includes sequentially connected current vortex sensor group, sensor collet, radial fretting
Feeding platform, angle position platform, vertical feeding platform and horizontal feed platform III, the horizontal feed platform I, the horizontal feed are flat
The direction of feed of platform II and the horizontal feed platform III is each perpendicular to the straight line,
The current vortex sensor group includes the current vortex of two relative displacements be oppositely arranged, detection low-pressure turbine reel
Sensor, two current vortex sensors are coaxial, and spacing is fixed.
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| CN106768584B (en) * | 2016-11-22 | 2019-04-16 | 大连理工大学 | A kind of aero-engine low-pressure turbine reel fastening force detection method and device based on line laser displacement sensor group |
| CN109085246B (en) * | 2018-07-24 | 2022-01-07 | 南昌航空大学 | Rapid ultrasonic detection equipment for copper-steel bimetal nine-hole rotor diffusion welding |
| CN110501108B (en) * | 2019-09-03 | 2020-07-14 | 大连理工大学 | Bolt pretightening force identification method based on independent component analysis and support vector machine |
| CN112652223B (en) * | 2020-12-25 | 2021-09-14 | 四川交通职业技术学院 | Demonstration teaching aid for stress and deformation relation of engine connecting component |
| CN116068045B (en) * | 2023-04-06 | 2023-06-02 | 中国石油大学(华东) | Composite structure defect identification method for inhibiting lift-off effect interference |
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