CN112684015B - Nondestructive testing system and method for applying bilinear array transducer to turbine disk - Google Patents

Nondestructive testing system and method for applying bilinear array transducer to turbine disk Download PDF

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CN112684015B
CN112684015B CN202011510510.5A CN202011510510A CN112684015B CN 112684015 B CN112684015 B CN 112684015B CN 202011510510 A CN202011510510 A CN 202011510510A CN 112684015 B CN112684015 B CN 112684015B
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sound velocity
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CN112684015A (en
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周正干
滕利臣
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Beihang University
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Abstract

The invention discloses a nondestructive testing system and a nondestructive testing method for a turbine disk by applying a bilinear array transducer, wherein the testing system uses a computer stored with a Space-Defect method to process an image formed by ultrasonic echo data acquired by the bilinear array transducer so as to obtain a Defect-imaging point on a tested object. The Space-Defect method is adopted to solve the problem that the conventional phased array is not easy to solve the characteristic of the small Defect smaller than the half wavelength, can automatically identify with high precision and image the test piece with a complex structure with high precision, and provides a new way for detecting the diffusion welding area type Defect of the aviation high-temperature alloy disc.

Description

Nondestructive testing system and method for applying bilinear array transducer to turbine disk
Technical Field
The invention relates to the technical field of nondestructive testing, in particular to a nondestructive testing device capable of carrying out nondestructive testing on a turbine disc with a narrow gap.
Background
A transducer is an energy conversion device that requires many parameters for performance description and evaluation. The characteristic parameters of the transducer include resonance frequency, frequency bandwidth, electromechanical coupling coefficient, electro-acoustic efficiency, mechanical quality factor, impedance characteristic, frequency characteristic, directivity, transmission and reception sensitivity, and the like. The performance parameters of transducers for different applications are different, for example, for transmitting type transducers, the transducers are required to have large output power and high energy conversion efficiency; on the other hand, the receiving transducer is required to have a wide frequency band and high sensitivity and resolution. Therefore, in the specific design process of the transducer, the relevant parameters of the transducer must be reasonably designed according to the object to be detected (or the sample to be detected).
"mechanical engineering journal of phased array ultrasound post-processing imaging technology research, application and development", author, Zhongzheng gan, lie ocean, Wen Bin, vol 52, 6, 3/2016. The full-matrix data acquisition system composed of a phased array ultrasonic transducer, an ultrasonic excitation receiving board card and a computer terminal is introduced, and is shown in fig. 1.
An aviation superalloy disk, which is one of the most critical components of a high-performance engine, is shown in fig. 2, in which a narrow gap exists between two adjacent blades. The material and the manufacturing technology of the composite material are always paid special attention to the aeronautical engineering world at home and abroad. As the most critical hot end component in the aircraft engine, the turbine disc bears the superposition of high temperature and high stress in the working process, the working condition is extremely harsh, and higher requirements are put forward for the turbine disc along with the improvement of the thrust-weight ratio/power-weight ratio of the aircraft engine.
Nondestructive testing is a general term for all technical means for detecting whether a defect or non-uniformity exists in a tested object by using characteristics of sound, light, magnetism, electricity and the like without damaging or influencing the use performance of the tested object, giving information such as the size, position, property, quantity and the like of the defect, and further judging the technical state (such as qualification or qualification, service life and the like) of the tested object. The german fraunhofer nondestructive testing institute develops a set of thick-wall cast austenitic stainless steel phased array ultrasonic testing system based on Sampling phased array technology (SPA), and the essence of the SPA technology is TFM imaging based on full matrix data.
The aviation superalloy disk is mainly used for fixing and mounting engine blades to transmit power. At present, the main body turbine disk and the integral blade ring are mainly connected through a diffusion welding mode. When the aviation high-temperature alloy disc works under extreme conditions of high rotating speed, high load, high temperature, high pressure and the like for a long time, a welding seam area is a stress concentration area, and when defects occur, the diffusion welding interface has area defects such as micro-close clearance, micro-distribution and the like, and the defects become important potential safety hazards influencing the performance of an aero-engine. The detection scheme based on the conventional single probe has the defects of low detection resolution, small sound wave energy, low imaging resolution and the like, so that the establishment of the detection method suitable for the diffusion welding area type defects of the high-temperature alloy disc has important practical significance.
Disclosure of Invention
One of the objectives of the present invention is to design a non-destructive testing system for turbine disks using a dual linear array transducer. The system consists of a bilinear array transducer, a deconcentrator, an ultrasonic excitation receiving board card and a computer, wherein an area type Defect detection execution program based on the bilinear array transducer full-focusing imaging is stored in a hard disk of the computer, namely a Space-Defect method. The Space-Defect method of the invention comprises an upper half part-Defect position acoustic wave model, a middle part-Defect position acoustic wave model and a lower half part-Defect position acoustic wave model.
The upper half part-defect position acoustic wave model means that when the defect is positioned at the upper half part of the diffusion welding interface and is equivalent to an angle that an incident angle alpha is smaller than a reflection angle beta, the working parameter of an incident wave is set to be a longitudinal sound velocity CLongitudinal directionThe working parameter of the reflected wave is set as the transverse wave sound velocity CHorizontal barTo carry out miningAnd collecting to obtain the defect-imaging point in the image.
The mid-section-defect-location acoustic model refers to the transverse acoustic velocity C when the defect is located in the mid-section of the diffusion weld interface at an angle corresponding to an angle where the angle of incidence α is equal to the angle of reflection βHorizontal barThe longitudinal wave sound velocity C can also beLongitudinal direction(ii) a Due to the longitudinal wave sound velocity CLongitudinal directionThe reflection angle of is less than the transverse wave sound velocity CHorizontal barThe larger the angle of incidence angle alpha, the higher the longitudinal wave sound velocity CLongitudinal directionThe less reflected energy; therefore, the working parameter of the incident wave is selected to be the transverse wave sound velocity CHorizontal barAnd the total reflection of the incident wave enables finding the defect-imaging point in the image.
The lower half part-defect position acoustic wave model means that when the defect is positioned on the lower half part of the diffusion welding interface and is equivalent to an angle with an incidence angle alpha larger than a reflection angle beta, according to Snell's law, at the moment, the incident wave should select a longitudinal sonic velocity CLongitudinal directionAs an operating parameter, the transverse wave sound velocity C should be selected as the reflected waveHorizontal barAnd as a working parameter, finding out a defect-imaging point in the image is realized.
The invention also provides a nondestructive testing method for applying the bilinear array transducer to the turbine disk, the nondestructive testing method applies spatial position to scale the positions of the probes which are arranged in pairs, imaging point information is obtained by means of image area division, and finally a sound wave model is adopted to obtain defect-imaging points. The Space-Defect method is adopted to solve the problem that the conventional phased array is not easy to solve the characteristic of the small Defect smaller than the half wavelength, can automatically identify with high precision and image the test piece with a complex structure with high precision, and provides a new way for detecting the diffusion welding area type Defect of the aviation high-temperature alloy disc.
The invention discloses a nondestructive testing method for a turbine disk by applying a bilinear array transducer, which comprises the following steps:
step one, setting working parameters of a bilinear array transducer;
step 11, calibrating the position of the probe;
modeling according to three-dimensional software to obtain a tested object model, setting the number of transmitting end probes and receiving end probes on the tested object model, and numbering each transmitting end probe and each receiving end probe with unique digital identities;
the computer storing the Space-Defect method maps the coordinate system O-XYZ into MATLAB software.
All transmit-side probes arranged form a transmit-side probe set, denoted
Figure GDA0003257619350000031
And the above-mentioned
Figure GDA0003257619350000032
Correspondingly arranged receiving end probes form a receiving end-probe set which is marked as
Figure GDA0003257619350000033
Step 12, setting sampling frequencies of a transmitting end probe and a receiving end probe;
sampling frequency fLoadingSet at 20 Hz-20 kHz.
Step 13, setting the transverse wave sound velocity C of the measured objectHorizontal barAnd longitudinal wave speed CLongitudinal direction。
Transverse wave sound velocity CHorizontal barIs 340m/s to 15240 m/s.
Longitudinal acoustic velocity CLongitudinal directionIs 340m/s to 15240 m/s.
Step two, setting an imaging area in a Space-Defect method;
after receiving image information represented by ultrasonic echo data acquired by a linear array transducer, a computer storing a Space-Defect method respectively sets the X-axis image length LxY-axis image length LyZ-axis image length LzPixel pitch d of X-axis imagexPixel pitch d of Y-axis imageyPixel pitch d of Z-axis imagez。
The information of any one imaging point in different planes is as follows: any one of the imaged point signals in the XY plane of the coordinate system O-XYZInformation is represented as
Figure GDA0003257619350000034
In an XZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure GDA0003257619350000035
In a YZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure GDA0003257619350000041
In the invention, after the working parameters of the bilinear array transducer are set, the first transmitting end probe
Figure GDA0003257619350000042
Excitation and first receiving end probe
Figure GDA0003257619350000043
Receiving, one-time collecting ultrasonic echo data to form an image information, and recording as a first group of images
Figure GDA0003257619350000044
For processing the first set of images in a computer storing the Space-Defect method
Figure GDA0003257619350000045
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the first set of images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA0003257619350000046
Can be expressed as
Figure GDA0003257619350000047
The subscript h is the first set of images
Figure GDA0003257619350000048
And h is 1,2,3 ….
In the invention, after the working parameters of the bilinear array transducer are set, the probe at the second transmitting end
Figure GDA0003257619350000049
Excitation and second receiving end probe
Figure GDA00032576193500000410
Receiving, one-time collecting ultrasonic echo data to form one image information, and recording as a second group of images
Figure GDA00032576193500000411
For processing the second set of images in the computer storing the Space-Defect method
Figure GDA00032576193500000412
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the second set of images is taken in the XZ plane of the coordinate system O-XYZ
Figure GDA00032576193500000413
Can be expressed as
Figure GDA00032576193500000414
The lower corner mark j is the second group of images
Figure GDA00032576193500000415
And j is 1,2,3 ….
In the invention, after the working parameters of the bilinear array transducer are set, the a-th transmitting end probe
Figure GDA00032576193500000416
Excitation and a-th receiving end probe
Figure GDA00032576193500000417
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as a group a image
Figure GDA00032576193500000418
The computer with Space-Defect method stored is used for processing the a-group image
Figure GDA00032576193500000419
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group a images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA00032576193500000420
Can be expressed as
Figure GDA00032576193500000421
The lower corner mark k is the a-th group image
Figure GDA00032576193500000422
And k is 1,2,3 ….
In the invention, after the working parameters of the bilinear array transducer are set, the A-th transmitting end probe
Figure GDA00032576193500000423
Excitation and A receiving end probe
Figure GDA00032576193500000424
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as group A image
Figure GDA00032576193500000425
For processing in a computer storing Space-Defect method, the A group image
Figure GDA00032576193500000426
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group A images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA00032576193500000427
Can be expressed as
Figure GDA00032576193500000428
The lower corner mark l is the A-th group image
Figure GDA00032576193500000429
And the identification number of the imaging point is 1,2,3 ….
The image information obtained by the processing of the step two comprises a first group of images
Figure GDA0003257619350000051
Second group of images
Figure GDA0003257619350000052
Group a images
Figure GDA0003257619350000053
Group A images
Figure GDA0003257619350000054
The first group of images
Figure GDA0003257619350000055
Second group of images
Figure GDA0003257619350000056
Group a images
Figure GDA0003257619350000057
Group A images
Figure GDA0003257619350000058
Form a set of images to be processed, denoted as IM, and
Figure GDA0003257619350000059
acquiring a defect-imaging point by adopting an acoustic wave model;
according to the sound wave model discrimination method, the image set obtained in the step two is subjected to
Figure GDA00032576193500000510
And defect detection is carried out, and a defect-imaging point can be obtained.
Upper half-defect position acoustic model;
in the invention, when the defect is positioned at the upper half part of the diffusion welding interface and corresponds to an angle that the incidence angle alpha is smaller than the reflection angle beta, the working parameter of the incident wave is set to be the longitudinal wave sound velocity CLongitudinal directionThe working parameter of the reflected wave is set as the transverse wave sound velocity CHorizontal barAcquisition is performed to obtain defect-imaging points in the image.
Middle part-defect position acoustic model;
in the present invention, when the defect is located in the middle portion of the diffusion welding interface, corresponding to an angle where the incident angle α is equal to the reflection angle β, the incident acoustic wave may be a transverse acoustic velocity CHorizontal barThe longitudinal wave sound velocity C can also beLongitudinal direction(ii) a Due to the longitudinal wave sound velocity CLongitudinal directionThe reflection angle of is less than the transverse wave sound velocity CHorizontal barThe larger the angle of incidence angle alpha, the higher the longitudinal wave sound velocity CLongitudinal directionThe less reflected energy; therefore, the working parameter of the incident wave is selected to be the transverse wave sound velocity CHorizontal barAnd the total reflection of the incident wave enables finding the defect-imaging point in the image.
The lower half-defect position acoustic model;
in the invention, when the defect is positioned at the lower half part of the diffusion welding interface and is equivalent to the angle that the incident angle alpha is larger than the reflection angle beta, according to Snell law, the incident wave should select the longitudinal wave sound velocity CLongitudinal directionAs an operating parameter, the transverse wave sound velocity C should be selected as the reflected waveHorizontal barAnd as a working parameter, finding out a defect-imaging point in the image is realized.
The Space-Defect method is adopted to solve the problem that the conventional phased array is not easy to solve the characteristic of the small Defect smaller than the half wavelength, can automatically identify with high precision and image the test piece with a complex structure with high precision, and provides a new way for detecting the diffusion welding area type Defect of the aviation high-temperature alloy disc.
Drawings
Fig. 1 is a system diagram of a conventional phased array ultrasonic transducer and a computer terminal for full matrix data information acquisition.
Fig. 2 is a photograph of a subject.
FIG. 2A is a schematic illustration of a probe layout of a blade weld after three-dimensional software modeling.
FIG. 3 is a block diagram of a system for non-destructive testing of a turbine disk using a bilinear array transducer in accordance with the present invention.
FIG. 3A is a block diagram of a three-axis table constructed in three-dimensional software according to the present invention.
Fig. 4A is a probe structure diagram of the paired dual linear array transducer of the present invention.
Figure 4B is a probe block diagram of another paired dual linear array transducer arrangement of the present invention.
Fig. 5 is a schematic diagram of image area division according to the present invention.
FIG. 6 is a diagram of point acquisition for an image by using Space-Defect method according to the present invention.
Fig. 7 is a structural diagram of the present invention using the upper half-defect position acoustic wave model for inspection.
Fig. 8 is a structural view of the present invention employing a mid-portion-defect-position acoustic wave model for inspection.
Fig. 9 is a structural diagram of the present invention using the lower half-defect position acoustic wave model for detection.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
In the invention, the bilinear array transducer comprises an array ultrasonic pocket board card and an ultrasonic probe. Because the number of blades of the aviation high-temperature alloy plate is large (as shown in fig. 2), one or more ultrasonic probes need to be arranged on each blade, and the number of interfaces of each array ultrasonic pocket board card is fixed, a deconcentrator is connected between the array ultrasonic pocket board card and the ultrasonic probes, and an ultrasonic excitation receiving board card is connected between the array ultrasonic pocket board card and a computer, as shown in fig. 3. The ultrasonic probe is a one-dimensional linear probe with a plurality of array element wafers. Referring to fig. 2, if a pair of probes is disposed at the diffusion welding position of the blade (i.e. a transmitting end probe is disposed above the blade and a receiving end probe is disposed below the blade), and a pair of probes is also disposed at the tip of the blade, this is called that a plurality of probes are disposed on the same blade.
In the invention, an area-type Defect detection execution program based on the bilinear array transducer full-focus imaging is called a Space-Defect method. The Space-Defect method is stored in a hard disk of a computer. The computer stored with the Space-Defect method is used for receiving ultrasonic echo data acquired by the bilinear array transducer.
Referring to fig. 3, the system for nondestructive testing by applying the bilinear array transducer to the turbine disk, which is designed by the invention, is composed of the bilinear array transducer, a splitter, an ultrasonic excitation receiving board card and a computer, wherein an area-type Defect detection execution program based on the bilinear array transducer full-focus imaging, namely a Space-Defect method, is stored in a hard disk of the computer. And the computer is connected with the ultrasonic excitation receiving board card through an R232 serial port to realize data transmission. Fig. 3 is different from fig. 1 in that a bilinear array transducer is used for detecting a sample to be tested, and a computer terminal processes received ultrasonic echo data in a different manner by applying a Space-Defect method. The bilinear array transducer manufacturer is electronic science and technology corporation of Dupule, Guangzhou, and the product performance parameters are as follows: the sampling frequency is 100MHz, the pulse voltage is 50V-100V, the pulse mode is negative square wave, the pulse width is 30ns/2.5 ns-1000 ns/2.5ns, and the sound velocity is 340 m/s-15240 m/s.
In fig. 1, T denotes transmitting end information, R denotes receiving end information, i denotes an identification number of a transmitting end array element, j denotes an identification number of a receiving end array element, and s denotesi,j(t) represents the information received by the ith array element exciting the jth array element, and si,j(t) is a two-dimensional array function.
Arrangement of dual linear array transducers
In order to realize the symmetrical detection of the tested sample (the superalloy turbine disk), the transducers of the double linear arrays which are arranged one after another are symmetrically arranged in the thickness direction of the superalloy turbine disk, as shown in fig. 4A and 4B. The thickness direction of the high-temperature alloy turbine disc refers to the Z axis of a coordinate system O-XYZ in a Space-Defect method.
In the present invention, the layout of the probes in a dual linear array transducer is shown in fig. 4A and 4B, the probes being arranged in pairs for transmit/receive ends. As shown in fig. 4A, when the transmitting end probe is disposed above the object to be measured in the thickness direction, the receiving end probe is disposed below the object to be measured in the thickness direction. As shown in fig. 4B, if the receiving probe is disposed on one side of the object to be measured, the transmitting probe is disposed on the other side of the object to be measured. When the probes are arranged, each pair of probes is numbered. Any one transmitting end probe mark
Figure GDA0003257619350000072
Any one of the receiving end probes is marked as
Figure GDA0003257619350000071
The lower corner mark a is the identification number of the probes arranged in pairs.
In the invention, a measured object (an aviation high-temperature alloy disk) is modeled by using three-dimensional drawing software (solidworks, UG and the like) to obtain a measured object model. And guiding the tested object model into simulation software (MATLAB) to carry out position calibration which is consistent with the object (aviation high-temperature alloy disk) and under a coordinate system O-XYZ.
In the invention, in order to realize the position calibration of the defect of the measured object (aeronautical high-temperature alloy disk), the measured object is fixed on an object stage of a three-axis translation stage (as shown in figure 3A). The coordinate system of the three-axis translation stage is marked as O-XYZ, the X axis is a transverse axis, the Y axis is a longitudinal axis, the Z axis is a vertical axis, and the vertical axis marks the thickness of the measured object arranged on the objective table. In the coordinate system O-XYZ, each probe arranged on the measured object has a well-defined position (X, Y, Z), X being a position value on the X-axis, Y being a position value on the Y-axis, and Z being a position value on the Z-axis.
The nondestructive testing method for the turbine disc by applying the Space-Defect method comprises the following steps:
step one, setting working parameters of a bilinear array transducer;
step 11, calibrating the position of the probe;
modeling according to three-dimensional software to obtain a tested object model, setting the number of transmitting end probes and receiving end probes on the tested object model, and numbering each transmitting end probe and each receiving end probe with unique digital identities;
such as the profiled structure shown in fig. 2A, with the upper layer schematically indicated as E1,E2,E3,E4Can be 4 probes at the transmitting end, and O arranged at the lower layer corresponding to the probes1,O2,O3,O4There are 4 probes at the receiving end.
All transmit-side probes arranged form a transmit-side probe set, denoted
Figure GDA0003257619350000081
And the above-mentioned
Figure GDA0003257619350000082
Correspondingly arranged receiving end probes form a receiving end-probe set which is marked as
Figure GDA0003257619350000083
Figure GDA0003257619350000084
Showing a first transmitting end probe; the above-mentioned
Figure GDA0003257619350000085
The position in the coordinate system O-XYZ is recorded as
Figure GDA0003257619350000086
Representing a first receiving end probe; the above-mentioned
Figure GDA0003257619350000087
The position in the coordinate system O-XYZ is recorded as
Figure GDA0003257619350000088
Figure GDA0003257619350000089
Showing a second transmitting end probe; the above-mentioned
Figure GDA00032576193500000810
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000811
Representing a second receiving end probe; the above-mentioned
Figure GDA00032576193500000812
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000813
Figure GDA00032576193500000814
Denotes any one of the transmitting-end probes, said
Figure GDA00032576193500000815
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000816
Denotes any one of the receiving-end probes, said
Figure GDA00032576193500000817
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000818
The lower subscript a indicates the identification numbers of the probes arranged in pairs.
Figure GDA00032576193500000819
Represents the last transmitting end probe, said
Figure GDA00032576193500000820
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000821
Represents the last receiving probe, said
Figure GDA00032576193500000822
The position in the coordinate system O-XYZ is recorded as
Figure GDA00032576193500000823
The subscript a denotes the total number of pairs of probes, a e a, set in pairs.
In the invention, a computer storing the Space-Defect method maps a coordinate system O-XYZ into MATLAB software. Namely, the object coordinate system is converted into software and adopts the same coordinate system with the coordinate system in MATLAB software, thus not only ensuring the sampling precision of the bilinear array transducer, but also improving the accuracy of image information segmentation.
Step 12, setting sampling frequencies of a transmitting end probe and a receiving end probe;
in the present invention, the sampling frequency fLoadingSet at 20 Hz-20 kHz.
Step 13, setting the transverse wave sound velocity C of the measured objectHorizontal barAnd longitudinal wave speed CLongitudinal direction。
In the present invention, the transverse wave sound velocity CHorizontal barThe sound velocity is 340 m/s-15240 m/s; longitudinal acoustic velocity CLongitudinal directionThe sound velocity is 340 m/s-15240 m/s. Transverse wave sound velocity CHorizontal barAnd longitudinal wave speed CLongitudinal directionThe angle between the incident sound ray and the reflected sound ray in fig. 7, 8 and 9 is related to the material of the aviation high-temperature alloy disk of the measured object.
Step two, setting an imaging area in a Space-Defect method;
referring to fig. 5 and 6, a computer storing the Space-Defect method is receivingSetting the length L of an X-axis image after reaching the image information represented by the ultrasonic echo data acquired by the linear array transducerxY-axis image length LyZ-axis image length LzPixel pitch d of X-axis imagexPixel pitch d of Y-axis imageyPixel pitch d of Z-axis imagez。
In the invention, the information of any one imaging point in different planes is as follows: in the XY plane of the coordinate system O-XYZ, any imaging point information is expressed as
Figure GDA0003257619350000091
In an XZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure GDA0003257619350000092
In a YZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure GDA0003257619350000093
In the invention, after the working parameters of the bilinear array transducer are set, the first transmitting end probe
Figure GDA0003257619350000094
Excitation and first receiving end probe
Figure GDA0003257619350000095
Receiving, one-time collecting ultrasonic echo data to form an image information, and recording as a first group of images
Figure GDA0003257619350000096
For processing the first set of images in a computer storing the Space-Defect method
Figure GDA0003257619350000097
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the first set of images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA0003257619350000098
Can be expressed as
Figure GDA00032576193500000915
The subscript h is the first set of images
Figure GDA0003257619350000099
And h is 1,2,3 ….
In the invention, after the working parameters of the bilinear array transducer are set, the probe at the second transmitting end
Figure GDA00032576193500000910
Excitation and second receiving end probe
Figure GDA00032576193500000911
Receiving, one-time collecting ultrasonic echo data to form one image information, and recording as a second group of images
Figure GDA00032576193500000912
For processing the second set of images in the computer storing the Space-Defect method
Figure GDA00032576193500000913
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the second set of images is taken in the XZ plane of the coordinate system O-XYZ
Figure GDA00032576193500000914
Can be expressed as
Figure GDA0003257619350000101
The lower corner mark j is the second group of images
Figure GDA0003257619350000102
And j is 1,2,3 ….
In the present invention, a bilinear array is setAfter the working parameters of the column transducer, the a-th transmitting end probe
Figure GDA0003257619350000103
Excitation and a-th receiving end probe
Figure GDA0003257619350000104
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as a group a image
Figure GDA0003257619350000105
The computer with Space-Defect method stored is used for processing the a-group image
Figure GDA0003257619350000106
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group a images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA0003257619350000107
Can be expressed as
Figure GDA0003257619350000108
The lower corner mark k is the a-th group image
Figure GDA0003257619350000109
And k is 1,2,3 ….
In the invention, after the working parameters of the bilinear array transducer are set, the A-th transmitting end probe
Figure GDA00032576193500001010
Excitation and A receiving end probe
Figure GDA00032576193500001011
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as group A image
Figure GDA00032576193500001012
For processing in a computer storing Space-Defect method, the A group image
Figure GDA00032576193500001013
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group A images are taken in the XZ plane of the coordinate system O-XYZ
Figure GDA00032576193500001014
Can be expressed as
Figure GDA00032576193500001015
The lower corner mark l is the A-th group image
Figure GDA00032576193500001016
And the identification number of the imaging point is 1,2,3 ….
Generally, an image is composed of a plurality of imaging points, and in the present invention, the number of imaging points is counted from the top left of an image and ends at the bottom right thereof, as shown in fig. 6.
The image information obtained by the processing of the step two comprises a first group of images
Figure GDA00032576193500001017
Second group of images
Figure GDA00032576193500001018
Group a images
Figure GDA00032576193500001019
Group A images
Figure GDA00032576193500001020
The first group of images
Figure GDA00032576193500001021
Second group of images
Figure GDA00032576193500001022
Group a images
Figure GDA00032576193500001023
Group A images
Figure GDA00032576193500001024
Form a set of images to be processed, denoted as IM, and
Figure GDA00032576193500001025
acquiring a defect-imaging point by adopting an acoustic wave model;
referring to fig. 7, 8 and 9, in the present invention, the image set obtained in step two is determined according to the acoustic wave model discrimination method
Figure GDA00032576193500001026
And defect detection is carried out, and a defect-imaging point can be obtained.
In fig. 7, 8, and 9, the waveform of the incident sound ray is referred to as an incident wave, and the waveform of the reflected sound ray is referred to as a reflected wave. The combination point of the incident sound ray and the reflected sound ray is positioned on the measured object and is marked as an area type defect point, the over-area type defect point is marked as a vertical line, the included angle formed by the vertical line and the incident sound ray is marked as an incident angle and is marked as alpha, and the included angle formed by the vertical line and the reflected sound ray is marked as a reflected angle and is marked as beta.
Upper half-defect position acoustic model;
in the invention, when the defect is positioned at the upper half part of the diffusion welding interface and corresponds to an angle that the incidence angle alpha is smaller than the reflection angle beta, the working parameter of the incident wave is set to be the longitudinal wave sound velocity CLongitudinal directionThe working parameter of the reflected wave is set as the transverse wave sound velocity CHorizontal barAcquisition is performed to obtain defect-imaging points in the image.
Middle part-defect position acoustic model;
in the present invention, when the defect is located in the middle portion of the diffusion welding interface, corresponding to an angle where the incident angle α is equal to the reflection angle β, the incident acoustic wave may be a transverse acoustic velocity CHorizontal barThe longitudinal wave sound velocity C can also beLongitudinal direction(ii) a ByAt longitudinal wave speed CLongitudinal directionThe reflection angle of is less than the transverse wave sound velocity CHorizontal barThe larger the angle of incidence angle alpha, the higher the longitudinal wave sound velocity CLongitudinal directionThe less reflected energy; therefore, the working parameter of the incident wave is selected to be the transverse wave sound velocity CHorizontal barAnd the total reflection of the incident wave enables finding the defect-imaging point in the image.
The lower half-defect position acoustic model;
in the invention, when the defect is positioned at the lower half part of the diffusion welding interface and is equivalent to the angle that the incident angle alpha is larger than the reflection angle beta, according to Snell law, the incident wave should select the longitudinal wave sound velocity CLongitudinal directionAs an operating parameter, the transverse wave sound velocity C should be selected as the reflected waveHorizontal barAnd as a working parameter, finding out a defect-imaging point in the image is realized.
Referring to the image shown in fig. 6, through the processing of step three, the defect-image point in each image can be detected.

Claims (5)

1. A non-destructive inspection system for a turbine disk using a dual linear array transducer, comprising: the system is composed of a bilinear array transducer, a deconcentrator, an ultrasonic excitation receiving board card and a computer, wherein an area-type Defect detection execution program based on the bilinear array transducer full-focus imaging is stored in a hard disk of the computer, namely a Space-Defect method; the computer is connected with the ultrasonic excitation receiving board card through an R232 serial port to realize data transmission; the bilinear array transducer comprises an array ultrasonic pocket board card and an ultrasonic probe;
performance parameters of the bilinear array transducer: the sampling frequency is 100MHz, the pulse voltage is 50V-100V, the pulse mode is negative square wave, the pulse width is 30ns/2.5 ns-1000 ns/2.5ns, and the sound velocity is 340 m/s-15240 m/s;
the Space-Defect method comprises an upper half part-Defect position acoustic wave model, a middle part-Defect position acoustic wave model and a lower half part-Defect position acoustic wave model;
the combination point of the incident sound ray and the reflected sound ray is positioned on a measured object and is marked as an area type defect point, the over-area type defect point is marked as a vertical line, the included angle formed by the vertical line and the incident sound ray is marked as an incident angle and is marked as alpha, and the included angle formed by the vertical line and the reflected sound ray is marked as a reflected angle and is marked as beta;
the upper half part-defect position acoustic wave model means that when the defect is positioned at the upper half part of the diffusion welding interface and is equivalent to an angle that an incident angle alpha is smaller than a reflection angle beta, the working parameter of an incident wave is set to be a longitudinal sound velocity CLongitudinal directionThe working parameter of the reflected wave is set as the transverse wave sound velocity CHorizontal barAcquiring to obtain a defect-imaging point in the image;
the mid-section-defect-location acoustic model refers to the transverse acoustic velocity C when the defect is located in the mid-section of the diffusion weld interface at an angle corresponding to an angle where the angle of incidence α is equal to the angle of reflection βHorizontal barThe longitudinal wave sound velocity C can also beLongitudinal direction(ii) a Due to the longitudinal wave sound velocity CLongitudinal directionThe reflection angle of is less than the transverse wave sound velocity CHorizontal barThe larger the angle of incidence angle alpha, the higher the longitudinal wave sound velocity CLongitudinal directionThe less reflected energy; therefore, the working parameter of the incident wave is selected to be the transverse wave sound velocity CHorizontal barAnd the defects in the image, namely imaging points, are found out by the total reflection of the incident wave;
the lower half part-defect position acoustic wave model means that when the defect is positioned on the lower half part of the diffusion welding interface and is equivalent to an angle with an incidence angle alpha larger than a reflection angle beta, according to Snell's law, at the moment, the incident wave should select a longitudinal sonic velocity CLongitudinal directionAs an operating parameter, the transverse wave sound velocity C should be selected as the reflected waveHorizontal barAnd as a working parameter, finding out a defect-imaging point in the image is realized.
2. A method for non-destructive testing of a turbine disk using a dual linear array transducer, comprising the steps of:
step one, setting working parameters of a bilinear array transducer;
step 11, calibrating the position of the probe;
modeling according to three-dimensional software to obtain a tested object model, setting the number of transmitting end probes and receiving end probes on the tested object model, and numbering each transmitting end probe and each receiving end probe with unique digital identities;
mapping a coordinate system O-XYZ into MATLAB software in a computer in which a Space-Defect method is stored;
all transmit-side probes arranged form a transmit-side probe set, denoted
Figure FDA0003257619340000021
And the above-mentioned
Figure FDA0003257619340000022
Correspondingly arranged receiving end probes form a receiving end-probe set which is marked as
Figure FDA0003257619340000023
Figure FDA0003257619340000024
Showing a first transmitting end probe; the above-mentioned
Figure FDA0003257619340000025
The position in the coordinate system O-XYZ is recorded as
Figure FDA0003257619340000026
Figure FDA0003257619340000027
Representing a first receiving end probe; the above-mentioned
Figure FDA0003257619340000028
The position in the coordinate system O-XYZ is recorded as
Figure FDA0003257619340000029
Figure FDA00032576193400000210
Showing a second transmitting end probe; the above-mentioned
Figure FDA00032576193400000211
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000212
Figure FDA00032576193400000213
Representing a second receiving end probe; the above-mentioned
Figure FDA00032576193400000214
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000215
Figure FDA00032576193400000216
Denotes any one of the transmitting-end probes, said
Figure FDA00032576193400000217
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000218
Figure FDA00032576193400000219
Denotes any one of the receiving-end probes, said
Figure FDA00032576193400000220
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000221
The lower subscript a indicates the identification numbers of the probes arranged in pairs;
Figure FDA00032576193400000222
represents the last transmitting end probe, said
Figure FDA00032576193400000223
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000224
Figure FDA00032576193400000225
Represents the last receiving probe, said
Figure FDA00032576193400000226
The position in the coordinate system O-XYZ is recorded as
Figure FDA00032576193400000227
The lower subscript A represents the total number of pairs of probes, a ∈ A;
step 12, setting sampling frequencies of a transmitting end probe and a receiving end probe;
sampling frequency fLoadingSetting the frequency to be 20 Hz-20 kHz;
step 13, setting the transverse wave sound velocity C of the measured objectHorizontal barAnd longitudinal wave speed CLongitudinal direction；
Transverse wave sound velocity CHorizontal barIs 340m/s to 15240 m/s;
longitudinal acoustic velocity CLongitudinal directionIs 340m/s to 15240 m/s;
step two, setting an imaging area in a Space-Defect method;
after receiving image information represented by ultrasonic echo data acquired by a linear array transducer, a computer storing a Space-Defect method respectively sets the X-axis image length LxY-axis image length LyZ-axis image length LzPixel pitch d of X-axis imagexPixel pitch d of Y-axis imageyPixel pitch d of Z-axis imagez；
The information of any one imaging point in different planes is as follows: in the XY plane of the coordinate system O-XYZ, any imaging point information is expressed as
Figure FDA0003257619340000031
In an XZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure FDA0003257619340000032
In a YZ plane of a coordinate system O-XYZ, any imaging point information is expressed as
Figure FDA0003257619340000033
After the working parameters of the bilinear array transducer are set, the first transmitting end probe
Figure FDA0003257619340000034
Excitation and first receiving end probe
Figure FDA0003257619340000035
Receiving, one-time collecting ultrasonic echo data to form an image information, and recording as a first group of images
Figure FDA0003257619340000036
For processing the first set of images in a computer storing the Space-Defect method
Figure FDA0003257619340000037
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the first set of images are taken in the XZ plane of the coordinate system O-XYZ
Figure FDA0003257619340000038
Can be expressed as
Figure FDA0003257619340000039
The subscript h is the first set of images
Figure FDA00032576193400000310
The identification number of the medium imaging point, h is 1,2,3 …;
after the working parameters of the bilinear array transducer are set, the probe at the second transmitting end
Figure FDA00032576193400000311
Excitation and second receiving end probe
Figure FDA00032576193400000312
Receiving, one-time collecting ultrasonic echo data to form one image information, and recording as a second group of images
Figure FDA00032576193400000313
For processing the second set of images in the computer storing the Space-Defect method
Figure FDA00032576193400000314
Since the present invention is concerned with the defects in the thickness direction of the turbine disk, the second set of images is taken in the XZ plane of the coordinate system O-XYZ
Figure FDA00032576193400000315
Can be expressed as
Figure FDA00032576193400000316
The lower corner mark j is the second group of images
Figure FDA00032576193400000317
The identification number of the medium imaging point, j is 1,2,3 …;
after the working parameters of the bilinear array transducer are set, the probe at the alpha transmitting end
Figure FDA00032576193400000318
Excitation and a-th receiving end probe
Figure FDA0003257619340000041
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as a group a image
Figure FDA0003257619340000042
The computer with Space-Defect method stored is used for processing the a-group image
Figure FDA0003257619340000043
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group a images are taken in the XZ plane of the coordinate system O-XYZ
Figure FDA0003257619340000044
Can be expressed as
Figure FDA0003257619340000045
The lower corner mark k is the a-th group image
Figure FDA0003257619340000046
The identification number of the medium imaging point, k is 1,2,3 …;
after the working parameters of the bilinear array transducer are set, the probe at the A-th transmitting end
Figure FDA0003257619340000047
Excitation and A receiving end probe
Figure FDA0003257619340000048
Receiving, acquiring ultrasonic echo data once to form an image information, and recording as group A image
Figure FDA0003257619340000049
For processing in a computer storing Space-Defect method, the A group image
Figure FDA00032576193400000410
Since the present invention is concerned with defects in the thickness direction of the turbine disk, the group A images are taken in the XZ plane of the coordinate system O-XYZ
Figure FDA00032576193400000411
Can be expressed as
Figure FDA00032576193400000412
The lower corner mark l is the A-th group image
Figure FDA00032576193400000413
The identification number of the medium imaging point, i is 1,2,3 …;
obtaining an image set IM to be processed after the processing of the step two, and
Figure FDA00032576193400000414
acquiring a defect-imaging point by adopting an acoustic wave model;
according to the sound wave model discrimination method, the image set obtained in the step two is subjected to
Figure FDA00032576193400000415
Defect detection is carried out, and defect-imaging points can be obtained;
upper half-defect position acoustic model;
when the defect is positioned on the upper half part of the diffusion welding interface and corresponds to an angle with an incident angle alpha smaller than a reflection angle beta, the working parameter of the incident wave is set to be a longitudinal wave sound velocity CLongitudinal directionThe working parameter of the reflected wave is set as the transverse wave sound velocity CHorizontal barAcquiring to obtain a defect-imaging point in the image;
middle part-defect position acoustic model;
when the defect is located in the holeIn the middle of the scatter-welded interface, the incident sound wave may be a shear sound velocity C at an angle where the incident angle α is equal to the reflection angle βHorizontal barThe longitudinal wave sound velocity C can also beLongitudinal direction(ii) a Due to the longitudinal wave sound velocity CLongitudinal directionThe reflection angle of is less than the transverse wave sound velocity CHorizontal barThe larger the angle of incidence angle alpha, the higher the longitudinal wave sound velocity CLongitudinal directionThe less reflected energy; therefore, the working parameter of the incident wave is selected to be the transverse wave sound velocity CHorizontal barAnd the defects in the image, namely imaging points, are found out by the total reflection of the incident wave;
the lower half-defect position acoustic model;
when the defect is positioned at the lower half part of the diffusion welding interface and is equivalent to an angle with an incidence angle alpha larger than a reflection angle beta, according to Snell's law, at the moment, the longitudinal wave sound velocity C should be selected for the incident waveLongitudinal directionAs an operating parameter, the transverse wave sound velocity C should be selected as the reflected waveHorizontal barAnd as a working parameter, finding out a defect-imaging point in the image is realized.
3. The method of claim 2, wherein the non-destructive testing of the turbine disk using the bilinear array transducer comprises: the bilinear array transducers are symmetrically distributed in the thickness direction of the measured object;
4. a method of non-destructive testing of a turbine disk using a bilinear array transducer as claimed in claim 2 or 3, wherein: nondestructive testing can be carried out on the turbine disc with a narrow gap;
5. the method of claim 2, wherein the non-destructive testing of the turbine disk using the bilinear array transducer comprises: a bilinear array transducer is used for image acquisition;
performance parameters of the bilinear array transducer: the sampling frequency is 100MHz, the pulse voltage is 50V-100V, the pulse mode is negative square wave, the pulse width is 30ns/2.5 ns-1000 ns/2.5ns, and the sound velocity is 340 m/s-15240 m/s.
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