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CN112362736B - Gas turbine compressor impeller blade root groove ultrasonic detection device and method - Google Patents

Gas turbine compressor impeller blade root groove ultrasonic detection device and method Download PDF

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Publication number
CN112362736B
CN112362736B CN202011312198.9A CN202011312198A CN112362736B CN 112362736 B CN112362736 B CN 112362736B CN 202011312198 A CN202011312198 A CN 202011312198A CN 112362736 B CN112362736 B CN 112362736B
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arm
probe
blade root
compressor impeller
rotating arm
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CN112362736A (en
Inventor
张炯
肖俊峰
高斯峰
高松
李永君
唐文书
南晴
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Xian Thermal Power Research Institute Co Ltd
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Xian Thermal Power Research Institute Co Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/02—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/22—Details, e.g. general constructional or apparatus details
    • G01N29/223—Supports, positioning or alignment in fixed situation
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/22—Details, e.g. general constructional or apparatus details
    • G01N29/26—Arrangements for orientation or scanning by relative movement of the head and the sensor
    • G01N29/265—Arrangements for orientation or scanning by relative movement of the head and the sensor by moving the sensor relative to a stationary material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/02—Indexing codes associated with the analysed material
    • G01N2291/028—Material parameters
    • G01N2291/02854—Length, thickness
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/02—Indexing codes associated with the analysed material
    • G01N2291/028—Material parameters
    • G01N2291/0289—Internal structure, e.g. defects, grain size, texture

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Acoustics & Sound (AREA)
  • Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)

Abstract

The invention discloses an ultrasonic detection device and method for a blade root groove of a gas turbine compressor impeller. The fixed arm, the lapping claw and the tightening device fix the detection tool on the blade root groove of the compressor impeller; the connecting bolt enables the fixed arm and the rotating arm to rotate around the center of the connecting bolt; the rotating arm is Z-shaped, a vernier is sleeved on the rotating arm and used for measuring the center distance between the ultrasonic probe and the connecting bolt, the upper end of the cantilever is fixed with the vernier, the lower end of the cantilever is connected with the probe clamp, and the probe clamp is used for fixing the ultrasonic probe through screw holes on two side surfaces. The ultrasonic probe is stably and reliably scanned by being stably coupled to the surface of the blade root groove of the impeller of the air compressor, the distance range of the ultrasonic probe during scanning is determined by the distance and angle measuring function of the detection tool, a basis is provided for the establishment of a detection process, and the accurate quantification of the crack size is realized by accurately measuring the position and the swing angle of the ultrasonic probe.

Description

Ultrasonic detection device and method for blade root groove of gas turbine compressor impeller
Technical Field
The invention belongs to the technical field of ultrasonic detection, and relates to an ultrasonic detection device and method for a blade root groove of a gas turbine compressor impeller.
Background
The movable blades of the compressor are main components of the compressor for doing work on gas at the inlet of the gas turbine, and are used as comprehensive functions of the rotary machinery, which are required to bear loads such as centrifugal stress, airflow impact force, vibration stress and the like in the operation process. The compressor movable blade and the compressor rotor are matched through the compressor impeller blade root groove, so that the key of transmitting the moment of the compressor rotor to the compressor movable blade is that the compressor impeller blade root groove not only bears the load effect which is equal or larger, but also has more severe working environment due to corrosion, fretting wear and the like, and the detection of the health state of the compressor impeller blade root groove is particularly important for ensuring the safe and stable operation of the gas turbine.
In the start-stop process of the gas turbine, the stress is maximum at the acute angle of the front end (upstream side) and the rear end (downstream side) of the blade root groove of the compressor impeller, and after a certain number of start-stop cycles, cracks can occur at the acute angle of the bottom of the blade root groove of the compressor impeller. The crack generally propagates in two directions, one along the front and rear surfaces of the rim radially toward the center of the compressor rotor and one along the length (axial) of the root slot.
The existing nondestructive testing technology for cracks of blade root grooves of gas turbine compressor impellers is mainly phased array ultrasonic testing technology, in actual detection, the possible cracks at the acute angles of the blade root grooves are found in time, quantitative evaluation is carried out on the sizes of the cracks, and detection data are provided for safety evaluation of the compressor impellers. Based on the detection tool, the detection tool capable of realizing accurate scanning and accurate positioning of the ultrasonic probe is designed and processed, and has very important significance for improving detection efficiency and quantitative accuracy.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides an ultrasonic detection device and an ultrasonic detection method for a blade root groove of a gas turbine compressor blade root groove, so that accurate scanning and accurate positioning of an ultrasonic probe are realized, and the crack detection efficiency and quantitative accuracy of the blade root groove of the gas turbine compressor blade root groove are improved.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme:
an ultrasonic detection device for a blade root groove of a gas turbine compressor impeller, comprising:
the fixed arms are buckled on the axial end faces of the blade root grooves of the compressor impellers through the overlapping claws at the two ends of the fixed arms;
the rotating arm comprises two transverse connecting arms and a longitudinal connecting arm, one end of the first transverse connecting arm is hinged with one end of the fixed arm, the other end of the first transverse connecting arm is fixedly connected with the bottom end of the longitudinal connecting arm, and the top end of the longitudinal connecting arm is fixedly connected with one end of the second transverse connecting arm;
The probe clamp, the inboard of probe clamp is used for fixed probe, and the bottom of cantilever is connected at the top, and the top fixedly connected with vernier of cantilever, vernier slip cap is established on the second transverse connection arm.
The invention is further improved in that:
The fixed arm comprises two sections, and the two sections are connected through a telescopic tightening device and used for fixing the fixed arm on the compressor impeller.
The tightening device tightens up in a screw compression mode.
The inclination angle of the lapping claw and the axial end face of the blade root groove of the compressor impeller is the same, and an anti-slip rubber sleeve is arranged on the inner side of the lapping claw.
The fixed arm is hinged with the first transverse connecting arm of the rotating arm through a connecting bolt, and the fixed arm and the rotating arm can rotate around the center of the connecting bolt.
The lower end of the connecting bolt is higher than the lower surface of the fixed arm.
Screw holes are respectively formed in two sides of the probe clamp.
The rotating arm is carved with a rotating arm scale with the minimum graduation of 1.0mm, a zero point of the rotating arm scale is positioned at the center of the connecting bolt, the vernier scale with the minimum graduation of 0.9mm is carved on the vernier scale, the fixed arm can be provided with a fixed arm and rotating arm included angle scale for calibrating an included angle between the fixed arm and the rotating arm, the cantilever is carved with a cantilever angle scale with the minimum graduation of 9 degrees, and the probe fixture is carved with a probe fixture angle scale with the minimum graduation of 10 degrees.
An ultrasonic detection method for a blade root groove of a gas turbine compressor impeller comprises the following steps:
The ultrasonic probe is fixed on a probe clamp through a screw hole, the ultrasonic probe moves back and forth along a rotating arm in the detection process, the ultrasonic probe is coupled to the upper surface of a blade root groove of an impeller of the air compressor in the front and back scanning process by a fixed arm, and the scanning position and the range of the probe in the scanning process and the swinging angle are recorded;
When the crack size of the blade root groove of the impeller of the air compressor is quantified, the ultrasonic probe is moved back and forth to find the highest crack wave, the position (L, theta) of the probe at the moment is recorded, the ultrasonic probe is scanned along the direction perpendicular to the length of the probe, the swing angle of the ultrasonic probe is kept unchanged, the probe positions (L 1,θ1) and (L 2,θ2) when the echo amplitude is reduced by 6dB are respectively found, and the crack length L=L 1-L2 at the moment.
Compared with the prior art, the invention has the following beneficial effects:
The ultrasonic probe is stably and reliably scanned by being stably coupled to the surface of the blade root groove of the impeller of the air compressor, the distance range of the ultrasonic probe during scanning is determined by the distance and angle measuring function of the detection tool, a basis is provided for the establishment of a detection process, and the accurate quantification of the crack size is realized by accurately measuring the position and the swing angle of the ultrasonic probe.
Drawings
For a clearer description of the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of a rotary arm scale according to the present invention;
fig. 3 is a schematic view of the inventive cantilever angle scale.
The device comprises a 1-fixed arm, a 2-claw, a 3-tightening device, a 4-connecting bolt, a 5-rotating arm, a 6-vernier, a 7-cantilever, an 8-probe clamp, a 9-screw hole, a 10-rotating arm scale, an 11-vernier scale, a 12-included angle scale between the fixed arm and the rotating arm, a 13-cantilever angle scale and a 14-probe clamp angle scale.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the embodiments of the present invention, it should be noted that, if the terms "upper," "lower," "horizontal," "inner," and the like indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, or the azimuth or the positional relationship in which the inventive product is conventionally put in use, it is merely for convenience of describing the present invention and simplifying the description, and does not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the term "horizontal" if present does not mean that the component is required to be absolutely horizontal, but may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, it should also be noted that, unless explicitly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediate medium, or communicating between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
The invention is described in further detail below with reference to the attached drawing figures:
referring to fig. 1-3, the ultrasonic detection device for the blade root groove of the gas turbine compressor impeller comprises a fixed arm 1, a claw 2, a tightening device 3, a connecting bolt 4 of the fixed arm and a rotating arm, a rotating arm 5, a vernier 6 on the rotating arm, a cantilever 7 for connecting the rotating arm and a probe clamp 8.
The fixed arm 1 is a key for fixing the detection device to a blade root groove of the compressor impeller, the claw 2 is buckled on the axial end face of the blade root groove of the compressor impeller, the claw 2 is tightened through the tightening device 3, the fixed arm 1 and the rotating arm 5 are connected through the connecting bolt 4, the fixed arm 1 and the rotating arm 5 can rotate around the center of the connecting bolt 4, the rotating arm 5 is Z-shaped and is used for accommodating a probe in the vertical direction, the vernier scale 6 is sleeved on the rotating arm 5 and can slide along the rotating arm 5 and is used for measuring the distance between the probe and the center of the connecting bolt 4, the upper end of the cantilever 7 is fixed with the vernier scale 6, the lower end of the cantilever is connected with the probe clamp 8, the probe clamp 8 is used for fixing an ultrasonic probe, and the two sides are provided with 1 screw hole 9 respectively.
The inclination angle of the axial end face of the claw 2 and the axial end face of the blade root groove of the compressor impeller are the same, and a rubber sleeve is arranged on the inner side of the claw 2 to prevent the tool from sliding.
The fixed arm 1 is composed of two sections, and a telescopic tightening device 3 is arranged between the two sections to change the length of the fixed arm 1 and is used for fixing the detection device on the impeller of the air compressor.
The tightening device 3 on the fixed arm 1 is tightened by means of screw compression.
The lower extreme of connecting bolt 4 does not surpass the lower surface of fixed arm 1, prevents to produce the clearance between detection device and the impeller upper surface and leads to the frock to fix unstably.
The rotating arm 5 is carved with a rotating arm scale 10 with the minimum graduation of 1.0mm, and the zero point of the rotating arm scale 10 is arranged at the center of the connecting bolt 4.
The rotating arm 5 is sleeved with a vernier 6, a vernier scale 11 with the minimum graduation of 0.9mm is carved on the vernier 6, and the dislocation amplification principle is adopted, so that the measurement accuracy of 0.1mm is realized.
The conventional method for measuring the angle between the fixed arm 1 and the rotating arm 5 is to set an angle gauge between the fixed arm 1 and the rotating arm 5 for measurement, and in consideration of the practical application process, the detection device is not too complex, so that too many parts are prevented from falling into the compressor cylinder in the field detection. A method is proposed for measuring the angle between the fixed arm 1 and the rotating arm 5 by calibrating the angle between the fixed arm 1 and the rotating arm 5 and marking the corresponding scale 12 on the fixed arm 1.
The cantilever 7 is engraved with a cantilever angle scale 13 with the minimum graduation of 9 degrees, and simultaneously the probe clamp 8 is engraved with a probe clamp angle scale 14 with the minimum graduation of 10 degrees, and the measurement precision of the minimum 1 degree is realized by adopting the dislocation amplification principle.
Screw threads are machined on the inner surfaces of screw holes 9 formed in the left side surface and the right side surface of the probe clamp 8, and the probe can be fixed through the screw holes 9 by screws.
The invention is further described with reference to fig. 1-3:
The ultrasonic probe is fixed on the probe clamp 8 through the screw hole 9, the ultrasonic probe moves back and forth along the rotating arm 5 in the detection process, the detection device ensures that the ultrasonic probe is stably coupled to the upper surface of the blade root groove of the impeller of the air compressor in the front and back scanning process, and meanwhile, the scanning position, the range, the swinging angle and the like of the probe in the scanning process can be recorded. The scanning position and range are determined by the length L of the vernier 6 measured on the rotating arm 5 and the included angle theta of the rotating arm 5 and the fixed arm 1, and the swinging angle is read out by the probe clamp angle scale 14 and the cantilever angle scale 13 of the cantilever 7.
When the crack size of the blade root groove of the impeller of the air compressor is quantified, the ultrasonic probe is moved back and forth to find the highest crack wave, the position (L, theta) of the probe at the moment is recorded, the ultrasonic probe is scanned along the direction perpendicular to the length of the probe, the swing angle of the ultrasonic probe is kept unchanged, and the probe positions (L 1,θ1) and (L 2,θ2) when the echo amplitude is reduced by 6dB are respectively found. At this time, the crack length l=l 1-L2 (positive value).
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (6)

1.一种燃气轮机压气机叶轮叶根槽超声检测装置，其特征在于，包括：1. A gas turbine compressor impeller blade root slot ultrasonic detection device, characterized in that it comprises: 固定臂（1），所述固定臂（1）的两端设置搭爪（2），所述固定臂（1）通过其两端的搭爪（2）扣在压气机叶轮叶根槽的轴向端面；所述固定臂（1）包括两段，两段之间通过可伸缩的收紧装置（3）相连，用于将固定臂（1）固定在压气机叶轮上；A fixed arm (1), wherein claws (2) are arranged at both ends of the fixed arm (1), and the fixed arm (1) is buckled on the axial end surface of the compressor impeller blade root groove through the claws (2) at both ends; the fixed arm (1) comprises two sections, and the two sections are connected by a retractable tightening device (3) for fixing the fixed arm (1) on the compressor impeller; 旋转臂（5），所述旋转臂（5）包括两根横向连接臂和一根纵向连接臂，第一横向连接臂的一端与固定臂（1）的一端铰接，第一横向连接臂的另一端与纵向连接臂的底端固定连接，纵向连接臂的顶端与第二横向连接臂的一端固定连接；A rotating arm (5), the rotating arm (5) comprising two transverse connecting arms and a longitudinal connecting arm, one end of the first transverse connecting arm being hinged to one end of the fixed arm (1), the other end of the first transverse connecting arm being fixedly connected to the bottom end of the longitudinal connecting arm, and the top end of the longitudinal connecting arm being fixedly connected to one end of the second transverse connecting arm; 探头夹具（8），所述探头夹具（8）的内侧用于固定探头，顶部连接悬臂（7）的底端，悬臂（7）的顶端固定连接有游标尺（6），所述游标尺（6）滑动套设在第二横向连接臂上；所述探头夹具（8）的两侧分别开设有螺丝孔（9）；A probe fixture (8), the inner side of the probe fixture (8) is used to fix the probe, the top of the probe fixture (8) is connected to the bottom end of the cantilever (7), the top of the cantilever (7) is fixedly connected to a vernier ruler (6), and the vernier ruler (6) is slidably sleeved on the second transverse connecting arm; screw holes (9) are respectively provided on both sides of the probe fixture (8); 所述旋转臂（5）上刻有最小分度为1.0mm的旋转臂刻度（10），旋转臂刻度（10）的零点位于连接螺栓（4）的中心；所述游标尺（6）上面刻有最小分度为0.9mm的游标尺刻度（11）；所述固定臂（1）上可有用于标定固定臂（1）和旋转臂（5）之间夹角的固定臂与旋转臂夹角刻度（12）；悬臂（7）上刻有最小分度为9°的悬臂角度刻度（13）；探头夹具（8）上刻有最小分度为10°的探头夹具角度刻度（14）。The rotating arm (5) is engraved with a rotating arm scale (10) with a minimum graduation of 1.0 mm, and the zero point of the rotating arm scale (10) is located at the center of the connecting bolt (4); the vernier scale (6) is engraved with a vernier scale scale (11) with a minimum graduation of 0.9 mm; the fixed arm (1) may have a fixed arm and rotating arm angle scale (12) for calibrating the angle between the fixed arm (1) and the rotating arm (5); the cantilever (7) is engraved with a cantilever angle scale (13) with a minimum graduation of 9°; and the probe fixture (8) is engraved with a probe fixture angle scale (14) with a minimum graduation of 10°. 2.根据权利要求1所述的燃气轮机压气机叶轮叶根槽超声检测装置，其特征在于，所述收紧装置（3）通过螺丝压紧的方式进行收紧。2. The gas turbine compressor impeller blade root groove ultrasonic detection device according to claim 1, characterized in that the tightening device (3) is tightened by screw tightening. 3.根据权利要求1或2所述的燃气轮机压气机叶轮叶根槽超声检测装置，其特征在于，所述搭爪（2）与压气机叶轮叶根槽轴向端面的倾斜角度相同，且内侧设置有防滑的橡胶套。3. The gas turbine compressor impeller blade root groove ultrasonic detection device according to claim 1 or 2, characterized in that the claw (2) has the same inclination angle as the axial end surface of the compressor impeller blade root groove, and an anti-slip rubber sleeve is provided on the inner side. 4.根据权利要求1所述的燃气轮机压气机叶轮叶根槽超声检测装置，其特征在于，所述固定臂（1）与旋转臂（5）的第一横向连接臂通过连接螺栓铰接，固定臂（1）和旋转臂（5）均能够绕连接螺栓（4）的中心进行旋转。4. The gas turbine compressor impeller blade root groove ultrasonic detection device according to claim 1 is characterized in that the fixed arm (1) and the first transverse connecting arm of the rotating arm (5) are hinged by a connecting bolt, and the fixed arm (1) and the rotating arm (5) can both rotate around the center of the connecting bolt (4). 5.根据权利要求4所述的燃气轮机压气机叶轮叶根槽超声检测装置，其特征在于，所述连接螺栓（4）的下端高于固定臂（1）的下表面。5. The gas turbine compressor impeller blade root groove ultrasonic detection device according to claim 4, characterized in that the lower end of the connecting bolt (4) is higher than the lower surface of the fixing arm (1). 6.一种采用权利要求1-5任一项所述装置的燃气轮机压气机叶轮叶根槽超声检测方法，其特征在于，包括以下步骤：6. A method for ultrasonically detecting the blade root groove of a gas turbine compressor impeller using the device according to any one of claims 1 to 5, characterized in that it comprises the following steps: 将超声探头通过螺丝孔（9）固定在探头夹具（8）上，在检测过程中超声探头沿着旋转臂（5）前后移动，固定臂（1）使超声探头在前后扫查过程中耦合在压气机叶轮叶根槽上表面，同时对探头在扫查过程中的扫查位置及范围、摆动角度的进行记录；扫查位置及范围通过游标尺（6）在旋转臂（5）上测量的长度L、旋转臂（5）和固定臂（1）的夹角θ确定，摆动角度通过探头夹具角度刻度（14）与悬臂（7）的悬臂角度刻度（13）确定；The ultrasonic probe is fixed to the probe fixture (8) through the screw hole (9). During the detection process, the ultrasonic probe moves forward and backward along the rotating arm (5). The fixed arm (1) couples the ultrasonic probe to the upper surface of the compressor impeller blade root groove during the forward and backward scanning process. At the same time, the scanning position and range and the swing angle of the probe during the scanning process are recorded. The scanning position and range are determined by the length L measured by the vernier ruler (6) on the rotating arm (5) and the angle θ between the rotating arm (5) and the fixed arm (1). The swing angle is determined by the probe fixture angle scale (14) and the cantilever angle scale (13) of the cantilever (7); 在对压气机叶轮叶根槽裂纹尺寸定量时，前后移动超声探头找到裂纹最高波，记录此时探头的位置（L, θ），将超声探头沿垂直于探头长度的方向进行扫查，保持超声探头的摆动角度不变，分别找到回波幅度降低6dB时的探头位置（L 1, θ 1）和（L 2, θ 2），此时裂纹长度L=L 1-L 2。When quantifying the crack size of the compressor impeller blade root groove, move the ultrasonic probe back and forth to find the highest wave of the crack, record the position of the probe at this time ( L , θ ), scan the ultrasonic probe in a direction perpendicular to the probe length, keep the swing angle of the ultrasonic probe unchanged, and find the probe positions ( L1 , θ1 ) and ( L2 , θ2 ) when the echo amplitude is reduced by 6dB. At this time, the crack length L = L1 - L2 .
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