CN114113321A - Gas turbine compressor impeller root groove phased array ultrasonic detection system and method - Google Patents
Gas turbine compressor impeller root groove phased array ultrasonic detection system and method Download PDFInfo
- Publication number
- CN114113321A CN114113321A CN202111343029.6A CN202111343029A CN114113321A CN 114113321 A CN114113321 A CN 114113321A CN 202111343029 A CN202111343029 A CN 202111343029A CN 114113321 A CN114113321 A CN 114113321A
- Authority
- CN
- China
- Prior art keywords
- phased array
- array ultrasonic
- root groove
- blade root
- compressor impeller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 56
- 238000000034 method Methods 0.000 title claims abstract description 12
- 230000007547 defect Effects 0.000 claims abstract description 55
- 239000000523 sample Substances 0.000 claims abstract description 49
- 230000001154 acute effect Effects 0.000 claims abstract description 27
- 238000012360 testing method Methods 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims abstract description 10
- 239000007822 coupling agent Substances 0.000 claims description 6
- 238000002592 echocardiography Methods 0.000 claims description 6
- 230000008054 signal transmission Effects 0.000 claims description 6
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000002604 ultrasonography Methods 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 abstract description 2
- 230000035945 sensitivity Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- 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
- 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
- G01N29/262—Arrangements for orientation or scanning by relative movement of the head and the sensor by electronic orientation or focusing, e.g. with phased arrays
-
- 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
- G01N29/28—Details, e.g. general constructional or apparatus details providing acoustic coupling, e.g. water
-
- 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
- G01N29/30—Arrangements for calibrating or comparing, e.g. with standard objects
-
- 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
-
- 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
- G01N2291/04—Wave modes and trajectories
- G01N2291/044—Internal reflections (echoes), e.g. on walls or defects
Landscapes
- Physics & Mathematics (AREA)
- Biochemistry (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Acoustics & Sound (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a phased array ultrasonic detection system and a phased array ultrasonic detection method for a gas turbine compressor impeller blade root groove, wherein the system comprises a phased array ultrasonic probe, a detection tool, a comparison test block and a phased array ultrasonic detector, and the method comprises the following steps: s1: processing reference blocks with equal proportion and same or similar materials; s2: carrying out TCG calibration; s3: finding the highest reflection echo of the defect of the reference block; s4: determining a defect judgment reference; s5: and carrying out actual detection on the leaf root groove to be detected. By designing the special phased array ultrasonic probe, the detection tool and the comparison test block, the invention realizes the effective simulation of the blade root groove crack of the compressor impeller and the accurate positioning of the phased array ultrasonic probe and the defect position in the defect detection; the acute angle of the blade root groove of the compressor impeller is scanned by utilizing the ultrasonic primary wave and secondary wave technology, so that the defects of different positions and trends are comprehensively detected.
Description
Technical Field
The invention belongs to the field of ultrasonic detection, and particularly relates to a phased array ultrasonic detection system and method for a gas turbine compressor impeller blade root groove.
Background
The gas turbine compressor moving blade is a main component of a gas compressor for applying work to gas at the inlet of the gas turbine, and is used as a comprehensive action of bearing loads such as centrifugal stress, airflow impact force, vibration stress and the like during the operation of a rotating machine. The compressor moving blade and the compressor rotor are matched through the compressor impeller root groove, the key of transmitting the compressor rotor torque to the compressor moving blade is that the compressor impeller root groove not only bears the same or larger load action, but also has worse working environment due to the existence of corrosion, fretting wear and the like, and the detection of the health state of the compressor impeller root groove is particularly important for ensuring the safe and stable operation of the gas turbine.
In the starting and stopping process of the gas turbine, the stress at the acute angle between the front end (upstream side) and the rear end (downstream side) of the blade root groove of the compressor impeller is maximum, and after a certain number of starting and stopping cycles, cracks may appear at the acute angle at the bottom of the blade root groove of the compressor impeller.
As the crack propagates, it may cause the stiffness of the rim of the impeller between the root grooves to decrease, thereby causing the loosening of the compressor moving blades. In addition, the variation of the blade root holding rigidity may affect the frequency response of the compressor moving blade, and finally cause high-cycle fatigue damage such as impeller blade root slot abrasion, blade crack and the like. The radial expansion of the crack along the front and rear surfaces of the rim may further cause the fracture of the compressor impeller, thereby causing major accidents of the unit.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a phased array ultrasonic detection system and method for a gas turbine compressor impeller root groove, which are used for carrying out in-situ phased array ultrasonic detection on a weak area of the compressor impeller root groove, finding out possible defects such as cracks in advance and the like, and ensuring the operation safety of a gas turbine unit.
The invention is realized by adopting the following technical scheme:
a phased array ultrasonic detection system for a gas turbine compressor impeller blade root groove comprises a phased array ultrasonic probe, a detection tool, a comparison test block and a phased array ultrasonic detector;
the phased array ultrasonic probe comprises a shell, a back lining, an electrode lead, a wafer, a matching layer and a wedge block; the shell is provided with a corresponding signal transmission interface, and the electric signal generated by the phased array ultrasonic probe is transmitted to the phased array ultrasonic detector through a cable; the back lining is in direct contact with the back surface of the wafer, can absorb high-amplitude ultrasonic waves emitted to the back surface of the wafer and reflected by a workpiece, has a vibration stopping effect on the wafer, reduces the width of an ultrasonic pulse signal and improves the axial resolution; the electrode lead is led out from the back of each array element of the wafer and is collected to a signal transmission interface on the shell; the wafer consists of a plurality of array elements, and each array element can independently excite and receive ultrasonic waves; the matching layer is in direct contact with the wafer and is used as a medium for transmitting the ultrasonic waves emitted by the wafer into the wedge block; the wedge block is connected with the probe shell, a coupling agent is filled between the upper surface of the wedge block and the matching layer and is in direct contact with the upper surface of the wedge block, and the lower surface of the wedge block is in direct contact with the root groove to be detected through the coupling agent;
the detection tool stably fixes the phased array ultrasonic probe on the upper surface of the to-be-detected blade root groove reference block, can realize stable coupling and continuous scanning of the phased array ultrasonic probe on the surface of the to-be-detected blade root groove, and can accurately measure and record the position and the swing angle of the phased array ultrasonic probe;
the overall dimension of the reference block is completely the same as that of the blade root groove to be detected, and artificial defects with different lengths, depths, shapes and trends are processed at the parts where the defects are easy to appear, so that the reference block is used for simulating various defect forms which are easy to appear in the blade root groove.
The invention has the further improvement that the detection tool is fixed on the upper surface of the reference test block of the blade root groove of the compressor impeller in a magnet or mechanical fixing mode, and does not have obvious relative displacement with the upper surface of the reference test block in the detection process.
The invention is further improved in that the parts of the reference block which are easy to have defects are sharp angles at the front end and the rear end.
The phased array ultrasonic detector is further improved in that the phased array ultrasonic detector is connected with the phased array ultrasonic probe through a cable, and the phased array ultrasonic detector at least has 64 channels, so that the pulse voltage and the pulse width can be adjusted.
A phased array ultrasonic detection method for a gas turbine compressor impeller blade root groove is based on the phased array ultrasonic detection system for the gas turbine compressor impeller blade root groove, and comprises the following steps:
s1: processing defects with different sizes, shapes and trends at acute angles of the leaf root groove reference test blocks made of the same material or similar materials according to the size, shape and material processing proportion of the leaf root groove to be detected;
s2: connecting a phased array ultrasonic probe with a phased array ultrasonic detector, setting pulse voltage, pulse width and focusing rule, and carrying out TCG calibration on a standard test block;
s3: fixing a phased array ultrasonic probe on the upper surface of a reference block through a detection tool, transmitting ultrasonic waves to carry out sector scanning on the acute angle position of a leaf root groove reference block, finding out the highest reflection echo by moving the phased array ultrasonic probe, and if the set defect reflection echo cannot be clearly distinguished, adjusting pulse voltage, pulse width and focusing rule until the clear distinguishing of the defect reflection echo is realized;
s4: after finding out the reflection echoes of the defects on the reference block, integrating the images and waveform display of S scanning and A scanning, enabling the reflection echoes to be displayed more clearly by adjusting the gain and scanning range of the phased array ultrasonic detector, and taking the images and waveforms of the S scanning and A scanning as the reference for judging the defects;
s5: fixing a phased array ultrasonic probe on the upper surface of a blade root groove to be detected through a detection tool, scanning through the detection tool, and judging that the detected part has no crack if a reflection echo at an acute angle of the blade root groove does not exceed a reference; and if the reflection echo at the acute angle of the blade root groove exceeds the reference, displaying and positioning the position of the defect through S scanning and A scanning, and quantifying the size of the defect.
The invention is further improved in that the defect size at the acute angle of the reference block is set according to the allowable minimum size defect, the shape and the trend of the defect are set by statistically finding the defect and analyzing the structure and the stress condition of the root groove.
The invention is further improved in that the sharp angle of the blade root groove is detected by adopting primary waves and secondary waves.
The invention has the further improvement that the focusing mode of the ultrasonic wave adopts depth focusing, and the focusing position is near the depth position at the acute angle of the blade root groove.
The invention has at least the following beneficial technical effects:
according to the phased array ultrasonic detection system for the blade root groove of the compressor impeller of the gas turbine, the special phased array ultrasonic probe, the detection tool and the comparison test block are designed, so that effective simulation of the blade root groove crack of the compressor impeller and accurate positioning of the phased array ultrasonic probe and the defect position in detection are realized, and a reliable and complete phased array ultrasonic detection system is provided for field in-situ detection of the blade root groove crack of the compressor impeller.
The phased array ultrasonic detection method for the blade root groove of the gas turbine compressor impeller provided by the invention has the advantages that the acute angle of the blade root groove of the compressor impeller is scanned by utilizing the ultrasonic primary wave and secondary wave technology, so that the defects of different positions and trends are comprehensively detected; the method combines S scanning and A scanning, and realizes accurate detection of the position and the trend of the defect by adjusting the pulse width, the pulse voltage and the focusing rule and accurately determining the position and the direction of the phased array ultrasonic probe.
Drawings
FIG. 1 is a schematic diagram of a gas turbine compressor impeller root groove phased array ultrasonic detection system and method of the present invention.
Description of reference numerals:
1-phased array ultrasonic probe, 101-shell, 102-backing, 103-electrode lead, 104-wafer, 105-matching layer, 106-wedge, 2-detection tool, 3-comparison block, 301-comparison block upper surface, 302-acute angle, 4-phased array ultrasonic detector, 5-ultrasonic wave, 501-primary wave and 502-secondary wave.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, the phased array ultrasonic detection system for the blade root slot of the gas turbine compressor impeller provided by the invention comprises a phased array ultrasonic probe 1, a detection tool 2, a reference block 3 and a phased array ultrasonic detector 4.
The phased array ultrasonic probe 1 includes a housing 101, a backing 102, electrode leads 103, a wafer 104, a matching layer 105, and a wedge 106; the shell 101 is provided with a corresponding signal transmission interface, and an electric signal generated by the phased array ultrasonic probe 1 can be transmitted to the phased array ultrasonic detector 4 through a cable; the back lining 102 is directly contacted with the back surface of the wafer 104, can absorb high-amplitude ultrasonic waves emitted by the wafer 104 to the back surface and reflected by a workpiece, has a vibration stopping effect on the wafer, reduces the width of an ultrasonic pulse signal and improves the axial resolution; the electrode lead 103 is led out from the back of each array element of the wafer 104 and is collected to a signal transmission interface on the shell 101; the wafer 104 is composed of a plurality of array elements, each array element can independently excite and receive ultrasonic waves, and the array element is the most core part in the phased array ultrasonic probe 1; the matching layer 105 is in direct contact with the wafer 104 and mediates the ultrasonic waves emitted by the wafer 104 into the wedge 106; the wedge 106 is connected with the probe shell 101 through a screw, the upper surface of the wedge is filled with coupling agent and directly contacts with the matching layer 105, and the lower surface of the wedge is directly contacted with a root groove to be detected through the coupling agent.
The detection tool 2 stably fixes the phased array ultrasonic probe 1 on the upper surface 301 of the leaf root groove contrast test block to be detected, can realize stable coupling and continuous scanning of the phased array ultrasonic probe 1 on the surface of the leaf root groove to be detected, and can accurately measure and record the position and the swing angle of the phased array ultrasonic probe 1.
The overall dimension of the reference block 3 is completely the same as that of the blade root groove to be detected, artificial defects with different lengths, depths, shapes and trends are processed at the parts where the defects are easy to appear, and various defect forms which are easy to appear in the blade root groove are simulated.
The detection tool 2 is fixed on the upper surface 301 of the reference test block of the blade root groove of the compressor impeller in a magnet or mechanical fixing mode and the like, and does not generate obvious relative displacement with the upper surface 301 of the reference test block in the detection process.
The reference block 3 is prone to defects, which are generally acute angles 302 between the front end and the rear end.
The phased array ultrasonic detector 4 is connected with the phased array ultrasonic probe 1 through a cable, and the phased array ultrasonic detector 4 at least has 64 channels, so that the pulse voltage and the pulse width can be adjusted.
A phased array ultrasonic detection method for a gas turbine compressor impeller blade root groove comprises the following steps:
s1: and processing defects with different sizes, shapes and trends at acute angles 302 of the leaf root groove reference test block 3 made of the same material or similar materials according to the equal proportion of the size, the shape and the material processing of the leaf root groove to be detected.
S2: the phased array ultrasonic probe 1 is connected with the phased array ultrasonic detector 4, pulse voltage, pulse width, focusing rule and the like are set, and TCG calibration is carried out on a standard test block.
S3: the phased array ultrasonic probe 1 is fixed on the upper surface 301 of a reference block through the detection tool 2, ultrasonic waves 5 are emitted to conduct sector scanning on the acute angle 302 of the leaf root groove reference block, and the highest reflection echo is found by moving the phased array ultrasonic probe 1. If the set defect reflection echo cannot be clearly distinguished, the clear distinguishing of the defect reflection echo can be realized by adjusting the pulse voltage, the pulse width, the focusing rule and the like.
S4: after the reflection echoes of the defects are found out on the reference block 3, the images and waveform display of the S scanning and the A scanning are integrated, the reflection echoes are displayed clearly by adjusting the gain, the scanning range and the like of the phased array ultrasonic detector 4, and the images and waveforms of the S scanning and the A scanning at the moment are used as the reference for judging the defects.
S5: fixing a phased array ultrasonic probe 1 on the upper surface of a blade root groove to be detected through a detection tool 2, scanning through the detection tool 2, and judging that the detected part has no crack if a reflection echo at an acute angle of the blade root groove does not exceed a reference; and if the reflection echo at the acute angle of the blade root groove exceeds the reference, displaying and positioning the position of the defect through S scanning and A scanning, and quantifying the size of the defect.
The defect size at the acute angle 302 of the reference block is set according to the allowable minimum size defect, and the shape and the trend of the defect are set by counting the defects found and analyzing the structure and the stress condition of the root groove.
The sharp corner 302 of the root groove can be detected by using a primary wave 501 and a secondary wave 502.
The focusing mode of the ultrasonic wave 5 adopts depth focusing, and the focusing position is near the depth position 302 at the acute angle of the blade root groove.
The invention is further illustrated:
the phased array ultrasonic probe 1 is stably coupled on the upper surface 301 of the reference block through the detection tool 2 and is aligned to the acute angle 302 of the compressor impeller blade root groove reference block. The phased array ultrasonic detector 4 emits pulse current to excite the phased array ultrasonic probe 1 to generate ultrasonic waves 5, the excitation sequence of each array element of the phased array probe wafer 104 is controlled to control the sound beam deflection angle, the defects of the acute angle 302 can be scanned by primary waves 501 and secondary waves 502, the phased array ultrasonic probe 1 is moved to find the highest echo of the defective primary waves 501 and secondary waves 502, and the highest echo serves as the phased array ultrasonic detection sensitivity.
The method comprises the steps of coupling a phase control array ultrasonic probe 1 on the upper surface of a blade root groove of a gas turbine compressor impeller to be detected through a detection tool 2, detecting the blade root groove of the gas turbine compressor impeller in service according to a set sensitivity standard, if a reflected echo is found, evaluating whether the blade root groove is cracked according to the sensitivity standard, and displaying and determining the position, the trend and the like of the crack through A scanning and S scanning.
The above embodiments are merely illustrative of the technical ideas and features of the present invention, and are intended to enable one skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.
Claims (8)
1. A phased array ultrasonic detection system for a gas turbine compressor impeller blade root groove is characterized by comprising a phased array ultrasonic probe (1), a detection tool (2), a reference block (3) and a phased array ultrasonic detector (4);
a phased array ultrasound probe (1) includes a case (101), a backing (102), electrode leads (103), a wafer (104), a matching layer (105), and a wedge (106); wherein, the shell (101) is provided with a corresponding signal transmission interface, and the electric signal generated by the phased array ultrasonic probe (1) is transmitted to the phased array ultrasonic detector (4) through a cable; the back lining (102) is in direct contact with the back surface of the wafer (104), can absorb high-amplitude ultrasonic waves emitted by the wafer (104) to the back surface and reflected by a workpiece, and has a vibration stopping effect on the wafer, so that the width of an ultrasonic pulse signal is reduced, and the axial resolution is improved; the electrode lead (103) is led out from the back of each array element of the wafer (104) and is converged to a signal transmission interface on the shell (101); the wafer (104) is composed of a plurality of array elements, and each array element can independently excite and receive ultrasonic waves; the matching layer (105) is in direct contact with the wafer (104) and serves as a medium for transmitting ultrasonic waves emitted by the wafer (104) into the wedge (106); the wedge block (106) is connected with the probe shell (101), a coupling agent is filled between the upper surface of the wedge block (106) and the matching layer (105) and is in direct contact with the upper surface of the wedge block, and the lower surface of the wedge block is in direct contact with the root groove to be detected through the coupling agent;
the detection tool (2) stably fixes the phased array ultrasonic probe (1) on the upper surface (301) of the to-be-detected blade root groove reference block, can realize stable coupling and continuous scanning of the phased array ultrasonic probe (1) on the surface of the to-be-detected blade root groove, and can accurately measure and record the position and the swing angle of the phased array ultrasonic probe (1);
the overall dimension of the reference block (3) is completely the same as that of the root groove to be detected, and artificial defects with different lengths, depths, shapes and trends are processed at the parts where the defects are easy to appear, so that the reference block is used for simulating various defect forms which are easy to appear in the root groove.
2. The phased array ultrasonic detection system for the blade root groove of the compressor impeller of the gas turbine as claimed in claim 1, wherein the detection tool (2) is fixed on the upper surface (301) of the comparison test block of the blade root groove of the compressor impeller in a magnet or mechanical fixing mode, and does not have obvious relative displacement with the upper surface (301) of the comparison test block in the detection process.
3. The phased array ultrasonic testing system for the root groove of the blade of the compressor impeller of the gas turbine as claimed in claim 1, wherein the parts of the reference block (3) prone to defects are acute angles (302) at the front end and the rear end.
4. The phased array ultrasonic detection system for the blade root slot of the gas turbine compressor impeller according to claim 1, wherein the phased array ultrasonic detector (4) is connected with the phased array ultrasonic probe (1) through a cable, and at least 64 channels are provided for the phased array ultrasonic detector (4) so as to adjust pulse voltage and pulse width.
5. A phased array ultrasonic detection method for a blade root groove of a compressor impeller of a gas turbine, which is based on the phased array ultrasonic detection system for the blade root groove of the compressor impeller of the gas turbine of any one of claims 1 to 4, and comprises the following steps:
s1: processing defects with different sizes, shapes and trends at acute angles (302) of the leaf root groove reference test block according to the size, shape and material processing proportion of the leaf root groove to be detected and the reference test block (3) made of the same material or similar materials;
s2: connecting a phased array ultrasonic probe (1) with a phased array ultrasonic detector (4), setting pulse voltage, pulse width and focusing rule, and carrying out TCG calibration on a standard test block;
s3: fixing a phased array ultrasonic probe (1) on the upper surface (301) of a comparison test block through a detection tool (2), transmitting ultrasonic waves (5) to carry out sector scanning on the acute angle (302) of a leaf root groove comparison test block, finding the highest reflection echo through moving the phased array ultrasonic probe (1), if the set defect reflection echo cannot be clearly distinguished, and adjusting pulse voltage, pulse width and focusing rule until the clear distinguishing of the defect reflection echo is realized;
s4: after the reflection echoes of the defects are found out on the reference block (3), images and waveforms of S scanning and A scanning are displayed comprehensively, the reflection echoes are displayed clearly by adjusting the gain and the scanning range of the phased array ultrasonic detector (4), and the images and waveforms of the S scanning and the A scanning at the moment are used as the reference for judging the defects;
s5: fixing a phased array ultrasonic probe (1) on the upper surface of a blade root groove to be detected through a detection tool (2), scanning through the detection tool (2), and judging that the detected part has no crack if a reflection echo at an acute angle of the blade root groove does not exceed a reference; and if the reflection echo at the acute angle of the blade root groove exceeds the reference, displaying and positioning the position of the defect through S scanning and A scanning, and quantifying the size of the defect.
6. The phased array ultrasonic testing method for the blade root groove of the gas turbine compressor impeller according to claim 5, characterized in that the defect size at the acute angle (302) of the reference block is set according to the allowable minimum size defect, and the shape and the trend of the defect are set by counting the defects found and analyzing the structure and the stress condition of the blade root groove.
7. The phased array ultrasonic testing method for the blade root groove of the gas turbine compressor impeller according to claim 5, characterized in that the acute angle (302) of the blade root groove is detected by using a primary wave (501) and a secondary wave (502).
8. The phased array ultrasonic testing method for the blade root groove of the gas turbine compressor impeller according to claim 5, characterized in that the ultrasonic waves (5) are focused in a depth focusing mode, and the focusing position is near the depth position of an acute angle (302) of the blade root groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111343029.6A CN114113321B (en) | 2021-11-12 | 2021-11-12 | Phased array ultrasonic detection system and method for blade root groove of gas turbine compressor impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111343029.6A CN114113321B (en) | 2021-11-12 | 2021-11-12 | Phased array ultrasonic detection system and method for blade root groove of gas turbine compressor impeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114113321A true CN114113321A (en) | 2022-03-01 |
| CN114113321B CN114113321B (en) | 2024-01-19 |
Family
ID=80379411
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111343029.6A Active CN114113321B (en) | 2021-11-12 | 2021-11-12 | Phased array ultrasonic detection system and method for blade root groove of gas turbine compressor impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114113321B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106342170B (en) * | 2007-12-07 | 2012-08-08 | 中国航空工业集团公司北京航空材料研究院 | Hollow turbine vane wall thickness method for automatic measurement |
| WO2013165817A1 (en) * | 2012-05-02 | 2013-11-07 | Siemens Energy, Inc. | System and method for industrial ultrasonic inspection using phased array probe and distance-gain-size flaw sizing |
| WO2014180262A1 (en) * | 2013-05-08 | 2014-11-13 | 江苏法尔胜材料分析测试有限公司 | Ultrasonic phased array detection method of steel box beam u-rib angle welding seam |
| CN104535648A (en) * | 2014-12-03 | 2015-04-22 | 国网河南省电力公司电力科学研究院 | Method for detecting ultrasonic guided wave of turbine blades |
| WO2016155403A1 (en) * | 2015-04-02 | 2016-10-06 | 深圳市神视检验有限公司 | Ultrasonic detection and locating method and device based on tofd and phased array |
| WO2018040117A1 (en) * | 2016-08-30 | 2018-03-08 | 广东汕头超声电子股份有限公司 | Method and system for ultrasonic imaging detection of welding seam of dual-array probe-based steel-rail |
| CN113311066A (en) * | 2021-03-19 | 2021-08-27 | 西安热工研究院有限公司 | Steam turbine rotor rim reverse T-shaped blade root groove phased array ultrasonic longitudinal wave detection method |
| CN113916988A (en) * | 2021-11-12 | 2022-01-11 | 西安热工研究院有限公司 | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe |
| CN216285075U (en) * | 2021-11-12 | 2022-04-12 | 西安热工研究院有限公司 | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe |
-
2021
- 2021-11-12 CN CN202111343029.6A patent/CN114113321B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106342170B (en) * | 2007-12-07 | 2012-08-08 | 中国航空工业集团公司北京航空材料研究院 | Hollow turbine vane wall thickness method for automatic measurement |
| WO2013165817A1 (en) * | 2012-05-02 | 2013-11-07 | Siemens Energy, Inc. | System and method for industrial ultrasonic inspection using phased array probe and distance-gain-size flaw sizing |
| WO2014180262A1 (en) * | 2013-05-08 | 2014-11-13 | 江苏法尔胜材料分析测试有限公司 | Ultrasonic phased array detection method of steel box beam u-rib angle welding seam |
| CN104535648A (en) * | 2014-12-03 | 2015-04-22 | 国网河南省电力公司电力科学研究院 | Method for detecting ultrasonic guided wave of turbine blades |
| WO2016155403A1 (en) * | 2015-04-02 | 2016-10-06 | 深圳市神视检验有限公司 | Ultrasonic detection and locating method and device based on tofd and phased array |
| WO2018040117A1 (en) * | 2016-08-30 | 2018-03-08 | 广东汕头超声电子股份有限公司 | Method and system for ultrasonic imaging detection of welding seam of dual-array probe-based steel-rail |
| CN113311066A (en) * | 2021-03-19 | 2021-08-27 | 西安热工研究院有限公司 | Steam turbine rotor rim reverse T-shaped blade root groove phased array ultrasonic longitudinal wave detection method |
| CN113916988A (en) * | 2021-11-12 | 2022-01-11 | 西安热工研究院有限公司 | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe |
| CN216285075U (en) * | 2021-11-12 | 2022-04-12 | 西安热工研究院有限公司 | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe |
Non-Patent Citations (3)
| Title |
|---|
| 何成;李文胜;赵建平;尹璐;纪轩荣;陈秀明;: "汽轮机T型叶根的超声相控阵检测", 无损检测, no. 05 * |
| 常文爽;: "汽轮机轮缘超声相控阵检测中缺陷定量研究", 科技展望, no. 24 * |
| 朱学耕;董世运;徐滨士;: "压缩机叶轮叶根缺陷相控阵超声检测方法研究", 中国机械工程, no. 18 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114113321B (en) | 2024-01-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2349911C2 (en) | Turbine blade flaw location method and device | |
| US6082198A (en) | Method of ultrasonically inspecting turbine blade attachments | |
| US6736011B2 (en) | Inspection of shrunk-on steam turbine disks using advanced ultrasonic techniques | |
| US7428842B2 (en) | Phased array ultrasonic testing system and methods of examination and modeling employing the same | |
| JP4694576B2 (en) | Turbine component defect detection method and apparatus | |
| CN104535648A (en) | Method for detecting ultrasonic guided wave of turbine blades | |
| JP2016520202A (en) | Improved inspection method by ultrasonic transmission | |
| JP2013536946A (en) | Phased array ultrasonic inspection system for turbine and generator rotors | |
| CN113311066A (en) | Steam turbine rotor rim reverse T-shaped blade root groove phased array ultrasonic longitudinal wave detection method | |
| JP5530975B2 (en) | Ultrasonic flaw detection method and ultrasonic flaw detection apparatus | |
| JP5104469B2 (en) | Ultrasonic flaw detection apparatus and flaw detection method for turbine blade implantation part | |
| US20090249879A1 (en) | Inspection systems and methods for detection of material property anomalies | |
| CN216285075U (en) | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe | |
| CN114113321B (en) | Phased array ultrasonic detection system and method for blade root groove of gas turbine compressor impeller | |
| CN113916988A (en) | Gas turbine compressor impeller blade root groove phased array ultrasonic detection probe | |
| EP2972289B1 (en) | Ultrasonic examination of components with unknown surface geometries | |
| US20080236288A1 (en) | Inspection systems and methods for detection of material property anomalies | |
| CN113252783A (en) | Method for detecting A-type pulse surface wave of crack of reverse T-shaped blade root groove | |
| CN114858920B (en) | Ultrasonic-based generator end part root crack identification method | |
| JP4077274B2 (en) | Gas turbine air compressor blade surface crack inspection method and apparatus | |
| JPH01145565A (en) | Ultrasonic flaw detector | |
| JP4049985B2 (en) | Ultrasonic flaw detection apparatus and method | |
| CN114113320A (en) | Gas turbine compressor impeller root groove crack defect quantification method | |
| CN113092581B (en) | Method for quantifying transverse cracks on surface of main shaft by using position of central hole of main shaft of wind driven generator | |
| CN216285087U (en) | Gas turbine compressor impeller blade root groove ultrasonic detection reference block |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |