CN114216960A - Nondestructive testing device for cracks of turbine blades - Google Patents
Nondestructive testing device for cracks of turbine blades Download PDFInfo
- Publication number
- CN114216960A CN114216960A CN202111348471.8A CN202111348471A CN114216960A CN 114216960 A CN114216960 A CN 114216960A CN 202111348471 A CN202111348471 A CN 202111348471A CN 114216960 A CN114216960 A CN 114216960A
- Authority
- CN
- China
- Prior art keywords
- composite probe
- turbine blade
- supporting device
- clamping plates
- sides
- 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
- 238000009659 non-destructive testing Methods 0.000 title claims abstract description 20
- 239000000523 sample Substances 0.000 claims abstract description 63
- 239000002131 composite material Substances 0.000 claims abstract description 54
- 238000000034 method Methods 0.000 claims description 5
- 239000007822 coupling agent Substances 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 3
- 230000005489 elastic deformation Effects 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 description 13
- 230000005284 excitation Effects 0.000 description 6
- 230000005291 magnetic effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000005294 ferromagnetic effect Effects 0.000 description 3
- 238000007689 inspection Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
Images
Classifications
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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
- 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
-
- 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
- G01N2291/26—Scanned objects
- G01N2291/269—Various geometry objects
- G01N2291/2693—Rotor or turbine parts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Abstract
The invention discloses a nondestructive testing device for cracks of turbine blades. The device is integrally and symmetrically arranged and comprises a clamping plate, a supporting device, a tensioning spring, a connecting bolt, a movable hinge and a composite probe; two sides of the supporting device are respectively movably connected with the two clamping plates through corresponding movable hinges, two sides of the supporting device are also respectively movably connected with the two clamping plates through corresponding tensioning springs, a composite probe is arranged below the supporting device, and two sides of the composite probe are respectively movably connected with the two clamping plates through corresponding connecting bolts; turbine blade places the lower surface at composite probe, strutting arrangement's downward pressing, and splint, strutting arrangement and composite probe's relative position change to composite probe takes place elastic deformation, makes composite probe's lower surface closely laminate with turbine blade's surface, and composite probe's operation realizes the nondestructive test to turbine blade surface. The invention improves the nondestructive testing efficiency of the turbine blade and has certain engineering significance.
Description
Technical Field
The invention relates to a nondestructive testing device for a blade in the field of blade detection, in particular to a nondestructive testing device for cracks of a turbine blade.
Background
Before the turbine blade inspection probe uses, need to bond magnetostrictive strip to the apex department of turbine blade, under the condition of detecting turbine blade, often detect a set of turbine blade for the work load of bonding the flexible strip of the term is huge, has also brought huge work load for turbine blade inspection to the disassembling of strip, makes the bonding mode all have certain shortcoming to the detection and the protection of blade.
Due to the special curve of the turbine blade, the magnetostrictive strips are fixed by a hard link mode of bonding, the bonded magnetostrictive strips cannot be reused, and the turbine blade is detected by a group of turbine blades instead of one turbine blade, so that the workload of nondestructive detection on the turbine blade is huge.
Therefore, there is an urgent need for a device that can facilitate the mounting and dismounting of magnetostrictive strips to improve the efficiency of nondestructive testing of turbine blades.
Disclosure of Invention
In order to solve the problems and requirements in the background art, the invention provides a nondestructive testing device for the cracks of the turbine blade, which can be used for frequently adhering and disassembling magnetostrictive strips when detecting the blade group by using a special probe, can also be used for increasing the nondestructive testing of blades with different widths, improving the efficiency of nondestructive testing the blade group and the adaptability of the detected blade, and can realize the soft connection between the magnetostrictive strips and the turbine blade and increase the adaptability of the nondestructive testing blade. The detection efficiency is greatly improved, and the detection types are more abundant.
In order to realize the purpose, the invention adopts the following technical scheme:
the probe devices are integrally and symmetrically arranged and comprise clamping plates, supporting devices, tensioning springs, connecting bolts, movable hinges and composite probes; two sides of the supporting device are respectively movably connected with the two clamping plates through corresponding movable hinges, two sides of the supporting device are also respectively movably connected with the two clamping plates through corresponding tensioning springs, a composite probe is arranged below the supporting device, and two sides of the composite probe are respectively movably connected with the two clamping plates through corresponding connecting bolts; turbine blade places the lower surface at composite probe, strutting arrangement's downward pressing, and splint, strutting arrangement and composite probe's relative position change to composite probe takes place elastic deformation, makes composite probe's lower surface closely laminate with turbine blade's surface, and composite probe's operation realizes the nondestructive test to turbine blade surface.
Two branches are arranged on one side, close to the middle part of the probe device, of the two clamping plates, the first branches of the two clamping plates are movably connected with the two sides of the supporting device through corresponding movable hinges respectively, first spring mounting seats are arranged on the upper surfaces of the first branches of the two clamping plates, second spring mounting seats are symmetrically arranged on the two sides of the upper surface of the supporting device, and two ends of each tensioning spring are connected with the first spring mounting seat and the second spring mounting seat respectively, so that the two sides of the supporting device are also movably connected with the two clamping plates through corresponding tensioning springs respectively;
the second branches of the two clamping plates are movably connected with the two sides of the composite probe through the corresponding connecting bolts respectively, and the movable hinges, the tensioning springs and the connecting bolts are arranged, so that the relative positions of the clamping plates, the supporting devices and the composite probe in the downward pressing process of the supporting devices are changed, and the flexible change of the composite probe is realized to better adapt to the curved surface radian of the turbine blade.
The composite probe comprises a magnetostrictive strip and two exciting circuits, wherein the two exciting circuits are symmetrically arranged on two sides of the upper surface of the magnetostrictive strip, the two exciting circuits are fixedly arranged on the magnetostrictive strip through a coupling agent, a gap is formed between the two exciting circuits and the supporting device, and the two exciting circuits are connected with a power supply.
And a handle is fixedly arranged in the middle of the upper surface of the supporting device.
One side of the tension spring, the connecting bolt and the movable hinge are one or more.
The invention has the beneficial effects that:
the invention greatly improves the detection efficiency, has richer detection types, reduces the time consumed by attaching magnetostrictive strips in the process of detecting the blades, and greatly reduces the time required for nondestructive detection.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a structural isometric view of the present invention.
FIG. 3 is a front view of the present invention in the configuration for inspecting the condition of a turbine blade.
FIG. 4 is a front view of the composite probe.
FIG. 5 is a top view of the composite probe.
FIG. 6 is a front view of a turbine blade.
FIG. 7 is a top view of a turbine blade.
In the figure: 1. the device comprises a clamping plate, 2, a connecting bolt, 3, a movable hinge, 4, a tension spring, 5, a composite probe, 6, a supporting device, 7, a turbine blade, 8, an excitation circuit, 9, a magnetostrictive strip material, 10, a handle, 11, a blade tip, 12 and a blade root.
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
As shown in FIGS. 1-3, the probe device of the invention is integrally and symmetrically arranged and comprises a blade magnetostrictive nondestructive testing clamping plate 1, a supporting device 6, a tension spring 4, a connecting bolt 2, a movable hinge 3 and a composite probe 5; strutting arrangement 6's both sides are respectively through the activity hinge 3 and two splint 1 swing joint that correspond for splint have certain degree of freedom, can change along with fixed turbine blade's width size, increase and detect the blade to the kind, also can adapt to different turbine blade's curve radian, make compound probe can be inseparabler paste on turbine blade, detect turbine blade with stricter. The two sides of the supporting device 6 are respectively movably connected with the two clamping plates 1 through the corresponding tensioning springs 4, and when the tensioning springs 4 are in an initial compression state, the composite probe 5 is in a state to be detected; when the composite probe 5 is bent, i.e. in a test state, the clamping plates on both sides are tightened, so that the spring is in a stretched state. A composite probe 5 is arranged below the supporting device 6, a gap is arranged between the supporting device 6 and the composite probe 5, and two sides of the composite probe 5 are respectively movably connected with the two clamping plates 1 through corresponding connecting bolts 2; a handle 10 is also fixedly arranged in the middle of the upper surface of the supporting device 6 and used for realizing the downward pressing of the supporting device 6. One or more tension springs 4, connecting bolts 2 and movable hinges 3 are arranged on one side, and the specific number is set according to actual needs.
The turbine blade 7 is placed on the lower surface of the composite probe 5, the supporting device 6 is pressed downwards, the relative positions of the clamping plate 1, the supporting device 6 and the composite probe 5 are changed, the composite probe 5 is elastically deformed, the lower surface of the composite probe 5 is tightly attached to the surface of the turbine blade 7, the lower surface of the composite probe 5 completely covers the surface of the blade, and the nondestructive detection of the surface of the turbine blade is realized by the operation of the composite probe 5.
Two branches are arranged on one side, close to the middle part of the probe device, of the two clamping plates 1, the first branches of the two clamping plates 1 are movably connected with the two sides of the supporting device 6 through corresponding movable hinges 3 respectively, first spring mounting seats are arranged on the upper surfaces of the first branches of the two clamping plates 1, second spring mounting seats are symmetrically arranged on the two sides of the upper surface of the supporting device 6, and two ends of each tensioning spring 4 are connected with the first spring mounting seats and the second spring mounting seats respectively, so that the two sides of the supporting device 6 are also movably connected with the two clamping plates 1 through corresponding tensioning springs 4 respectively;
the second branches of the two clamping plates 1 are movably connected with the two sides of the composite probe 5 through the corresponding connecting bolts 2 respectively, and the movable hinges 3, the tensioning springs 4 and the connecting bolts 2 are arranged, so that the relative positions of the clamping plates 1, the supporting devices 6 and the composite probe 5 are changed in the downward pressing process of the supporting devices 6, and the flexible change of the composite probe 5 is realized to better adapt to the curved surface radian of the blade.
As shown in fig. 4 and 5, the composite probe 5 includes a magnetostrictive strip 9 and two exciting circuits 8, the two exciting circuits 8 are symmetrically arranged on two sides of the upper surface of the magnetostrictive strip 9, the two exciting circuits 8 are fixedly mounted on the magnetostrictive strip 9 through a coupling agent, a space is provided between the two exciting circuits 8 and the supporting device 6, and the two exciting circuits 8 are connected with a power supply; when crack detection of the turbine blade is performed, the lower surface of the magnetostrictive strip 9 covers the surface of the blade and is in close contact with the surface of the turbine blade.
The front view and the top view of the turbine blade are respectively shown in fig. 6 and fig. 7, the turbine blade comprises a blade tip 11 and a blade root 12, and the blade tip surface and the blade root surface of the turbine blade need to be detected during actual detection.
The working process of the invention is as follows:
when the nondestructive testing of the cracks of the turbine blades is needed, the turbine blades are fixedly placed, a handle of the device is held tightly, the device is aligned to the blade tip surface or the blade root surface of the turbine blades and is pressed downwards, the lower surface of the composite probe can be attached to the blade tip surface or the blade root surface of the blades, the ultrasonic guided wave instrument is connected with an excitation circuit of the composite probe, the excitation circuit is electrified, and the magnetic field generated by the excitation circuit and pulses generated by magnetostrictive strips are used for carrying out ultrasonic guided wave nondestructive testing on the turbine blades.
The magnetostrictive effect is a phenomenon that when a ferromagnetic body is magnetized by an external magnetic field, the volume and the length of the ferromagnetic body are changed. Although the change of volume and length caused by the magnetostrictive effect is slight, the change of length is much larger than the change of volume, and the magnetostrictive material is a main object of research and application and is called line magnetostriction. The turbine blade has ferromagnetic performance, excitation of an external magnetic field is generated by connecting an excitation circuit 8 on a composite probe 5 through an ultrasonic guided wave instrument, a detection signal is excited at the blade tip under the combined action of a magnetostrictive strip 9 and the external magnetic field, if the blade tip is damaged, the detection signal is propagated in the blade to form a damage signal, and the damage signal is received by the ultrasonic guided wave instrument, so that the damage signal is analyzed to determine the position and the type of the blade tip damage.
Claims (5)
1. A nondestructive testing device for turbine blade cracks is characterized in that a probe device is integrally and symmetrically arranged and comprises a clamping plate (1), a supporting device (6), a tension spring (4), a connecting bolt (2), a movable hinge (3) and a composite probe (5); two sides of the supporting device (6) are movably connected with the two clamping plates (1) through corresponding movable hinges (3), two sides of the supporting device (6) are also movably connected with the two clamping plates (1) through corresponding tensioning springs (4), a composite probe (5) is arranged below the supporting device (6), and two sides of the composite probe (5) are movably connected with the two clamping plates (1) through corresponding connecting bolts (2); the turbine blade (7) is placed on the lower surface of the composite probe (5), the supporting device (6) is pressed downwards, the relative positions of the clamping plate (1), the supporting device (6) and the composite probe (5) are changed, the composite probe (5) is elastically deformed, the lower surface of the composite probe (5) is tightly attached to the surface of the turbine blade, and the nondestructive testing of the surface of the turbine blade is realized by the operation of the composite probe (5).
2. The nondestructive testing device for the cracks of the turbine blade as claimed in claim 1, wherein one side of the two clamping plates (1) close to the middle part of the probe device is provided with two branches, the first branch of the two clamping plates (1) is movably connected with two sides of the supporting device (6) through corresponding movable hinges (3), the upper surface of the first branch of the two clamping plates (1) is provided with a first spring mounting seat, two sides of the upper surface of the supporting device (6) are symmetrically provided with a second spring mounting seat, and two ends of each tension spring (4) are respectively connected with the first spring mounting seat and the second spring mounting seat, so that two sides of the supporting device (6) are also movably connected with the two clamping plates (1) through corresponding tension springs (4);
the second branches of the two clamping plates (1) are respectively movably connected with the two sides of the composite probe (5) through the corresponding connecting bolts (2), and the movable hinges (3), the tension springs (4) and the connecting bolts (2) are arranged, so that the relative positions of the clamping plates (1), the supporting devices (6) and the composite probe (5) in the downward pressing process of the supporting devices (6) are changed, and the flexible change of the composite probe (5) is realized to better adapt to the curved surface radian of the turbine blade.
3. The nondestructive testing device for the cracks of the turbine blade as claimed in claim 1, wherein the composite probe (5) comprises a magnetostrictive strip (9) and two exciting circuits (8), the two exciting circuits (8) are symmetrically arranged on two sides of the upper surface of the magnetostrictive strip (9), the two exciting circuits (8) are fixedly arranged on the magnetostrictive strip (9) through a coupling agent, a gap is arranged between the two exciting circuits (8) and the supporting device (6), and the two exciting circuits (8) are connected with a power supply.
4. The nondestructive testing device for the cracks of the turbine blade as claimed in claim 1, wherein a handle (10) is further fixedly installed at the middle part of the upper surface of the supporting device (6).
5. The nondestructive testing device for turbine blade cracks according to claim 1, wherein one side of the tension spring (4), the connecting bolt (2) and the living hinge (3) is one or more.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111348471.8A CN114216960B (en) | 2021-11-15 | 2021-11-15 | Turbine blade crack nondestructive test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111348471.8A CN114216960B (en) | 2021-11-15 | 2021-11-15 | Turbine blade crack nondestructive test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114216960A true CN114216960A (en) | 2022-03-22 |
| CN114216960B CN114216960B (en) | 2024-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111348471.8A Active CN114216960B (en) | 2021-11-15 | 2021-11-15 | Turbine blade crack nondestructive test device |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102622A (en) * | 2009-12-22 | 2011-06-22 | 西门子公司 | Blade deflection measurement with magnetostrictive sensor |
| CN203824722U (en) * | 2012-12-05 | 2014-09-10 | 工业设备运营公司 | Rotor-blade test board and device therewith |
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| US20170225804A1 (en) * | 2016-02-05 | 2017-08-10 | The Boeing Company | Non-Destructive Inspection of Airfoil-Shaped Body Using Self-Propelling Articulated Robot |
| JP2017198663A (en) * | 2016-04-22 | 2017-11-02 | 三菱日立パワーシステムズ株式会社 | Ultrasonic flaw detecting device, and ultrasonic flaw detecting method |
| KR20180126274A (en) * | 2017-05-17 | 2018-11-27 | 두산중공업 주식회사 | ECT sensor array fixing and surface defect inspection device of the object to be inspected using the same |
| CN109752450A (en) * | 2018-12-07 | 2019-05-14 | 兰州空间技术物理研究所 | A kind of engine blade non-destructive control probe |
| CN208937540U (en) * | 2018-10-31 | 2019-06-04 | 山东晨洋动力科技有限公司 | A kind of turbine blade non-destructive testing device |
| CN112077850A (en) * | 2020-09-17 | 2020-12-15 | 中国矿业大学 | Ultrasonic nondestructive testing probe auto-collimation device based on manipulator and working method |
| CN212341109U (en) * | 2020-07-17 | 2021-01-12 | 杭州浙达精益机电技术股份有限公司 | Guide wave detection device for edge defects of turbine blades |
| CN113466332A (en) * | 2021-07-02 | 2021-10-01 | 西安交通大学 | Flexible array eddy current probe and method for detecting cracks of blade gas film hole edge |
-
2021
- 2021-11-15 CN CN202111348471.8A patent/CN114216960B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102622A (en) * | 2009-12-22 | 2011-06-22 | 西门子公司 | Blade deflection measurement with magnetostrictive sensor |
| CN203824722U (en) * | 2012-12-05 | 2014-09-10 | 工业设备运营公司 | Rotor-blade test board and device therewith |
| US20170225804A1 (en) * | 2016-02-05 | 2017-08-10 | The Boeing Company | Non-Destructive Inspection of Airfoil-Shaped Body Using Self-Propelling Articulated Robot |
| CN105890826A (en) * | 2016-04-01 | 2016-08-24 | 北京工业大学 | Steel blade residual stress micro-magnetic nondestructive testing method and steel blade residual stress micro-magnetic nondestructive testing device based on incremental permeability |
| JP2017198663A (en) * | 2016-04-22 | 2017-11-02 | 三菱日立パワーシステムズ株式会社 | Ultrasonic flaw detecting device, and ultrasonic flaw detecting method |
| KR20180126274A (en) * | 2017-05-17 | 2018-11-27 | 두산중공업 주식회사 | ECT sensor array fixing and surface defect inspection device of the object to be inspected using the same |
| CN208937540U (en) * | 2018-10-31 | 2019-06-04 | 山东晨洋动力科技有限公司 | A kind of turbine blade non-destructive testing device |
| CN109752450A (en) * | 2018-12-07 | 2019-05-14 | 兰州空间技术物理研究所 | A kind of engine blade non-destructive control probe |
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| CN112077850A (en) * | 2020-09-17 | 2020-12-15 | 中国矿业大学 | Ultrasonic nondestructive testing probe auto-collimation device based on manipulator and working method |
| CN113466332A (en) * | 2021-07-02 | 2021-10-01 | 西安交通大学 | Flexible array eddy current probe and method for detecting cracks of blade gas film hole edge |
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| Publication number | Publication date |
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| CN114216960B (en) | 2024-03-08 |
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