CN112345633A - Heavy gas turbine blade TBCs interlayer crack eddy current detection system and method - Google Patents
Heavy gas turbine blade TBCs interlayer crack eddy current detection system and method Download PDFInfo
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- CN112345633A CN112345633A CN202011312421.XA CN202011312421A CN112345633A CN 112345633 A CN112345633 A CN 112345633A CN 202011312421 A CN202011312421 A CN 202011312421A CN 112345633 A CN112345633 A CN 112345633A
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- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
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- G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
- G01N27/90—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
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Abstract
The invention discloses a heavy gas turbine blade TBCs interlayer crack eddy current detection system and a heavy gas turbine blade TBCs interlayer crack eddy current detection method, and belongs to the field of nondestructive detection. The eddy current detecting probe is connected with the eddy current instrument, and the contrast sample is provided with a plurality of rectangular grooves. The eddy current detection system has high sensitivity to interlayer crack signals of the turbine blade TBCs, can effectively detect the interlayer crack defects of the turbine blade TBCs with the minimum dimension of 0.1mm in depth and 2mm in length, the eddy current detection probe can be well attached to the blade profile, the interference caused by the shaking and lifting of the eddy current detection probe is reduced, the flexible rubber mud layer and the insulating rubber cloth layer of the sealing block at the bottom of the eddy current detection probe are convenient to detach and replace, an eddy current signal alarm range is arranged in eddy current detection process parameters, an inspector can clearly distinguish the crack signals from normal signals, and the operation is simple and easy to learn.
Description
Technical Field
The invention belongs to the technical field of eddy current detection, and particularly relates to an eddy current detection system and method for interlayer cracks of a heavy-duty gas turbine blade TBCs.
Background
The turbine blade is a core component of a heavy-duty combustion engine and is made of high-temperature alloy with excellent high-temperature mechanics and oxidation corrosion resistance. To further improve the service temperature, the corrosion and oxidation resistance and the service life of the turbine blade, Thermal Barrier Coatings (TBCs) are sprayed on the surface of the turbine blade. TBCs are composed of a surface ceramic layer and a bonding layer, wherein the surface ceramic layer mainly plays a role in heat insulation and temperature reduction, and the bonding layer plays a role in reducing stress caused by mismatching of thermal expansion coefficients between the ceramic layer and a high-temperature alloy matrix and improving the high-temperature oxidation resistance and corrosion resistance of the matrix.
The comprehensive action of loads such as thermal stress, centrifugal stress (moving blades), airflow impact force, vibration stress and the like in the service process of the turbine blade of the heavy-duty gas turbine easily causes the initiation and the expansion of cracks between a TBCs bonding layer and a ceramic layer, further causes the TBCs to fall off or the oxidation corrosion of a matrix, causes the reduction of the heat insulation effect, the corrosion resistance and the oxidation resistance of the turbine blade, and endangers the safe operation of the gas turbine. Therefore, it is highly desirable to perform nondestructive testing and evaluation of turbine blade TBCs interlaminar cracks.
The eddy current detection technology is one of five conventional nondestructive detection technologies, is sensitive to crack defects on the surface or near surface of a detected workpiece, and is an effective method for detecting interlayer cracks of the TBCs of the turbine blades. The blade profile of the turbine blade is a cambered surface with gradually changed curvature, and the turbine blade is easy to lift off and shake in the vortex detection process, so that a larger interference signal is generated, the probability of misjudgment and missed detection is increased, and the probability is increased frequently
Disclosure of Invention
The invention aims to provide an eddy current detection system and method for interlayer cracks of heavy-duty gas turbine blades, which can effectively detect the interlayer cracks of the heavy-duty gas turbine blades.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme:
a heavy-duty gas turbine blade TBCs interlayer crack eddy current detection system comprises an eddy current instrument, an eddy current detection probe, a comparison sample and a signal transmission line; the eddy current instrument is connected with a probe signal transmission line of the eddy current detection probe through a signal transmission line, and the contrast sample is provided with a plurality of rectangular grooves;
the eddy current detection probe comprises a magnetic core, an excitation coil, a detection coil, a shell and a probe bottom sealing block; the magnetic core is arranged on the shell, the excitation coil and the detection coil are respectively spirally wound on the magnetic core, the excitation coil and the detection coil are led out of the shell through the probe signal transmission line, and the probe bottom sealing block is arranged at the opening end of the shell.
The invention is further improved in that the magnetic core is made of manganese-zinc ferrite, the diameter of the magnetic core is 1-2 mm, and the length of the magnetic core is 4-6 mm.
A further improvement of the present invention is that both the excitation and detection coils are high strength enameled copper wire.
The invention is further improved in that the diameter of the copper wire is 0.05 mm-0.08 mm.
The invention has the further improvement that the shell is made of plastic steel, and the outer diameter of the shell is 5 mm-7 mm.
The invention is further improved in that the bottom sealing block of the probe consists of a hard rubber layer, a flexible rubber mud layer and an insulating rubber cloth layer, wherein the hard rubber layer is arranged close to the opening end of the shell, the thickness of the hard rubber layer is less than 1.5mm, and the thickness of the flexible rubber mud layer is less than 2 mm.
The invention is further improved in that the geometric structure, alloy chemical composition, heat treatment state, surface state and electromagnetic property of the comparison sample are the same as those of the detected blade.
The invention has the further improvement that the comparison sample is provided with a first rectangular groove to a sixth rectangular groove, the first rectangular groove to the third rectangular groove are positioned on the inner cambered surface of the comparison sample blade, the fourth rectangular groove to the sixth rectangular groove are positioned on the back cambered surface of the comparison sample blade, and the depth, the width and the length of the rectangular grooves are respectively 0.1 mm-0.8 mm, 0.1 mm-0.2 mm and 2 mm-8 mm.
The invention has the further improvement that the first rectangular groove and the sixth rectangular groove are parallel to the direction of the blade top, the included angle between the second rectangular groove and the fifth rectangular groove and the direction of the blade top is 15-60 degrees, and the third rectangular groove and the fourth rectangular groove are vertical to the direction of the blade top.
A heavy-duty combustion engine turbine blade TBCs interlaminar crack eddy current testing method comprises the following steps:
the first step is as follows: selecting a corresponding comparison sample according to the model of the detected blade;
the second step is that: connecting the eddy current detection probe with an eddy current instrument, and starting the eddy current instrument;
the third step: debugging the sensitivity of the instrument on a comparison sample;
the fourth step: setting detection process parameters and an alarm range on the vortex instrument according to acceptance criteria;
the fifth step: pressing the eddy current detection probe on the surface of the turbine blade to ensure that the bottom of the eddy current detection probe is well attached to the profile of the turbine blade;
and a sixth step: moving a vortex detection probe on the surface of the detected blade to scan, and observing signals of a vortex instrument;
the seventh step: evaluating cracks in the detected blade by means of the comparison sample;
eighth step: judging according to the alarm range set in the fourth step, and finally giving a detection result;
the ninth step: the vortex finder was turned off.
The invention has at least the following beneficial technical effects:
1. the sensitivity to signal interference caused by the vibration of the eddy current detection probe is low;
2. the eddy current detection probe can be well attached to the profile of the blade, so that the interference caused by shaking and lifting of the eddy current detection probe is reduced;
3. rectangular grooves with different sizes are carved on the comparison sample, so that the method can be effectively used for setting the detection sensitivity and evaluating the size of cracks;
4. the flexible rubber mud layer and the insulating rubber cloth layer of the sealing block at the bottom of the eddy current detection probe are convenient to detach and replace;
5. the magnetic core, the coil, the plastic steel shell, the hard rubber layer, the flexible rubber mud layer and the insulating rubber cloth layer used by the eddy current detection probe are all common materials, and can be conveniently obtained by a person skilled in the art;
6. the eddy current detection system has high sensitivity to interlayer crack signals of the turbine blade TBCs, and can effectively detect the interlayer crack defects of the turbine blade TBCs with the minimum size of 0.1mm in depth and 2mm in length;
7. the eddy current signal alarm range is set in the detection process parameters, so that an inspector can clearly distinguish crack signals and normal signals, and the eddy current detection system is simple to operate and easy to learn.
Drawings
FIG. 1 is a schematic view of an eddy current testing system for interlayer cracks of a heavy-duty gas turbine blade TBCs according to the present invention;
FIG. 2 is a schematic structural diagram of an eddy current testing system for interlayer cracks of a heavy-duty gas turbine blade TBCs according to the present invention;
FIG. 3 is a schematic diagram of an interlayer crack eddy current test comparison sample of a heavy-duty gas turbine blade TBCs of the present invention; wherein fig. 3(a) is a schematic diagram of an intrados surface of a comparative sample, and fig. 3(b) is a schematic diagram of a back arc surface of the comparative sample.
Description of reference numerals:
1-eddy current instrument, 2-eddy current detection probe, 21-magnetic core, 22-excitation coil, 23-detection coil, 24-shell, 25-hard rubber layer, 26-flexible rubber cement layer, 27-insulating rubber cloth layer, 28-probe signal transmission line, 3-comparison sample, 31-comparison sample inner arc surface, 32-comparison sample back arc surface, 33-first rectangular groove, 34-second rectangular groove, 35-third rectangular groove, 36-fourth rectangular groove, 37-fifth rectangular groove, 38-sixth rectangular groove and 4-signal transmission line.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in FIGS. 1 and 2, the eddy current testing system for interlayer cracks of heavy-duty combustion turbine blades TBCs provided by the invention comprises an eddy current instrument 1, an eddy current testing probe 2, a comparison sample 3 and a signal transmission line 4; the eddy current instrument 1 is connected with a probe signal transmission line 28 of the eddy current detection probe 2 through a signal transmission line 4, and a plurality of rectangular grooves are formed in the comparison sample 3; the eddy current detection probe 2 comprises a magnetic core 21, an exciting coil 22, a detection coil 23, a shell 24 and a probe bottom sealing block; wherein, shell 24 has the cavity and one end opening, and magnetic core 21 sets up in shell 24, and excitation coil 22 and detection coil 23 are respectively spiral winding on magnetic core 21, and excitation coil 22 and detection coil 23 draw to the outside of shell 24 through probe signal transmission line 28, and the sealed piece of probe bottom sets up the open end in shell 24.
Wherein, the magnetic core is made of manganese-zinc ferrite with the diameter of 1 mm-2 mm and the length of 4 mm-6 mm. The coil material is high-strength enameled copper wire with the diameter of 0.05-0.08 mm. The shell is made of plastic steel, so that signal interference is reduced, and the outer diameter is 5-7 mm. The probe bottom sealing block consists of a hard rubber layer 25, a flexible rubber mud layer 26 and an insulating rubber cloth layer 27, has good flexibility, good wear resistance and good toughness, can be well attached to the profile of the blade, and is suitable for the change of the curvature of the profile at different positions of the turbine blade.
As shown in FIG. 3, the geometry, alloy chemical composition, heat treatment state, surface state and electromagnetic performance of the comparative sample are the same as those of the blade to be tested, and no natural defect exists. First rectangular channel to third rectangular channel are located contrast sample blade intrados, and fourth rectangular channel to sixth rectangular channel are located contrast sample blade back of the body cambered surface, and the degree of depth, width and the length of rectangular channel are 0.1mm ~ 0.8mm, 0.1mm ~ 0.2mm, 2mm ~ 8mm respectively. The first rectangular groove and the sixth rectangular groove are parallel to the direction of the blade top, the included angles between the second rectangular groove and the fifth rectangular groove and the direction of the blade top are 15-60 degrees, and the third rectangular groove and the fourth rectangular groove are perpendicular to the direction of the blade top.
Example 1
As shown in FIGS. 1 to 3, an eddy current testing system for interlayer cracks of heavy-duty gas turbine blades TBCs comprises: the device comprises an eddy current instrument 1, an eddy current detection probe 2, a comparison sample 3 and a signal transmission line 4. The eddy current detecting probe 2 is connected with the eddy current instrument 1, and the contrast sample 3 is provided with a plurality of rectangular grooves.
The embodiment can be specifically realized as follows:
1) 1 manganese-zinc ferrite cylindrical magnetic core is manufactured, the diameter of the magnetic core is 1.5mm, and the length of the magnetic core is 5 mm;
2) selecting copper wires with the diameter of 0.06mm, and winding 1 eddy current detection excitation coil and 1 detection coil, wherein the inner diameter of each coil is 2mm, and the outer diameter of each coil is 4 mm;
3) sleeving an eddy current detection excitation coil and a detection coil on a magnetic core and fixing;
4) 1 probe plastic steel shell is processed, and the outer diameter is 6 mm;
5) 1 hard rubber layer with the thickness of 1.2mm is sealed at the bottom of the probe;
6) filling a flexible rubber mud layer into the sealed hard rubber layer at the bottom of the probe, wherein the flexible rubber mud layer is slightly convex, and the thickness of the flexible rubber mud layer is 1.5 mm;
7) wrapping the head of the flexible rubber mud layer by using an insulating rubber cloth layer;
8) plugging the bottom of the shell by using the prepared probe bottom sealing blocks from 5) to 7);
9) and connecting the signal transmission line.
The width of the first rectangular groove to the sixth rectangular groove on the comparison sample is 0.1mm, the depth of the first rectangular groove to the third rectangular groove is 0.1mm, 0.2mm, 0.3mm, 0.5mm, 0.6mm and 0.8mm respectively, the length is 2mm, 4mm, 3mm, 6mm, 5mm and 2mm respectively, and the included angles between the second rectangular groove and the fifth rectangular groove and the leaf top direction are 15 degrees and 30 degrees respectively.
The eddy current detection process for the interlayer cracks of the TBCs of the turbine blade is as follows:
1) selecting a corresponding comparison sample according to the model of the detected blade;
2) connecting the eddy current detection probe with an eddy current instrument, and starting the eddy current instrument;
3) debugging the sensitivity of the instrument on a comparison sample;
4) setting detection process parameters and an alarm range on the vortex instrument according to acceptance criteria;
5) pressing the eddy current detection probe on the surface of the turbine blade to ensure that the bottom of the eddy current detection probe is well attached to the profile of the turbine blade;
6) moving a vortex detection probe on the surface of the detected blade to scan, and observing signals of a vortex instrument;
7) evaluating cracks in the detected blade by means of the comparison sample;
8) judging according to the alarm range set in the step 4), and finally giving a detection result;
9) the vortex finder was turned off.
Example 2
As shown in FIGS. 1 to 3, an eddy current testing system for interlayer cracks of heavy-duty gas turbine blades TBCs comprises: the device comprises an eddy current instrument 1, an eddy current detection probe 2, a comparison sample 3 and a signal transmission line 4. The eddy current detecting probe 2 is connected with the eddy current instrument 1, and the contrast sample 3 is provided with a plurality of rectangular grooves.
The embodiment can be specifically realized as follows:
1) 1 manganese-zinc ferrite cylindrical magnetic core is manufactured, the diameter of the magnetic core is 1.5mm, and the length of the magnetic core is 5 mm;
2) selecting copper wires with the diameter of 0.06mm, and winding 1 eddy current detection excitation coil and 1 detection coil, wherein the inner diameter of each coil is 2mm, and the outer diameter of each coil is 4 mm;
3) sleeving an eddy current detection excitation coil and a detection coil on a magnetic core and fixing;
4) 1 probe plastic steel shell is processed, and the outer diameter is 6 mm;
5) 1 hard rubber layer with the thickness of 1.2mm is sealed at the bottom of the probe;
6) filling a flexible rubber mud layer into the sealed hard rubber layer at the bottom of the probe, wherein the flexible rubber mud layer is slightly convex, and the thickness of the flexible rubber mud layer is 1.5 mm;
7) wrapping the head of the flexible rubber mud layer by using an insulating rubber cloth layer;
8) plugging the bottom of the shell by using the prepared probe bottom sealing blocks from 5) to 7);
9) and connecting the signal transmission line.
The width of the first rectangular groove to the sixth rectangular groove on the comparison sample is 0.15mm, the depth of the first rectangular groove to the third rectangular groove is 0.3mm, 0.1mm, 0.2mm, 0.6mm, 0.4mm and 0.7mm respectively, the length is 2mm, 8mm, 5mm, 3mm and 2mm respectively, and the included angles between the second rectangular groove and the fifth rectangular groove and the leaf top direction are 45 degrees and 60 degrees respectively.
The eddy current detection process for the interlayer cracks of the TBCs of the turbine blade is as follows:
1) selecting a corresponding comparison sample according to the model of the detected blade;
2) connecting the eddy current detection probe with an eddy current instrument, and starting the eddy current instrument;
3) debugging the sensitivity of the instrument on a comparison sample;
4) setting detection process parameters and an alarm range on the vortex instrument according to acceptance criteria;
5) pressing the eddy current detection probe on the surface of the turbine blade to ensure that the bottom of the eddy current detection probe is well attached to the profile of the turbine blade;
6) moving a vortex detection probe on the surface of the detected blade to scan, and observing signals of a vortex instrument;
7) evaluating cracks in the detected blade by means of the comparison sample;
8) judging according to the alarm range set in the step 4), and finally giving a detection result;
9) the vortex finder was turned off.
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 (10)
1. A heavy-duty combustion engine turbine blade TBCs interlaminar crack eddy current testing system is characterized by comprising an eddy current instrument (1), an eddy current testing probe (2), a comparison sample (3) and a signal transmission line (4); the eddy current instrument (1) is connected with a probe signal transmission line (28) of the eddy current detection probe (2) through a signal transmission line (4), and the contrast sample (3) is provided with a plurality of rectangular grooves;
the eddy current detection probe (2) comprises a magnetic core (21), an excitation coil (22), a detection coil (23), a shell (24) and a probe bottom sealing block; the magnetic core (21) is arranged on the shell (24), the excitation coil (22) and the detection coil (23) are respectively spirally wound on the magnetic core (21), the excitation coil (22) and the detection coil (23) are led out of the shell (24) through the probe signal transmission line (28), and the probe bottom sealing block is arranged at the opening end of the shell (24).
2. The eddy current inspection system for interlayer cracks of heavy gas turbine blades TBCs of claim 1, wherein the magnetic core (21) is made of Mn-Zn ferrite, and the diameter of the magnetic core (21) is 1mm to 2mm and the length of the magnetic core is 4mm to 6 mm.
3. The heavy duty combustion engine turbine blade TBCs interlaminar crack eddy current inspection system of claim 1, characterized in that both the excitation coil (22) and the detection coil (23) are high strength enameled copper wires.
4. The heavy gas turbine blade TBCs interlaminar crack eddy current inspection system of claim 3, wherein the copper wire diameter is between 0.05mm and 0.08 mm.
5. The eddy current testing system for interlayer cracks of heavy combustion engine turbine blades TBCs of claim 1, characterized in that the outer casing (24) is made of plastic steel, and the outer diameter of the outer casing (24) is 5mm to 7 mm.
6. The eddy current testing system for interlayer cracks of heavy-duty combustion engine turbine blades TBCs according to claim 1, characterized in that the probe bottom sealing block is composed of a hard rubber layer (25), a flexible rubber cement layer (26) and an insulating rubber cloth layer (27), the hard rubber layer (25) is arranged close to the open end of the outer shell (24), the thickness of the hard rubber layer (25) is less than 1.5mm, and the thickness of the flexible rubber cement layer (26) is less than 2 mm.
7. The heavy-duty gas turbine blade TBCs interlaminar crack eddy current inspection system of claim 1, wherein the comparison sample (3) has the same geometry, alloy chemical composition, heat treatment state, surface state and electromagnetic properties as the inspected blade.
8. The eddy current inspection system for the interlayer cracks of the heavy gas turbine blade TBCs of the claim 1, wherein the comparison sample (3) is provided with a first rectangular groove to a sixth rectangular groove, the first rectangular groove to the third rectangular groove are positioned on the intrados of the comparison sample blade, the fourth rectangular groove to the sixth rectangular groove are positioned on the dorsiflexion of the comparison sample blade, and the depth, the width and the length of the rectangular grooves are respectively 0.1mm to 0.8mm, 0.1mm to 0.2mm and 2mm to 8 mm.
9. The eddy current testing system for interlayer cracks of heavy-duty gas turbine blades TBCs of claim 8, wherein the first rectangular groove and the sixth rectangular groove are parallel to the direction of the blade top, the second rectangular groove and the fifth rectangular groove form an angle of 15-60 degrees with the direction of the blade top, and the third rectangular groove and the fourth rectangular groove are perpendicular to the direction of the blade top.
10. A heavy-duty combustion engine turbine blade TBCs interlaminar crack eddy current testing method is characterized by comprising the following steps:
the first step is as follows: selecting a corresponding comparison sample according to the model of the detected blade;
the second step is that: connecting the eddy current detection probe with an eddy current instrument, and starting the eddy current instrument;
the third step: debugging the sensitivity of the instrument on a comparison sample;
the fourth step: setting detection process parameters and an alarm range on the vortex instrument according to acceptance criteria;
the fifth step: pressing the eddy current detection probe on the surface of the turbine blade to ensure that the bottom of the eddy current detection probe is well attached to the profile of the turbine blade;
and a sixth step: moving a vortex detection probe on the surface of the detected blade to scan, and observing signals of a vortex instrument;
the seventh step: evaluating cracks in the detected blade by means of the comparison sample;
eighth step: judging according to the alarm range set in the fourth step, and finally giving a detection result;
the ninth step: the vortex finder was turned off.
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| CN113933119A (en) * | 2021-09-24 | 2022-01-14 | 成都飞机工业（集团）有限责任公司 | Multilayer structure eddy current test block with fatigue cracks, manufacturing method and detection method |
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