CN109625317A - A kind of detecting instrument having aircraft and engine component eddy current inspection function concurrently - Google Patents
A kind of detecting instrument having aircraft and engine component eddy current inspection function concurrently Download PDFInfo
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- CN109625317A CN109625317A CN201811439303.8A CN201811439303A CN109625317A CN 109625317 A CN109625317 A CN 109625317A CN 201811439303 A CN201811439303 A CN 201811439303A CN 109625317 A CN109625317 A CN 109625317A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- 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
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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Abstract
The invention discloses a kind of detecting instruments for having aircraft and engine component eddy current inspection function concurrently, comprising: host, engine labyrinth fluted disc feeler lever, aircraft wheel hub feeler lever, the main frame feeler lever of aircraft, the test block of engine labyrinth fluted disc, the test block of aircraft wheel hub, the main frame test block of aircraft；In engine labyrinth fluted disc eddy current inspection, engine labyrinth fluted disc feeler lever is connected into host, looks into benchmark using engine labyrinth fluted disc briquette marking regular inspection；In aircraft wheel hub eddy current inspection, aircraft wheel hub feeler lever is connected into host, looks into benchmark using aircraft wheel hub briquette marking regular inspection；In the main frame eddy current inspection of aircraft, the main frame feeler lever of aircraft is connected into host, looks into benchmark using the main frame briquette marking regular inspection of aircraft.The present invention realizes that previous single aircraft eddy current inspection apparatus and aero-engine are integrated with eddy current inspection apparatus function, and the eddy current inspection of aircraft and engine technical routine is realized using a type equipment.
Description
Technical field
The present invention relates to a kind of Grounds to ensure equipment, especially provides one kind and has the vortex inspection of aircraft and engine component concurrently
Look into the detecting instrument of function.
Background technique
Existing eddy current inspection equipment function is relatively single, and majority is examined to specific a kind of or a kind of detection target
It looks into.Existing eddy current inspection equipment otherwise be to aero-engine component carry out eddy current examination special equipment or be
Aircraft components are carried out with the special equipment of eddy current examination, existing aviation eddy current examination equipment does not have compatible aircraft
With engine components audit function, have a single function；The pattern of feeler lever is designed according only to single aircraft or engine components structure,
It is not able to satisfy aircraft-engine components detection structure requirement；The material and damage data template of test block are not able to satisfy detection calibration
It is required that.
Summary of the invention
The purpose of the present invention is to provide a kind of detecting instruments for having aircraft and engine component eddy current inspection function concurrently, real
Now previous single aircraft eddy current inspection apparatus and aero-engine are integrated with eddy current inspection apparatus function, are reached using a type
The eddy current inspection purpose of equipment realization aircraft and engine technical routine.
The technical scheme is that a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently, packet
It includes: host 100, engine labyrinth fluted disc feeler lever 200, aircraft wheel hub feeler lever 300, the main frame feeler lever 400 of aircraft, the examination of engine labyrinth fluted disc
Block 500, aircraft wheel hub test block 600, the main frame test block 700 of aircraft；In engine labyrinth fluted disc eddy current inspection, by engine labyrinth fluted disc
Feeler lever 200 connects host 100, is demarcated using engine labyrinth fluted disc test block 500 and checks benchmark；In aircraft wheel hub eddy current inspection,
Aircraft wheel hub feeler lever 300 is connected into host 100, is demarcated using aircraft wheel hub test block 600 and checks benchmark；In the main frame vortex inspection of aircraft
The main frame feeler lever 400 of aircraft is connected host 100 by Cha Shi, checks benchmark using the main calibration of frame test block 700 of aircraft.
Preferably, the engine labyrinth fluted disc feeler lever 200 include probe 201, adjustment part 202, feeler lever I 203, pushing block 204,
Handle 205, conducting wire I 206, plug I 207；Described I 203 one end of feeler lever is by adjusting the installation of part 202 probe 201, other end installation
Handle 205, the handle 205 are equipped with the pushing block 204 of driving adjustment part 202, and 205 other end of handle passes through conducting wire I 206
Connection plug I 207.
Preferably, the aircraft wheel hub feeler lever 300 includes detection coil II 301, feeler lever II 302, conducting wire II 303, plug
Ⅱ304；Detection coil II 301 is installed in described II 302 one end of feeler lever, and the other end passes through II 303 connection plug II 304 of conducting wire.
Preferably, the main frame feeler lever 400 of the aircraft includes detection coil III 401, locator 402, set screw 403, visits
Bar III 404, conducting wire III 405, plug III 406；Detection coil III 401 is installed in described III 404 one end of feeler lever, and the other end passes through conducting wire
III 405 connection plugs III 406, installation positioner 402 and set screw 403 on the feeler lever III 404.
Preferably, the engine labyrinth fluted disc test block 500 is arc strip, is set above there are two hole, in hole and hole edge
Edge is equipped with crack defect.
Preferably, the aircraft wheel hub test block 600 is two-sided cutting reference block, and upper surface groove depth from left to right divides
Not Wei 0.1,0.2,0.4,0.6mm, depth allowable error is ± the 15% of depth nominal value, but without departing from ± 0.05mm；Following table
Face groove depth is from left to right respectively 0.8,1.0,1.2,1.4mm, and depth allowable error is ± 0.1mm；Cutting width is
0.13±0.01mm。
Preferably, hole there are five being set in the main frame test block 700 of the aircraft, I flawless of hole；Respectively in hole II, hole III, hole IV
On engrave chink line, hurt width: 0.13 ± 0.02mm quarter, II chink line depth H of hole is 0.67mm, and III chink line depth H of hole is
1.27mm；IV chink line depth H of hole is 3mm, and hole II, hole III, crack length and depth H are isometric on hole IV, accuracy class ±
0.05mm；Hole V is penetrating crack, penetrates slab, hurts 0.13 ± 0.02mm of width, crack length 5mm at quarter, depth H is
10mm, accuracy class ± 0.05mm.
The present invention has following beneficial effect:
The present invention realizes previous single aircraft eddy current inspection apparatus and aero-engine eddy current inspection apparatus function
The eddy current inspection of aircraft and engine technical routine is realized in integration using a type equipment.
Detailed description of the invention
Fig. 1 is eddy current inspection schematic diagram；
Fig. 2 is overall structure figure of the invention；
Fig. 3 is the schematic diagram of host panel in the present invention；
Fig. 4 is the structure chart of engine labyrinth fluted disc feeler lever in the present invention；
Fig. 5 is the structure chart of aircraft wheel hub feeler lever in the present invention；
Fig. 6 is the structure chart of the main frame feeler lever of aircraft in the present invention；
Fig. 7 is the structure chart of engine labyrinth fluted disc test block in the present invention；
Fig. 8 is the structure chart of the main frame test block of aircraft in the present invention；
Fig. 9 is the structure chart of aircraft wheel hub test block in the present invention；
Figure 10 is nine grades of labyrinth defect detecting test position-balancing orifice schematic diagrames of engine；
Figure 11 is 1 frame inspection area (dash area) of aircaft configuration；
Figure 12 is 2 frame inspection area (dash area) of aircaft configuration；
Figure 13 is front hub eddy current inspection emphasis inspection area；
Figure 14 is main hub vortex flaw detection emphasis inspection area；
In figure: 100, host；200, engine labyrinth fluted disc feeler lever；201, it pops one's head in；202, adjustment part；203, feeler lever I；204,
Pushing block；205, handle；206, conducting wire I；207, plug I；300, aircraft wheel hub feeler lever；301, detection coil II；302, feeler lever II；
303, conducting wire II；304, plug II；400, the main frame feeler lever of aircraft；401, detection coil III；402, locator；403, spiral shell is positioned
Silk；404, feeler lever III；405, conducting wire III；406, plug III；500, engine labyrinth fluted disc test block；600, aircraft wheel hub test block；
700, the main frame test block of aircraft；
Specific embodiment
The present invention will be described in detail with reference to the accompanying drawings and examples.
One, it summarizes
Eddy current flaw detec be Ground ensure commonly used equipment, present invention is mainly used for before aircraft/main wheel wheel hub, activity
The balancing orifice nondestructive flaw detection examination of nine grades of labyrinths of the structural members such as wheel rim, structural frames and engine detects.
Two, working principle (as shown in Figure 1)
Eddy current inspection is one of many NDT (non-destructive testing) method, its applied electromagnetics basic theories is detected as conductor
Basis.When the properties that defect or measuring metallic materials occur in conductive surface or near surface change, vortex it is strong
Degree and distribution change therewith, by the situation of change of detection vortex, instruct the presence of conductor defect indirectly and metal is
It is no to be changed.
The principle of eddy current flaw detec is to be made to generate eddy current in conductor component with magnetizing coil, measures electricity by search coil
The variable quantity of stream, to obtain component defect for information about.It is different according to the shape of search coil, through mode can be divided into and (used
In wire rod, bar and tubing), sonde-type (for component surface part detect) and plug-in type (for pore inside detection)
Three kinds.The probe form that equipment uses is sonde-type and plug-in type.
Three, master-plan (as shown in Figure 2)
Zhu Ji system software develops design again, for nine grades of labyrinth eddy current inspections of integrated engine, aircraft wheel hub with
Three Xiang Gongneng of aircaft configuration frame flaw detection.The feeler lever for being used for aircraft wheel hub and aircaft configuration frame flaw detection is newly developed, redesign has
The protection of specific environment adaptability.
For eddy current flaw detec after Integration Design, exemplar is two packing cases, and one is mainframe box, and one is feeler lever case, because
The work of engine eddy current inspection is more, and use is more frequent, and the quantity of configuration is more.
A kind of detecting instrument having aircraft and engine component eddy current inspection function concurrently, comprising: host 100, engine labyrinth
Fluted disc feeler lever 200, aircraft wheel hub feeler lever 300, the main frame feeler lever 400 of aircraft, engine labyrinth fluted disc test block 500, aircraft wheel hub test block
600, the main frame test block 700 of aircraft；In engine labyrinth fluted disc eddy current inspection, engine labyrinth fluted disc feeler lever 200 is connected into host
100, it is demarcated using engine labyrinth fluted disc test block 500 and checks benchmark；In aircraft wheel hub eddy current inspection, by aircraft wheel hub feeler lever
300 connection hosts 100, are demarcated using aircraft wheel hub test block 600 and check benchmark；In the main frame eddy current inspection of aircraft, by aircraft master
Frame feeler lever 400 connects host 100, checks benchmark using the main calibration of frame test block 700 of aircraft.
Four, host design (as shown in Figure 3)
Host functionalities design:
Easy to operate: menu prompt, hot key help.
Actions menu: main menu divides menu to show that directly operation interface is intuitive.
Display: it uses EL screen (organic EL display panel).
Data analysis: instrument can be played back, analyzed and be printed to signal collected.
Data storage: detection parameters, figure, file can be stored in instrument and call at any time.
Data communication: network interface or USB communication interface and computer or similar instrument communication, conveyor apparatus figure can be passed through
The data such as shape, file.
Portable practical: it is small in size, light-weight, low energy consumption, it is compact-sized light.AC/DC integrated power module, instrument
It can be continuous work 8 hours or more under battery power supply.
Balance: Fast simulation balancing technique and digital electronic equilibrium technology are used.
Gain adjustment: advanced gain techniques, adjustable extent is big, and it is thin to adjust step-length.
Display function: having more track graphical displays, Automatic calendar, time showing, and on-line operation prompt helps to show.
Using simplicity: not needing to do detected surface any processing；It does not need to do detected object and specially magnetize.
Highly sensitive: the position of metal defect and size can determine in the detection process.
Main machine structure design:
Eddy current flaw detec is integrated portable equipment, using electroluminescent display panel, touch keyboard operation, built-in charging electricity
Pond.User can need to match the external equipments such as printer according to detection.Instrument is not necessarily to using total digitalization design, built-in computer
Excessive control handle dial switch, repertoire are completed with operation by software control.
Five, feeler lever designs
1, engine labyrinth fluted disc feeler lever
As shown in figure 4, engine labyrinth fluted disc feeler lever 200 is by 201, adjustment part 202, feeler lever I 203, pushing block 204, hand of popping one's head in
Handle 205, conducting wire I 206, plug I 207 form.Probe 201 be used for EDDY CURRENT, adjustment part 202 for be adjusted into hole visit mouth and
Adjustment 201 measurement angles of probe, feeler lever I 203 adapt to operating space adjustment molding, the mobile driving adjustment part of the adjustment of pushing block 204
202, handle 205 is held for operator, and conducting wire I 206 is used for transmission electric signal, and plug I 207 is used to connect biography with host 100
Pass electric signal.Feeler lever detects end and is designed to can be changed bending angle manually, realizes that the flaw detection direction of 90 degree of probe and 180 degree becomes
It changes.
Engine labyrinth fluted disc feeler lever 200 can enter flaw detection position in engine installation state, and probe 201 passes through engine
It observes lid position and keeps straight, when flaw detection, be able to enter the balancing orifice parallel with engine axis.
2, aircraft wheel hub feeler lever
As shown in figure 5, aircraft wheel hub feeler lever 300 is by detection coil II 301, feeler lever II 302, conducting wire II 303, plug II
304 compositions；Detection coil II 301 is used for EDDY CURRENT, and feeler lever II 302 is held for operator, conducting wire II 303 and plug II
304 are used for electric signal transmission.
Aircraft wheel hub feeler lever 300 is general eddy current inspection feeler lever, predominantly detects Surface Crack of Hub.Aircraft wheel hub feeler lever
300 be hand-held, connects socket by longer harness, and intermediate feeler lever II 302 is shorter, and spy is conveniently protruded into when relatively narrow in flaw detection position
Wound.
3, the main frame feeler lever of aircraft
As shown in fig. 6, the main frame feeler lever 400 of aircraft is by detection coil III 401, locator 402, set screw 403, feeler lever III
404, conducting wire III 405, plug III 406 form；Detection coil III 401 is used for EDDY CURRENT, and locator 402 is for adjusting and positioning
Position is detected, for feeler lever III 404 for holding, conducting wire III 405, plug III 406 are used for transmission electric signal.
The main frame feeler lever 400 of aircraft predominantly detects hole internal fissure.The main frame feeler lever 400 of aircraft passes through the adjustment inspection of set screw 403
Test coil III 401 stretches out the length of fixing seat, to adjust the depth that detection coil III 401 protrudes into measured hole.Deeply it is being tested
Kong Hou realizes the position circumferencial direction detection of this depth in hole, when the main frame feeler lever 400 of aircraft uses by rotary fixing base
It keeps in probe vertical insertion measured hole, set screw 403 could rotate feeler lever, feeler lever III after need to being locked with Speical screwdriver
It also needs to keep vertical with direction in hole when 404 rotation.
Six, test block designs
1, engine labyrinth fluted disc test block
Engine labyrinth fluted disc test block 500 is designed according to the material of detection part, structure.Engine labyrinth fluted disc test block 500 is set
It is calculated as arc strip, with a thickness of 5mm, makes two holes above, size is respectively 5.0mm and 5.2mm.In hole and bore edges,
Crack defect is made, flaw size is shown in Fig. 7.Defect is used for EDDY CURRENT standard comparison.
2, the main frame test block of aircraft
Main 700 material of frame test block of aircraft is the same as 2 frame of 1 frame of aircaft configuration and structure.The main frame knot of the main frame test block structural simulation of aircraft
Structure, before manufacture of intraocular defect；I flawless of hole；Chink line is engraved on hole II, hole III, hole IV respectively, carves and hurts width: 0.13 ±
0.02mm, II chink line depth H of hole are 0.67mm, and III chink line depth H of hole is 1.27mm；IV chink line depth H of hole is 3mm,
Hole II, hole III, crack length and depth H are isometric on hole IV, accuracy class ± 0.05mm；Hole V is penetrating crack, penetrates thickness
Plate, quarter hurt 0.13 ± 0.02mm of width, crack length 5mm, depth H 10mm, accuracy class ± 0.05mm.In side electricity consumption
Chemical attack marking mark, which is carved, hurts length, and the label and crackle of marking are ipsilateral；2.5mm aperture beside diameter 6.5mm aperture,
Before riveting two layers of test block, rivets and complete in thicker test block.Two layers of test block is riveted by 6 rivets, rivet aperture is 4mm.
3, aircraft wheel hub test block
Aircraft wheel hub test block 600 evaluates the two-sided quarter of depth of defect referring to GJB 2908-97 " eddy-current test method " standard
Slot reference block is made of two-sided cutting.Hub vortex is examined identical as tested part with reference block material.
Upper surface groove depth is from left to right respectively 0.1,0.2,0.4,0.6mm, and depth allowable error is that depth is nominal
± the 15% of value, but without departing from ± 0.05mm；Lower surface groove depth is from left to right respectively 0.8,1.0,1.2,1.4mm, depth
Degree allowable error is ± 0.1mm；Cutting width is 0.13 ± 0.01mm.Before manufacture of intraocular defect, by GJB2367A-2005 into
Row fluorescent penetrant detects, and the artificial defect in reference block can be vertical or horizontal cutting, and the cross-sectional shape of cutting is V-type.It is right
Than the cutting in test block using machining, electrical discharge machining or chemical attack.Do not allow that test block is caused to deform when processing.Do not permit
Permitted have other surfaces opening display.
Seven, eddy current detection method
1, nine grades of labyrinths of engine
Flexible borescope is ready to, is allowed to be in standby.Borescope flexible probe is inserted into engine main duct
The hole on supporting plate top.Borescope flexible probe is transferred to the remote location of nine grades of labyrinth balancing orifices, adjusts probe orientation, it is ensured that
Borescope can see nine grades of labyrinth balancing orifices and feeler lever sensor, locking borescope probe.
It is in straight configuration that eddy current flaw detec feeler lever handle pushing block, which is adjusted, by sensor, and feeler lever sensor is inserted into supporting plate lower part
Hole.After the insertion of feeler lever sensor, eddy current flaw detec feeler lever sensor is affranchised plumbness.Being changed a job with Special rocking, it is slow to have
Engine high pressure rotor certain angle is moved in slow-speed, and a balancing orifice of nine grades of labyrinths is made to be in the right opposite of feeler lever sensor.
By borescope observation examined balancing orifice and feeler lever sensor, sensor vertical is inserted into nine grades of high-pressure compressor
First balancing orifice of labyrinth.
It after checking out first balancing orifice, sensor vertical is extracted out and is maintained at is inserted into position, rotate high pressure rotor,
The insertion position that nine grades of next balancing orifices of labyrinth are in feeler lever sensor is observed by borescope.
It repeats upper balancing orifice defect detecting test work and carries out defect detecting test.
2, aircaft configuration frame
The fatigue crack of 1 frame region of aircaft configuration, 16 plate nut hole 6.5H9 (in figure in ellipse) inner walls (see Figure 11).
The fatigue crack of 2 frame region of aircaft configuration, 9 plate nut hole 6.5H9 (in figure in ellipse) inner walls (see Figure 12).
1 frame region of structure, 16 self-locking nuts and 2 frame region of structure, 9 Self-locking screws are removed from aircraft.Remove aircraft
Corresponding covering.Feeler lever probe vertical is inserted in the hole, rotation feeler lever one circle to two circles, when rotation also needs to keep feeler lever probe and hole
Interior direction is vertical.All aircaft configuration frame plate nut holes of defect detecting test in order.
5~10 holes of every inspection carry out primary calibration to sensor with test block, continue checking after calibration is without exception, such as
There is exception, the plate nut hole that rechecking has been crossed on inspection after calibration.
Inspection finishes, and restores aircaft configuration frame covering, restores corresponding plate nut Self-locking screw.
3, aircraft wheel hub
Remove wheel hub.Probe vertical is put down gently in check point.With " W " scanning mode inspection one week, scanning spacing was less than
2mm, Scanning speed about 25mm/s.Successively all check point scannings of interior half wheel hub are finished, replacement is wanted when checking outer half wheel hub
Equipment is recalibrated using test block.
If there is the signal to form an angle with shaking signal, and enter alert box, then there may be crack defects.When
It was found that when nearby, good place " balances " simultaneously rechecking again, good with whether checking signal has when having doubtful crackle
Repeatability.
It keeps probe vertical with check surface when scanning, and pays attention to observation signal track.If signal along shake signal trajectory into
Enter alert box, does not indicate that there are crackles；Real Signal of Cracks is to form an angle from equalization point and shaking signal into report
Alert frame.
Normal, host, probe and test block through nine grades of labyrinths flaw detection module parameters of field adjustable present invention flaw detection engine
On-line debugging parameter is normal, and defect can be shown and be alarmed.Do not tear open aboard ignition electric nozzle state verification can complete it is left,
Nine grades of labyrinth eddy current inspections of right engine, using good.
Ground debugging of the present invention, hub vortex is detected a flaw, and module parameter is normal, and host, probe and test block on-line debugging parameter are just
Often, defect can be shown and is alarmed, test can carry out aircraft main wheel, the structures such as preceding/main wheel wheel hub, movable wheel rim on machine
Part flaw detection, using good.
Ground debugging of the present invention, main frame eddy current inspection module parameter is normal, and host, probe and test block on-line debugging parameter are just
Often, defect can be shown and is alarmed, test can carry out 1 frame of aircaft configuration, 16 plate nut hole 6.5H9 inner hole walls on machine,
2 frame of structure, 9 plate nut hole 6.5H9 inner hole wall flaw detections, using good.
The present invention incorporates use the function of distinct device by optimization design, complete the engine of gainer with
Aircraft eddy current examination technical indicator is saved functionally instead of the inspection work for using two sets of equipment to carry out gainer
Equipment purchase cost improves Ground and ensures utilization rate of equipment and installations, reduces the maintenance cost of equipment, meet aviation
Synthesization, generalization, the miniaturization requirement of ground handling equipment.
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Scholar cans understand the content of the present invention and implement it accordingly, and it is not intended to limit the scope of the present invention.It is all according to the present invention
Equivalent change or modification made by Spirit Essence, should be covered by the protection scope of the present invention.
Claims (7)
1. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently characterized by comprising host
(100), the main frame feeler lever (400) of engine labyrinth fluted disc feeler lever (200), aircraft wheel hub feeler lever (300), aircraft, engine labyrinth fluted disc
Test block (500), aircraft wheel hub test block (600), the main frame test block (700) of aircraft；In engine labyrinth fluted disc eddy current inspection, will start
Machine labyrinth feeler lever (200) connects host (100), is demarcated using engine labyrinth fluted disc test block (500) and checks benchmark；In aircraft wheel
When hub eddy current inspection, aircraft wheel hub feeler lever (300) is connected into host (100), is demarcated using aircraft wheel hub test block (600) and checks base
It is quasi-；In the main frame eddy current inspection of aircraft, by main frame feeler lever (400) connection host (100) of aircraft, the main frame test block of aircraft is used
(700) calibration checks benchmark.
2. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is that the engine labyrinth fluted disc feeler lever (200) includes probe (201), adjustment part (202), feeler lever I (203), pushing block
(204), handle (205), conducting wire I (206), plug I (207)；It installs and visits by adjusting part (202) in described feeler lever I (203) one end
Head (201), the other end install handle (205), and the handle (205) is equipped with the pushing block (204) of driving adjustment part (202), institute
It states handle (205) other end and passes through conducting wire I (206) connection plug I (207).
3. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is that the aircraft wheel hub feeler lever (300) includes detection coil II (301), feeler lever II (302), conducting wire II (303), plug
Ⅱ(304)；Detection coil II (301) are installed in described feeler lever II (302) one end, and the other end passes through conducting wire II (303) connection plug
Ⅱ(304)。
4. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is that the main frame feeler lever (400) of aircraft includes detection coil III (401), locator (402), set screw (403), visits
Bar III (404), conducting wire III (405), plug III (406)；Detection coil III (401) are installed in described feeler lever III (404) one end, another
End passes through conducting wire III (405) connection plug III (406), installation positioner (402) and set screw on the feeler lever III (404)
(403)。
5. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is, the engine labyrinth fluted disc test block (500) is arc strip, sets that there are two holes above, is equipped in hole with bore edges
Crack defect.
6. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is that the aircraft wheel hub test block (600) is two-sided cutting reference block, and upper surface groove depth is from left to right respectively
0.1,0.2,0.4,0.6mm, depth allowable error are ± the 15% of depth nominal value, but without departing from ± 0.05mm；It carves lower surface
Groove depth is from left to right respectively 0.8,1.0,1.2,1.4mm, and depth allowable error is ± 0.1mm；Cutting width is 0.13
±0.01mm。
7. a kind of detecting instrument for having aircraft and engine component eddy current inspection function concurrently described in accordance with the claim 1, special
Sign is, sets that there are five hole, I flawlesses of hole on the main frame test block (700) of aircraft；It is engraved on hole II, hole III, hole IV respectively
Chink line hurts width: 0.13 ± 0.02mm quarter, and II chink line depth H of hole is 0.67mm, and III chink line depth H of hole is 1.27mm；
IV chink line depth H of hole is 3mm, and hole II, hole III, crack length and depth H are isometric on hole IV, accuracy class ± 0.05mm；Hole
V is penetrating crack, penetrates slab, hurts 0.13 ± 0.02mm of width, crack length 5mm, depth H 10mm, precision etc. at quarter
Grade ± 0.05mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811439303.8A CN109625317B (en) | 2018-11-29 | 2018-11-29 | Detection instrument with eddy current inspection function of airplane and engine parts |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811439303.8A CN109625317B (en) | 2018-11-29 | 2018-11-29 | Detection instrument with eddy current inspection function of airplane and engine parts |
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| CN109625317B CN109625317B (en) | 2022-06-03 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113155952A (en) * | 2021-03-26 | 2021-07-23 | 中国飞机强度研究所 | Test block for testing internal crack capability of eddy current detection multilayer structure and application method thereof |
| CN113504248A (en) * | 2021-06-18 | 2021-10-15 | 国营四达机械制造公司 | Auxiliary tool for detecting blade hole of high-pressure compressor of aircraft engine and detection method |
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