CN201681029U - Testing device for simulating and testing failure of heat fatigue of high-temperature parts in real time - Google Patents
Testing device for simulating and testing failure of heat fatigue of high-temperature parts in real time Download PDFInfo
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- CN201681029U CN201681029U CN2010200001590U CN201020000159U CN201681029U CN 201681029 U CN201681029 U CN 201681029U CN 2010200001590 U CN2010200001590 U CN 2010200001590U CN 201020000159 U CN201020000159 U CN 201020000159U CN 201681029 U CN201681029 U CN 201681029U
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Abstract
The utility model belongs to the field of high-temperature part detecting equipment, which particularly relates to a testing device for simulating and testing failure of heat fatigue of high-temperature parts in real time. The device comprises a high-temperature gas bidirectional heating system, a real-time temperature test collecting system, a cooling system, an ARAMIS non-contact type three-dimensional deformation testing system, a PCI-2 sound transmitting non-destructive testing system, a 1260+1296 type material electric alternating current impedance spectroscopy testing system, a test control platform and the like. The device can simulate the heat fatigue working environment of temperature alternating circulation in the high-property aerospace engine, and synchronously realize the real-time data test and analysis of sample temperature, temperature gradient, surface topography image evolution, three-dimensional deformation field, three-dimensional displacement field, interface oxidizing layer, thickening rule, heat fatigue crack growth and expansion, cooling gas flow rate, and the like. The utility model can provide important test platform for effectively evaluating the fatigue failure process and failure mechanism of the high-temperature parts under the high-temperature heat circulation environment.
Description
Technical field
The utility model belongs to high-temperature component checkout equipment field, what be specifically related to is a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time, what be particularly related to is a kind of heat fatigue working environment that is used to simulate aeromotor high temperature alloy and band thermal barrier coating high-temperature component, and realizes the test unit of a plurality of thermal fatigue failure parameter real-time testings.
Background technology
In recent years, along with aeromotor develops to high bypass ratio, high thrust-weight ratio, high turbine inlet temperature (TIT) direction, the working temperature of engine hot parts is more and more higher, particularly fuel gas temperature in the firing chamber and gaseous-pressure improve constantly, compare with first generation machine as gaseous-pressure and to improve 3 times, fuel gas temperature surpasses 1650 ℃, and this makes intensity, reliability and the heat-insulating problem of high-temperature component just seem particularly outstanding.In order to guarantee the performance of engine high-temperature metal parts, prolong the life-span of engine as far as possible, the research staff constantly proposes new solution: on the one hand, improve the preparation technology of high temperature alloy, improve indexs such as its fusing point and elevated temperature strength; On the other hand, utilize the high-intensity characteristics of nonmetal high-melting-point, use monomer structure pottery silicon nitride, silit and zirconia and ceramic matric composite instead of part high temperature alloy, perhaps be coated in high-temperature alloy surface to play the heat insulation and heat control protective effect; Next is the compound type of cooling of advanced design, reduces the surface and internal temperature of high-temperature component, has prolonged the serviceable life of high-temperature component.Yet, in reality is on active service, because high-temperature oxydation, material parameter do not match, factor affecting such as high-temperature material is out of shape, thermal stress, these high-temperature components (as turbo blade, guide vane, leaf groove, rotor etc.) are in the abominable Service Environment of high temperature, high combustion gas erosion, high order heat fatigue for a long time, usually occur ftractureing, come off, thermal fatigue failure and fracture such as interfacial separation, reduced the serviceable life and the reliability of high-temperature component.
Heat fatigue is because material free expansion or contraction that temperature variation causes suffer restraints.Consequently at material internal because of being out of shape the restricted thermal stress that produces.When temperature changed repeatedly, this thermal stress also changed repeatedly, causes material to sustain damage.A lot of high-temperature components in the aeromotor (as the intake and exhaust pipeline of rocket launcher, cylinder, engine, forging die etc.) often bear thermal stress loading effect and heat fatigue cracking occurs repeatedly.And heat fatigue cracking generally forms along the zone of surface heat strain maximum, also often germinate from stress raiser.So for actual working environment, how do we monitor these thermal strain with complex geometric shapes high-temperature component material and thermal stress? how to monitor the germinating of judging the high-temperature component fatigue crack, the moment and the particular location of expansion? do you how to judge the fatigue failure time and the serviceable life of these high-temperature components? in the face of these thorny high temperature test difficult problems, the present both at home and abroad main ground experiment by the ground simulation Service Environment of space worker is as thermal shock test, high-temperature tunnel experiment, the experiment of engine testsand complete machine, single tube burner etc.Although these methods can be simulated some working environment in the aeromotor, but human and material resources expend very big, experimental facilities requires high, and lacks or can't obtain in real time the key message of sample, therefore is difficult to a kind of research and development of products in early stage and pilot plant test that is used for aeromotor.Therefore by design correlation test device and simulation test, how cost-effectively high-temperature component thermal fatigue fracture failure behaviour being characterized, will be the real engineering problem that the space worker must directly face.
The test unit that relates to high-temperature component thermal fatigue property aspect in simulation and the test aeromotor at present has: the artificial defective that can only simulate the single environment situation in the existing environmental test analogue means of improving such as Gong Shengkai, design and developed a class thermal barrier coating service environment simulator (patent publication No.: CN1699994), can realize that to hollow cylinder thermal barrier coating sample temperature and mechanical load rise synchronously, keep and descend, can the real-time testing Temperature Distribution, the Interface Crack spread scenarios.Though this device can be simulated the working environment of aeromotor, mainly lay particular emphasis under the loading and the condition of heating, test interface oxidation, the crack propagation situation of common coating sample, but also do not possess the function of surface topography, bulk deformation situation and the stress distribution of real-time testing high-temperature component.People such as Cheng Laifei disclose a kind of materials for aeroengines hot junction environmental experiment analogy method and device (patent publication No.: CN1546974A), its device is that normal pressure subsonic wind tunnel and material property testing machine are combined, adopt the silicon nitride combined silicon carbide pottery to improve the high temperature resistant level of firing chamber as the firing chamber liner, the structure of its test specimen frame+turning joint+turning handle can be carried out the thermal shock simulation.
Summary of the invention
The purpose of this utility model is to solve the existing thorny difficult problem that exists in the thermal fatigue failure of high-temperature part that detects in real time, a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time is provided, and in process of the test, realize a plurality of heat fatigue parameters are carried out in-situ test, for the thermal fatigue property and the reliability assessment of high-temperature component provides effective solution.
The technical solution adopted in the utility model is: described test unit structure comprises: experimental test platform, and the two-way heating system of high-temperature fuel gas that is connected with this experimental test platform respectively, temperature test acquisition system, cooling system, non-contact 3-D deformation test system, acoustic emission nondestructive detection system, ac impedance frequency spectrum monitoring system, test control platform.
Experimental test platform structure is: the centre position is equipped with 1 anchor clamps and anchor clamps stationary installation that is used for the clamping sample on the experimental test platform, and the anchor clamps upper-lower position is adjustable; The moving guide rail that is supported by interior location-plate and outside fix plate is set respectively in the both sides of anchor clamps, gun fixture is set on moving guide rail, in a side of anchor clamps, the position of close anchor clamps one or more thermocouple fixing devices are set, therein 2 ccd video cameras of the arranged outside of an outside fix plate.
The two-way heating system of described high-temperature fuel gas comprises 2 heat gun, and heated perimeter is 20 ℃～3000 ℃, fixes with gun fixture, is moved by servomotor control spray gun; Be connected with cooling circulating water in the described gun fixture.
All mechanical drive and collection of experiment data on the described test control platform control experimental test platform; Comprise temperature indicator, graphoscope, travel control switch, power light, emergency stop switch, duty display lamp, cooling system gauge tap, cooling system relay indicating light, computing machine on the test control platform.
Described temperature test acquisition system comprises thermopair, temperature indicator, temperature acquisition software, and described thermopair is connected with the temperature indicator that test is controlled on the platform.
Described thermopair adopts the platinum rhodium thermocouple of 1600 ℃ of Type Bs, measures surface, internal channel, 6 temperature of refrigerating gas outlet of sample, realizes the temperature test of effect of heat insulation and assigned address.
Described cooling system comprises air compressor, cooling water tank, flow valve, the cooling duct inlet that connects successively; Refrigerating gas is through cooling duct inlet and cooling water tank, entered by the bottom inlet of sample internal cooling channel, through the sample internal channel, discharged by the refrigerating gas outlet at top.
Described non-contact 3-D deformation test system is an ARAMIS non-contact 3-D distortion on-line measurement system, finishes under hot environment strain field distribution, Stress Field Distribution and the displacement field distribution situation to sample and carries out real-time testing and analysis.
Described acoustic emission nondestructive detection system is that sensitivity is 10
-8The PCI-2 type acoustic emission nondestructive detection system of cm magnitude is implemented under the elevated temperature heat cycling condition, to germinating, expansion and the crackle location of sample internal dynamic in situ detection crackle.
Described ac impedance frequency spectrum monitoring system is a 1260+1296 section bar material electrical property AC impedance frequency spectrum monitoring system, the sample of band thermal barrier coating is carried out the real-time testing of thermal barrier coating inner structure, crack initiation and interface oxidation.
The beneficial effects of the utility model are:
(1) the two-way heating system of the high-temperature fuel gas of test unit described in the utility model is made heating source with the high speed oxygen acetylene torch, and intensification and rate of temperature fall are fast, can reach the working temperature of high-temperature material in the aeromotor.This heating system is to adopt the two-way ring of symmetrical structure around type of heating, it is more even that specimen surface is heated, by the distance of mechanical driving device control heating flame gun, can regulate heating region and heating-up temperature easily, the tired Service Environment of simulation elevated temperature heat again to specimen surface.Characteristics of heating system is: the temperature range of heating is wide, can realize from the heating of 20 ℃～3000 ℃ of scopes; Simple to operate, testing equipment realizes that easily experimentation cost is low, and is convenient to realize coordinating test with other testing tool.
(2) test unit described in the utility model has 2 kinds of dissimilar cooling devices, and a kind of is cooling system to high-temperature clamp, and the mode that passes to chilled water is cooled off; Another kind is that the sample of being with the cooling duct is cooled off, and the mode that passes to cooling air is cooled off.For example the hollow turbine vane sample with the band thermal barrier coating is an example, processing is done in the turbo blade bottom to be handled, internal thread is set, connect the cooling duct, stream cooling in logical cooling air carries out turbo blade, guarantee that the blade internal surface temperature remains on the temperature of setting, and then realize thermograde of formation from ceramic surface to the blade inside surface.Cooling gas flow is by flow valve control and measurement.By external thermopair, can the survey record specimen surface, 6 temperature datas such as sample inside, cooling draught, the effect of heat insulation of effective evaluation coating.
(3) test unit described in the utility model adopts ARAMIS non-contact 3-D distortion on-line measurement system that German GOM company produces as sample 3 D deformation proving installation under the hot environment.Its test philosophy is to adopt Digital Image Correlation Method (DIC method), promptly object under test is taken distortion front and back two width of cloth speckle fields, system software changes into the digital speckle field with speckle field and carries out computing, can measure in the face of real-world object to move, realize that noncontact, the whole audience, terrain use and be convenient to robotization.The important technological parameters of this instrument has: measured specimen surface temperature can be up to 1500 ℃; Ccd video camera resolution is 2448 * 2050 pixels; Real time data processing, its sample frequency is 15-29Hz; Strain measurement scope: 0.01%～500%; Measurement maximal value from the face strain is 140mm.
(4) test unit described in the utility model adopts dynamic in situ detection of PCI-2 type acoustic emission and the signal acquiring processing system that U.S. physical acoustics company produces, the high-temperature component sample inside of dynamic real-time monitoring band heat insulating coat in the heat fatigue simulation test procedure or the germinating and the expansion process of surface crack.Its test philosophy is: when coating inside and surface crack, will launch sound wave.Adopt twin-channel detector, this system can judge position, the type of crackle to the detection of sound wave.The important technological parameters of this instrument is: built-in 18 A/D converters and suitableeer a kind of setting, maximum signal amplitudes 100dB, dynamic range＞85dB, 4 high passes and 6 low passes that are used for short arc, low threshold value (17dB) of processor; Acoustic emission data stream measuring device is housed on the PCI-2, acoustic emission waveform constantly can be turned to hard disk, speed can reach 10M/second; 2 optional parameter passages are housed on the PCI-2 plate, and this passage has 16 A/D converter, and speed is 10000/second, parallel a plurality of FPGA processors and ASIC IC chip.
(5) test unit described in the utility model is selected the 1260+1296 section bar material electrical property AC impedance spectrum testing system of Britain Solartron company for use.This device has highstrung characteristics such as the physical property of band coating high-temperature component, micromechanism, chemical composition, defectives, can be implemented in the military service process of high-temperature material original position assessment and monitoring are carried out in above-mentioned variation.The important technological parameters of this instrument is: range of current is 200nA～2A; Electric current resolution is 1pA; Voltage range is ± 14.5V; Voltage resolution is 1 μ V; Frequency range is 10 μ～1M Hz.
In sum, test unit of the present utility model has following outstanding characteristics: a. can simulate temperature alternating round-robin heat fatigue working environment in the aeromotor, obtain test findings targetedly, for the service life of predicting high-temperature component provides important experimental basis.B. temperature, thermograde, the differentiation of surface topography image, 3 D deformation field, three-D displacement field, interface oxide layer that can real-time testing complex geometric shapes sample and thicken rule, heat fatigue cracking germinating and spread scenarios, cooling gas flow.Wherein function the most outstanding of this device is: can obtain the bulk deformation distribution situation of high-temperature component under hot environment in real time, this will provide very important experimental data to the destruction situation and the reliability of effective prediction high-temperature material.Have not yet to see the patent report of test unit with this respect function.C. the operating temperature range of this device wide (high energy reach 3000 ℃) can be finished the test of high-temperature component material thermal fatigue failure in the simulation different field, and application is strong.
Description of drawings
Fig. 1 is the overall schematic of described test unit;
Fig. 2 is the structural representation of the experimental test platform of described test unit;
Fig. 3 is the test control platform structure synoptic diagram of described test unit;
Fig. 4 is by pyrometry sample and proving installation annexation figure.
Number in the figure:
101-experimental test platform; 2-test control platform; 11-acoustic emission nondestructive detection system; 12-temperature test acquisition system; 13-ac impedance frequency spectrum monitoring system; The 14-cooling system; 16-non-contact 3-D deformation test system; The 102-movable pulley; The 103-cooling water tank; The 104-thermometer; 105-cooling duct inlet; The 106-flow valve; 107-anchor clamps stationary installation; The 108-CCD camera fixing device; The 109-CCD video camera; 110-gas control switch fixed pedestal; The 111-anchor clamps; The 112-gun fixture; Location-plate in the 113-; 114-outside fix plate; The 115-thermocouple fixing device; The 116-moving guide rail; The 201-power switch; The 202-travel control switch; 203-duty display lamp; The 204-power light; The 205-temperature indicator; The 206-graphoscope; 207-cooling system gauge tap; 208-cooling system relay indicating light; The 209-emergency stop switch; The 5-sample; The 501-waveguide; The 502-electrode; The 503-thermopair; 504-cools off top exit; 505-cooling sole inlet.
Embodiment
The utility model provides a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time, below by description of drawings and embodiment the utility model is described further.
As shown in Figure 1, the structure of this test unit comprises: experimental test platform, the two-way heating system of high-temperature fuel gas that is connected with this experimental test platform, temperature test acquisition system 12, cooling system 14, non-contact 3-D deformation test system 16, acoustic emission nondestructive detection system 11, ac impedance frequency spectrum monitoring system 13, test control platform 2 respectively.
As shown in Figure 2, experimental test platform structure is: the centre position is equipped with 1 anchor clamps 111 and anchor clamps stationary installation 107 that is used for clamping sample 5 on experimental test platform 101, and anchor clamps 111 upper-lower positions are adjustable; The moving guide rail 116 that is supported by interior location-plate 113 and outside fix plate 114 is set respectively in the both sides of anchor clamps 111, gun fixture 112 is set on moving guide rail 116, in a side of anchor clamps 111, the position of close anchor clamps 111 6 thermocouple fixing devices 115 are set, therein the arranged outside ccd video camera 109 of an outside fix plate 114.
The two-way heating system of high-temperature fuel gas comprises 2 heat gun, and heated perimeter is 20 ℃～3000 ℃, and is fixing with gun fixture 112, moved by servomotor control spray gun; Be connected with cooling circulating water in the described gun fixture 112.
As shown in Figure 3, all mechanical drive and the collection of experiment data on the test control platform 2 control experimental test platforms 101.Test control platform 2 is provided with temperature indicator 205, graphoscope 206, travel control switch 202, power light 204, emergency stop switch 209, duty display lamp 203, cooling system gauge tap 207, cooling system relay indicating light 208, computing machine.
As shown in Figure 4, temperature test acquisition system 12 comprises thermopair 503, temperature indicator 205, temperature acquisition software, and described thermopair 503 is connected with the temperature indicator 205 that test is controlled on the platform 2.Described thermopair 503 adopts the platinum rhodium thermocouple of 1600 ℃ of Type Bs, measures surface, internal channel, 6 temperature of refrigerating gas outlet of sample 5, realizes the temperature test of effect of heat insulation and assigned address.6 thermopairs 503 are put on experimental test platform 101 by 6 thermocouple fixing devices that move freely 115 respectively, and thermopair 503 is connected with temperature indicator 205 and computing machine that test is controlled on the platform 2; Cooling air, is entered by sample cooling sole inlet 505 through cooling water tank 103 by cooling duct inlet 105, discharges through sample cooling top exit 504, and system is by flow valve 106 control cooling air delivery and test traffics; Ccd video camera 109 is connected with strain on-line testing platform 4; Sample 5 mounted on surface have two electrodes 502, are connected with ac impedance frequency spectrum monitoring system 13 respectively; Two waveguides 501 of sample 5 two ends welding, waveguide is connected with acoustic emission nondestructive detection system 11.
Non-contact 3-D deformation test system 16 is ARAMIS non-contact 3-D distortion on-line measurement system, finishes under hot environment strain field distribution, Stress Field Distribution and the displacement field distribution situation to sample 5 and carries out real-time testing and analysis.
Acoustic emission nondestructive detection system 11 is that sensitivity is 10
-8The PCI-2 type acoustic emission nondestructive detection system of cm magnitude is implemented under the elevated temperature heat cycling condition, to germinating, expansion and the crackle location of sample internal dynamic in situ detection crackle.
Ac impedance frequency spectrum monitoring system 13 is a 1260+1296 section bar material electrical property AC impedance frequency spectrum monitoring system, the sample 5 of band thermal barrier coating is carried out the real-time testing of thermal barrier coating inner structure, crack initiation and interface oxidation.
Use described test unit to be to the step that the turbo blade of being with thermal barrier coating carries out heat fatigue simulation test and real-time testing:
The first step, preparation sample: adopt plasma spray coating process, at certain model hollow turbine vane surface spraying thermal barrier coating heat-barrier material.Its system forms: buffer layer material is the NiCrAIY alloy, and its thickness is about 100 μ m; Ceramic powder material is for containing 8%Y
2O
3Zirconium dioxide, ceramic layer thickness is about 300 μ m.Spray one deck black superhigh temperature resistant lacquer at specimen surface at last, make specimen surface be formed with the speckle field of higher reflective function, with feature speckle field as ARAMIS non-contact 3-D distortion on-line measurement system.
Second step, with electric welding equipment electrode 502, the waveguide 501 of test usefulness are welded in respectively on the turbo blade specimen surface and two ends metallic substrates of the band thermal barrier coating that the first step finishes, the electrode 502 and waveguide 501 other ends are connected to acoustic emission nondestructive detection system 11 and ac impedance frequency spectrum monitoring system 13, then on turbo blade sample 5 stationary fixtures 115 of band thermal barrier coating.Then 4 thermopairs 503 are fixed on enter the mouth 505 places, 1 thermopair of cooling sole that turbo blade ceramic coat surface, 1 thermopair be fixed on the turbo blade cooling duct and are fixed on cooling top exit 504 places of blade cooling duct.Every thermopair is connected respectively to temperature test acquisition system 12, and judges whether operate as normal of each instrument.
In the 3rd step, start ARAMIS non-contact 3-D deformation test system.Regulate CCD camera 109, determine the zone of the sample to be tested of paying close attention to, and carry out the staking-out work in early stage.Operation strain testing software, setting ARAMIS testing software filming frequency is 1/5 seconds, data pattern is preserved in on-line testing automatically.
The 4th goes on foot, and opens the cooling water switch of specimen holder 111 and gun fixture 112.Open the refrigerating gas gauge tap of turbo blade inner passage, refrigerating gas is entered in the blade from cooling duct, turbo blade bottom, discharge, make ceramic coat surface to metallic substrates inside surface form high-temperature gradient by the top through hole.
The 5th step started the quick two-way heating arrangement of oxy-acetylene, regulated the fuel gas flow amount, and the fuel gas temperature of light a fire after 8～10 seconds is stablized.By control mechanical drive switch, turbine blade surface is carried out two-sided Fast Heating, the about 100 ℃/s of heating rate is stabilized in about 11500 ℃ surface temperature, and keeps 5 minutes.In this specific embodiment, each thermal cycle mode is 10s heat time heating time, and temperature retention time is 300s, cool time 200s.Setting times of thermal cycle is 500 times.
The 6th step, in heat fatigue simulated experiment process, the growth development law of the differentiation of the change of temperature field of the turbo blade sample of real-time testing and recording strip thermal barrier coating, the variation of 3 D deformation field, the variation of three-D displacement field, ceramic coat surface topography, the event number of acoustic emission monitor(ing), interface oxide layer and coating shedding situation etc.
The 7th step, treat that simulated experiment is finished after, analyze and the arrangement experimental data, judge the failure mechanism and the hazardous location of the turbo blade floating coat of band thermal barrier coating.
Claims (8)
1. test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time, it is characterized in that, this device comprises: experimental test platform, and the two-way heating system of high-temperature fuel gas that is connected with this experimental test platform respectively, temperature test acquisition system (12), cooling system (14), non-contact 3-D deformation test system (16), acoustic emission nondestructive detection system (11), ac impedance frequency spectrum monitoring system (13), test control platform (2);
Experimental test platform structure is: go up the centre position at experimental test platform (101) 1 anchor clamps (111) and anchor clamps stationary installation (107) that is used for clamping sample (5) is installed, anchor clamps (111) upper-lower position is adjustable; The moving guide rail (116) that is supported by interior location-plate (113) and outside fix plate (114) is set respectively in the both sides of anchor clamps (111), gun fixture (112) is set on moving guide rail (116), in a side of anchor clamps (111), the position of close anchor clamps (111) one or more thermocouple fixing devices (115) are set, therein 2 ccd video cameras of the arranged outside of an outside fix plate (114) (109).
2. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1, it is characterized in that, the two-way heating system of described high-temperature fuel gas comprises 2 heat gun, and heated perimeter is 20 ℃～3000 ℃, and is fixing with gun fixture (112).
3. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1, it is characterized in that, described temperature test acquisition system (12) comprises that described thermopair (503) is connected with temperature indicator (205) by temperature indicator (205), temperature acquisition software on the fixing thermopair (503) of thermocouple fixing device (115), the test control platform (2).
4. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 4 is characterized in that described thermopair (503) adopts the platinum rhodium thermocouple of 1600 ℃ of Type Bs.
5. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1, it is characterized in that described cooling system (14) comprises air compressor, cooling water tank (103), flow valve (106), the cooling duct inlet (105) that connects successively.
6. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1 is characterized in that described non-contact 3-D deformation test system (16) is an ARAMIS non-contact 3-D distortion on-line measurement system.
7. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1 is characterized in that, described acoustic emission nondestructive detection system (11) for sensitivity 10
-8The PCI-2 type acoustic emission nondestructive detection system of cm magnitude.
8. a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time according to claim 1 is characterized in that described ac impedance frequency spectrum monitoring system (13) is a 1260+1296 section bar material electrical property AC impedance frequency spectrum monitoring system.
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| CN102288505A (en) * | 2011-08-08 | 2011-12-21 | 淮阴工学院 | In situ measurement method in surface quality evaluation |
| CN102288505B (en) * | 2011-08-08 | 2012-10-03 | 淮阴工学院 | In situ measurement method in surface quality evaluation |
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| CN104914168B (en) * | 2015-06-23 | 2018-03-09 | 中国科学院上海硅酸盐研究所 | A kind of frock for the detection of thermal barrier coating high temperature acoustic emission signal |
| CN104914168A (en) * | 2015-06-23 | 2015-09-16 | 中国科学院上海硅酸盐研究所 | Tool for detecting high-temperature acoustic emission signal of thermal barrier coating |
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