CN101762452B - Test device for simulating and testing thermal fatigue failure of high-temperature part in real time - Google Patents

Test device for simulating and testing thermal fatigue failure of high-temperature part in real time Download PDF

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CN101762452B
CN101762452B CN2010100001519A CN201010000151A CN101762452B CN 101762452 B CN101762452 B CN 101762452B CN 2010100001519 A CN2010100001519 A CN 2010100001519A CN 201010000151 A CN201010000151 A CN 201010000151A CN 101762452 B CN101762452 B CN 101762452B
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testing
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CN101762452A (en
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周益春
毛卫国
吴多锦
杨丽
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Xiangtan University
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Abstract

The invention belongs to the field of high-temperature part detecting equipment, in particular to a test device for simulating and testing the thermal fatigue failure of a high-temperature part in real time. The device mainly comprises a high-temperature gas two-way heating system, a real-time temperature testing and collecting system, a cooling system, an ARAMIS non-contact three-dimensional deformation test system, a PCI-2 AE non-destructive detection system, a 1260+1296-type material electric property AC impedance spectroscopy test system, a test control platform and the like. The device can simulate the thermal fatigue work environment of alternating temperature cycle in a high-performance aircraft engine, and synchronously realize the real-time testing and the analysis to the sample temperature, temperature gradient, surface morphology image evolution, three-dimensional deformation field, three-dimensional displacement field, interfacial oxide layer and thickening law, thermal fatigue crack initiation and propagation, cooling gas flow and other data. The device can provide an important experimental platform for effectively evaluating the fatigue failure process and the failure mechanism of the high-temperature part in the high-temperature thermal cycle environment.

Description

A kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time
Technical field
The invention 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 increasingly high, and particularly fuel gas temperature in the firing chamber and gaseous-pressure improve constantly, and compares with first generation machine like gaseous-pressure and improves 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 (like 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, have 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 (like 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 maximum zone of surface heat strain, 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 through the ground simulation Service Environment of space worker is like 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 through 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 one type of 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; Major side overweights 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 objective of the invention 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 scheme that the present invention adopts is: said test unit structure comprises: the 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 are controlled platform.
Experimental test platform structure is: the centre position is equipped with 1 anchor clamps and clamps device 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, one or more thermocouple fixing devices are set near the position of anchor clamps, 2 ccd video cameras of arranged outside of an outside fix plate therein.
The two-way heating system of said high-temperature fuel gas comprises 2 special 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 said gun fixture.
All mechanical drive and collection of experiment data on the said test control platform control experimental test platform; Comprise temperature indicator, graphoscope, travel control switch, power light, emergency stop switch, duty display lamp, cooling system CS, cooling system relay indicating light, computing machine on the test control platform.
Said temperature test acquisition system comprises thermopair, temperature indicator, temperature acquisition software, and said thermopair is connected with the temperature indicator that test is controlled on the platform.
Said 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.
Said cooling system comprises air compressor, cooling water tank, flow valve, cooling duct inlet; Refrigerating gas is inlet and cooling water tank through the cooling duct, by the bottom inlet entering of sample internal cooling channel, through the sample internal channel, is discharged by the refrigerating gas outlet at top.
Said non-contact 3-D deformation test system is an ARAMIS non-contact 3-D distortion on-line measurement system, accomplishes 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.
Said 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.
Said ac impedance frequency spectrum monitoring system is a 1260+1296 type 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.
Beneficial effect of the present invention is:
(1) the two-way heating system of the high-temperature fuel gas of test unit according to the invention 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; Through 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 according to the invention 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; Processed is done in the turbo blade bottom; Internal thread is set, connects 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 forming a thermograde from ceramic surface to blade inside surface.Cooling gas flow is by flow valve control and measurement.Through 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 according to the invention 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, whole audience property, 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 SF is 15-29Hz; Strain measurement scope: 0.01%~500%; Measurement maximal value from the face strain is 140mm.
(4) test unit according to the invention 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 processor are more fitted 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); The last acoustic emission data stream measuring device that is equipped with of PCI-2 can constantly turn to hard disk with acoustic emission waveform, and 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 according to the invention is selected the 1260+1296 type 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~1MHz.
In sum; Test unit of the present invention 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: under hot environment, can obtain the bulk deformation distribution situation of high-temperature component in real time, this will provide very important experimental data to the destruction situation and the reliability of effective prediction high-temperature material.Do not see at present the patent report of test unit as yet with this respect function.C. the operating temperature range of this device wide (high energy reach 3000 ℃) can be accomplished 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 said test unit;
Fig. 2 is the structural representation of the experimental test platform of said test unit;
Fig. 3 is the test control platform structure synoptic diagram of said test unit;
Fig. 4 is by pyrometry sample and proving installation annexation figure.
Label among 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-clamps device; 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 CS; 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 invention provides a kind of test unit that is used to simulate with testing thermal fatigue failure of high-temperature part in real time, through description of drawings and embodiment the present invention is further specified below.
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 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.
As shown in Figure 2, experimental test platform structure is: the centre position is equipped with 1 anchor clamps 111 and clamps device 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 111,6 thermocouple fixing devices 115 are set near the position of anchor clamps 111, the arranged outside ccd video camera 109 of an outside fix plate 114 therein.
The two-way heating system of high-temperature fuel gas comprises 2 special 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 said gun fixture 112.
As shown in Figure 3, all mechanical drive and 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 CS 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 said thermopair 503 is connected with the temperature indicator 205 that test is controlled on the platform 2.Said 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 through 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 got into by sample cooling sole inlet 505 through cooling water tank 103 through cooling duct inlet 105, discharges through sample cooling top exit 504, and system is through 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.
Cooling system 14 comprises air compressor, cooling water tank 103, flow valve 106, cooling duct inlet 105; Refrigerating gas is inlet 105 and cooling water tank 103 through the cooling duct, by the cooling sole inlet entering of sample 5 internal cooling channels, through the sample internal channel, is discharged by the refrigerating gas outlet at top.
Non-contact 3-D deformation test system 16 is an ARAMIS non-contact 3-D distortion on-line measurement system, and completion strain field distribution, Stress Field Distribution and displacement field distribution situation to sample 5 under hot environment carried 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 type 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 said 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.At last at specimen surface spraying one layer black superhigh temperature resistant lacquer, make specimen surface be formed with the speckle field of higher reflective function, with characteristic speckle field as ARAMIS non-contact 3-D distortion on-line measurement system.
Second step; Be welded in electrode 502, the waveguide 501 of test usefulness respectively on the turbo blade specimen surface and two ends metallic substrates of the band thermal barrier coating that the first step accomplishes with electric welding equipment; Be connected to acoustic emission nondestructive detection system 11 and ac impedance frequency spectrum monitoring system 13 to the electrode 502 and waveguide 501 other ends, 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, confirm 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 CS of turbo blade inner passage, refrigerating gas is got 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 oxy-acetylene Fast Dual to heating arrangement, regulated the fuel gas flow amount, and the fuel gas temperature of light a fire after 8~10 seconds is stablized.Through 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 1150 ℃ 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 incident quantity of acoustic emission monitor(ing), interface oxide layer and coating shedding situation etc.
The 7th step, treat that simulated experiment is accomplished 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 (6)

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 clamps device (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), one or more thermocouple fixing devices (115) are set near the position of anchor clamps (111), 2 ccd video cameras of arranged outside (109) of an outside fix plate (114) therein;
The two-way heating system of said high-temperature fuel gas comprises 2 special heat gun, and heated perimeter is 20 ℃~3000 ℃, and is fixing with gun fixture (112), moved by servomotor control spray gun; Said gun fixture is connected with cooling circulating water in (112);
Said temperature test acquisition system (12) comprises thermopair (503), temperature indicator (205), temperature acquisition software, and said thermopair (503) is connected with the temperature indicator (205) that test is controlled on the platform (2);
Said cooling system (14) comprises air compressor, cooling water tank (103), flow valve (106), cooling duct inlet (105); Refrigerating gas is inlet (105) and cooling water tank (103) through the cooling duct, by the bottom inlet entering of sample (5) internal cooling channel, through the sample internal channel, is discharged by the refrigerating gas outlet at top.
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 is characterized in that all mechanical drive and collection of experiment data on said test control platform (2) the control experimental test platform (101).
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; Said thermopair (503) adopts the platinum rhodium thermocouple of 1600 ℃ of Type Bs; Measure surface, internal channel, 6 temperature of refrigerating gas outlet of sample (5), realize the temperature test of effect of heat insulation and assigned address.
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 1; It is characterized in that; Said non-contact 3-D deformation test system (16) is ARAMIS non-contact 3-D distortion on-line measurement system, accomplishes under hot environment strain field distribution, Stress Field Distribution and displacement field distribution situation real-time testing and analysis to sample (5).
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 is characterized in that, said acoustic emission nondestructive detection system (11) for sensitivity 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.
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; It is characterized in that; Said ac impedance frequency spectrum monitoring system (13) is a 1260+1296 type 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.
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