Thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device

Abstract

The invention relates to a thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device which comprises a base and a stretching instrument, a heating device, a cooling device and a powder feeding device which are arranged on the base, the stretching instrument is used for applying a stretching load to a sample, the heating device is used for heating the sample, and the cooling device is used for cooling the sample. The cooling device is used for cooling the back surface of the sample, so that the temperature of the back surface of the sample is lower than that of the front surface of the sample, and the interior of the sample has a temperature gradient; the powder feeding device is used for providing powder for the sample, so that the sample is in a powder corrosion state. According to the thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device, the high temperature, thermal gradient, tensile load and corrosion service environment of a thermal barrier coating can be simulated at the same time, and the thermal barrier coating thermodynamic coupling field synchrotron radiation in-situ characterization device is very close to the real service environment.

Description

Technical Field

[0001] The invention relates to an in-situ experiment of a thermal barrier coating, and more specifically to an in-situ characterization device of a thermal barrier coating by using a thermomechanical coupled field synchrotron radiation. Background Art

[0002] In recent years, with the increase in the temperature of the front inlet of the aircraft engine turbine, thermal barrier coatings (TBCs), as an important protective material for the hot end components, play a key role in improving the thrust-to-weight ratio and thermal efficiency of the engine. These ceramic coatings reduce the thermal erosion of the underlying high-temperature alloys from ultra-high-speed and extremely high-temperature combustion gases, and have low thermal conductivity and high-temperature durability that reduces the surface temperature of the high-temperature alloy to produce a large temperature gradient. These excellent properties are conducive to improving the service performance and extending the service life of high-temperature components. In order to analyze the failure mode of the coating and improve the durability of the coating, extensive research has been carried out. However, conventional research methods are not conducive to making judgments on TBCs working in high temperature, high load and large temperature gradient in actual service environment. Therefore, it is necessary to reproduce the extreme environment in which TBCs serve in the laboratory to study the behavior evolution and failure progression of TBCs in similar service environments.

[0003] The failure of TBCs is mainly concentrated on the thermal mismatch between layers and corrosion caused by foreign objects caused by the high-temperature oxidizing environment. Previous studies have made some contributions to reproducing the service environment of TBCs in the laboratory. Different simulation experiments have been carried out on TBCs with different failure states, including static long-term thermal exposure, high-frequency thermal cycles, thermal mechanical fatigue with load, and corrosion of particles such as volcanic ash. Some large-scale devices such as experimental simulators for high-speed gas thermal shock have also appeared. This provides strong evidence for studying the failure progression of TBCs and new ideas for improving performance. However, these laboratory simulation methods have the limitation of decoupling single or several conditions of the service environment, and fail to fully feedback the status of TBCs in real time. Summary of the invention

[0004] The purpose of the present invention is to provide a thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device to simulate the actual service environment of the thermal barrier coating and improve the accuracy of the experiment.

[0005] Based on the above purpose, the present invention provides a thermal barrier coating thermomechanical coupled field synchrotron radiation in-situ characterization device, comprising a base and a tensile tester, a heating device, a cooling device and a powder feeding device arranged on the base, the tensile tester is used to apply a tensile load to a sample, the heating device is used to heat the sample, the cooling device is used to cool the back side of the sample so that the back side temperature of the sample is lower than the front side temperature of the sample and the interior of the sample has a temperature gradient; the powder feeding device is used to provide powder to the sample so that the sample is in a corroded state of the powder.

[0006] Further, the stretching instrument includes an outer frame and a driving mechanism, the outer frame has an installation cavity, a slide plate, a first clamp and a second clamp are arranged in the installation cavity, the slide plate is slidably connected to the outer frame, the first clamp is fixedly connected to the outer frame, the second clamp is fixedly connected to the slide plate, the two ends of the sample are respectively fixed to the first clamp and the second clamp, the driving mechanism is fixed on the outer frame and connected to the slide plate, and is used to drive the slide plate to slide relative to the outer frame to apply a tensile load to the sample.

[0007] Furthermore, a force sensor is provided on the second fixture, and the force sensor is coaxial with the sample and is used to measure the magnitude of the tensile load applied to the sample.

[0008] Furthermore, the driving mechanism includes a motor and at least one ball screw structure, the ball screw structure includes a screw rod and a nut, the motor is connected to the screw rod, the screw rod is installed on the outer frame, the nut is threadedly connected to the screw rod, and the slide plate is fixedly connected to the nut.

[0009] Furthermore, the driving mechanism includes a belt transmission mechanism and three ball screw structures, the belt transmission mechanism includes a first pulley, a second pulley, a third pulley and a belt, the belt is respectively wound around the first pulley, the second pulley and the third pulley, the motor is connected to the first pulley, and the first pulley, the second pulley and the third belt are each connected to a screw of the ball screw structure.

[0010] Furthermore, it also includes a temperature measuring device, which is used to measure the front temperature of the sample; a thermocouple is provided on the back of the sample, and the thermocouple is used to measure the back temperature of the sample.

[0011] Furthermore, the heating device includes a gas spray gun and an igniter, the nozzle of the gas spray gun is aimed at the front of the sample, and is used to spray gas to the sample; the ignition head of the igniter is close to the front of the sample, and is used to ignite the gas sprayed from the nozzle to form a jet flame.

[0012] Furthermore, the outlet of the nozzle is a long strip-shaped microhole.

[0013] Furthermore, the fuel gas is hydrogen, and the heating device also includes a hydrogen generator, which is connected to the inlet of the gas spray gun through a connecting pipe and is used to generate hydrogen and transport the hydrogen to the gas spray gun; the connecting pipe is provided with a first valve and a first flow meter.

[0014] Furthermore, the powder feeding device includes a powder feeder, a mixer, a powder inlet pipe and a powder outlet pipe. The powder feeder is connected to the mixer via the powder inlet pipe, and the powder outlet pipe is connected to the mixer for providing different powders to the mixer. The mixer is used to mix different powders and transport the mixed powder to the sample via the powder outlet pipe.

[0015] Furthermore, the cooling device includes a cooling gas supply device, an air inlet pipe, a first cooling block and a second cooling block, the two ends of the air inlet pipe are respectively connected to the cooling gas supply device and the first cooling block, the cooling gas supply device is used to transport cooling gas to the first cooling block, the second cooling block is fixed on the first cooling block, the first cooling block is used to guide the cooling gas to the second cooling block, and the second cooling block is used to guide the cooling gas to the back of the sample.

[0016] Furthermore, an air outlet portion is provided on the second cooling block, the air outlet portion is located below the sample, and a plurality of air outlet holes are provided on the air outlet portion.

[0017] Furthermore, the first cooling block has a first guide cavity, the second cooling block has a second guide cavity, the second guide cavity is connected to the first guide cavity, the air outlet is connected to the second guide cavity, and the cooling gas passes through the first guide cavity and the second guide cavity in sequence and is discharged from the air outlet.

[0018] Furthermore, a plurality of guide columns are provided in the first guide cavity.

[0019] Furthermore, the air intake pipe is provided with a second valve and a second flow meter.

[0020] Furthermore, the outer frame is provided with a first side opening and a second side opening, the first side opening and the second side opening lead to the mounting cavity, the first side opening is used for allowing X-rays to pass through to enter the mounting cavity and irradiate the sample, and the second side opening is used for allowing X-rays that penetrate the sample to pass through to leave the mounting cavity. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 Schematic diagram of the structure of a thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to an embodiment of the present invention;

[0022] Figure 2 It is a schematic structural diagram of a stretching instrument of a thermal barrier coating thermal-mechanical coupled-field synchrotron radiation in-situ characterization device according to an embodiment of the present invention, viewed from the top in a first perspective;

[0023] Figure 3It is a schematic structural diagram of a second viewing angle from the top of a tensile tester of a thermal barrier coating thermal coupled field synchrotron radiation in-situ characterization device according to an embodiment of the present invention;

[0024] Figure 4 It is a schematic structural diagram of a tensile tester of a thermal barrier coating thermal coupled field synchrotron radiation in-situ characterization device according to an embodiment of the present invention as viewed from the bottom;

[0025] Figure 5 This is a schematic diagram of the structure of the thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to an embodiment of the present invention after removing the temperature measuring device and the stretching instrument;

[0026] Figure 6 for Figure 5 A magnified view of part I;

[0027] Figure 7 It is a schematic structural diagram of a cooling device of a thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to an embodiment of the present invention;

[0028] Figure 8 It is a schematic structural diagram of a first cooling block and a second cooling block of a cooling device of a device for thermal-mechanical coupled-field synchrotron radiation in-situ characterization of thermal barrier coatings according to an embodiment of the present invention after being connected together;

[0029] Fig. 9 This is a schematic structural diagram of a first cooling block of a cooling device of a thermal barrier coating thermal coupled field synchrotron radiation in-situ characterization device according to an embodiment of the present invention;

[0030] Fig.10 Schematic diagram of the bottom structure of the second cooling block of the cooling device of the thermal barrier coating thermal coupled field synchrotron radiation in-situ characterization device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0031] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings and described in detail.

[0032] like Figure 1As shown, an embodiment of the present invention provides a thermal-mechanical coupled field synchrotron radiation in-situ characterization device for thermal barrier coatings, which includes a base 100, a stretcher 200, a heating device 300, a cooling device 400 and a powder feeding device 500. The stretcher 200, the heating device 300, the cooling device 400 and the powder feeding device 500 are all arranged on the base 100. The stretcher 200 is used to clamp the sample and apply a tensile load to the sample; the heating device 300 is used to heat the sample to make the sample in a high temperature state to simulate the high temperature service environment of the thermal barrier coating; the cooling device 400 is used to cool the back side of the sample to make the back side temperature of the sample lower than the front side temperature, so that the sample has a temperature gradient inside; the powder feeding device 500 is used to provide powder particles to the sample to make the sample in a corrosive state of the powder particles to simulate the corrosive service environment of the thermal barrier coating. The high temperature, thermal gradient, tensile load and corrosion service environment of the thermal barrier coating can be simulated simultaneously by the tensile tester 200, the heating device 300, the cooling device 400 and the powder feeding device 500, which is very close to the actual service environment. Failure experiments of samples in this environment can obtain more realistic (i.e. more accurate) results.

[0033] like Figure 2 , Figure 3 and Figure 4 As shown, the stretching instrument 200 includes an outer frame 210, and the outer frame 210 has an installation cavity 211. A slide plate 220, a first clamp 230, and a second clamp 240 are arranged in the installation cavity 211. The slide plate 220 is slidably connected to the outer frame 210, the first clamp 230 is fixedly connected to the outer frame 210, and the second clamp 240 is fixedly connected to the slide plate 220. The two ends of the sample 600 are respectively fixed to the first clamp 230 and the second clamp 240; the stretching instrument 200 also includes a driving mechanism 250, which is arranged on the outer frame 210 and connected to the slide plate 220, and is used to drive the slide plate 220 to slide relative to the outer frame 210. When the slide plate 220 slides in a direction away from the first clamp 230, the second clamp 240 will also move in a direction away from the first clamp 230, thereby applying a tensile load to the sample 600.

[0034] In some embodiments, a force sensor (not shown) may be provided on the second fixture 240 . The force sensor is coaxial with the sample 600 and is used to measure the magnitude of the tensile load applied to the sample 600 .

[0035] In some embodiments, the driving mechanism 250 may include a motor 251 and at least one ball screw structure, the ball screw structure includes a screw and a nut, the screw is installed on the outer frame 210, the nut is sleeved on the outside of the screw and is threadedly connected to the screw, the motor 251 is connected to the screw directly or through a transmission mechanism to drive the screw to rotate, and the rotation of the screw causes the nut to move linearly along the axial direction of the screw. The nut is fixedly connected to the slide plate 220, so that the slide plate 220 can move along the axial direction of the screw with the nut. Exemplarily, the driving mechanism 250 may include three ball screw structures, and the motor 251 is connected to the screws of the three ball screw structures through a belt transmission mechanism. The belt transmission mechanism includes a first pulley 252, a second pulley 253, a third pulley 254 and an annular belt 255. The belt 255 is respectively wound around the first pulley 252, the second pulley 253 and the third pulley 254. The motor 251 is connected to the first pulley 252 for driving the first pulley 252 to rotate. The rotation of the first pulley 252 causes the second pulley 253 and the third pulley 254 to rotate together through the belt 255. The first pulley 252, the second pulley 253 and the fourth pulley 254 are respectively connected to the screws of their corresponding ball screw structures, so that their respective screws also rotate. The rotation of the screws will cause the corresponding nuts to move linearly, thereby causing the skateboard 220 to slide relative to the outer frame 210. For example, the ball screw structure corresponding to the third pulley 254 includes a screw rod 256 and a nut 257. The screw rod 256 is connected to the third pulley 254, the nut 257 is threadedly connected to the screw rod 256, and the slide plate 220 is fixedly connected to the nut 257. When the third pulley 254 rotates, it can rotate with the screw rod 256, and the rotation of the screw rod 256 causes the nut 257 and the slide plate 220 to move.

[0036] In some embodiments, the thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device may further include a temperature measurement device 700 (such as Figure 1 As shown in FIG. 6 , the temperature measuring device 700 is used to measure the temperature of the front surface of the sample 600. For example, the temperature measuring device 700 may be an infrared thermal imager.

[0037] In some embodiments, a thermocouple (not shown in the figure) may be fixed (eg, welded) on the back side of the sample 600 , and the thermocouple is used to monitor the temperature of the back side of the sample 600 .

[0038] like Figure 5 and Figure 6As shown, in some embodiments, the heating device 300 may include a gas spray gun 310 and an igniter 320, wherein the nozzle 311 of the gas spray gun 310 is aimed at the front of the sample 600, and is used to spray gas to the sample 600; the ignition head 321 of the igniter 320 is close to the front of the sample 600, and is used to ignite the gas sprayed from the nozzle 311 to form a jet flame, and the jet flame directly impacts the front of the sample 600, thereby heating the sample 600 and placing it in a high-temperature environment. The outlet of the nozzle 311 may be a long strip of micropores, so that a high-temperature uniform temperature zone in a wider area can be generated. The igniter 320 may be a pulse igniter, and an electric spark may be formed at its ignition head 321, thereby igniting the gas. The igniter 320 can be connected to the cylinder 330, the cylinder body of the cylinder 330 is fixed on the base 100, and the piston rod of the cylinder 330 is connected to the igniter 320. The igniter 320 can be driven by the cylinder 300 to move relative to the base 100, thereby adjusting the relative position of the ignition head 321 of the igniter 320 and the sample 600.

[0039] In some embodiments, the fuel gas may be hydrogen, and the heating device 300 may further include a hydrogen generator (not shown in the figure), which is connected to the inlet 312 of the gas spray gun 310 through a connecting pipe, and the hydrogen generator is used to generate hydrogen and transport the hydrogen to the gas spray gun 310 so that the gas spray gun 310 sprays the hydrogen. Exemplarily, the hydrogen generator may be configured to generate hydrogen and oxygen by electrolyzing water, and transport the hydrogen and oxygen mixed gas to the gas spray gun 310, and the gas spray gun 310 sprays the hydrogen and oxygen mixed gas together. Since the gas spray gun 310 sprays a mixture of hydrogen and oxygen, it is easier to burn.

[0040] In some embodiments, the powder feeding device 400 may include a powder feeder (not shown in the figure), a mixer 410, a powder inlet pipe 420 and a powder outlet pipe 430. The powder outlet pipe 430 is connected to the mixer 410. The powder feeder is connected to the mixer 410 via the powder inlet pipe 420, and is used to provide different powders to the mixer 410. The mixer 410 is used to mix different powders and transport the mixed powder to the sample 600 via the powder outlet pipe 430 so that it is in a corrosive environment of powder particles. The powder can be powder existing in the actual service environment of the thermal barrier coating, such as CMAS particles (i.e., particles with calcium oxide, magnesium oxide, aluminum oxide and silicon dioxide as the main components), salt spray, etc. The number of powder outlet pipes 430 can be set as needed, for example, one, two, three or more. Figure 6 Two powder outlet pipes 430 are shown, and the two powder outlet pipes 430 are arranged opposite to each other, so that the powder can fully cover the sample 600, making it closer to the actual service environment.

[0041] In some embodiments, the mixer 410 may be fixed on the base 100 via a mixer bracket 440 , that is, the mixer bracket 440 is fixed on the base 100 , and the mixer 410 is fixed on the mixer bracket 440 .

[0042] like Figure 7 As shown, the cooling device 500 includes a cooling gas supply device (not shown in the figure), an air inlet pipe 510, a first cooling block 520 and a second cooling block 530. The two ends of the air inlet pipe 510 are connected to the cooling gas supply device and the first cooling block 520 respectively. The cooling gas supply device can deliver cooling gas to the first cooling block 520 through the air inlet pipe 510. The second cooling block 530 is fixed on the first cooling block 520. The first cooling block 520 can guide the cooling gas to the second cooling block 530. The second cooling block 530 is used to guide the cooling gas to the back of the sample 600, so as to cool the back of the sample 600 by the cooling gas. The larger the flow rate of the cooling gas, the faster the cooling speed, and the lower the temperature of the back of the sample 600. Conversely, the smaller the flow rate of the cooling gas, the slower the cooling speed, and the higher the temperature of the back of the sample 600. Exemplarily, the cooling gas can be compressed air.

[0043] The first cooling block 520 can be fixed on the base 100 through a cooling block bracket 540. The cooling block bracket 540 can be provided with a height-adjustable component, and the first cooling block 520 can be fixed on the component, so that the height of the first cooling block 520 and the second cooling block 530 can be adjusted through the component.

[0044] like Figure 8 As shown, the second cooling block 530 is provided with an air outlet 531, the air outlet 531 is located below the sample 600, and the air outlet 531 is provided with a plurality of air outlet holes 532, and the cooling gas can be output from the air outlet holes 532 and blown on the back of the sample 600, thereby cooling the sample 600. The air outlet holes 532 can be arranged in a matrix on the air outlet 531, so that the gas can be evenly blown on the back of the sample 600 to achieve uniform cooling.

[0045] like Fig. 9 and Fig.10 As shown, the first cooling block 520 has a first guide cavity 521, and the second cooling block 530 has a second guide cavity 533. The second guide cavity 533 is connected to the first guide cavity 521, and the air outlet 532 is connected to the second guide cavity 533. The cooling gas enters the first guide cavity 521 through the air inlet pipe 510, and then enters the second guide cavity 533 through the first guide cavity 521, and is finally discharged to the back of the sample 600 through the air outlet 532.

[0046] In some embodiments, a plurality of guide columns 522 may be provided in the first guide cavity 521 , and the guide columns 522 are used to guide the cooling gas so that the cooling gas discharged from the gas outlet 532 is more uniform.

[0047] The number of air inlet pipes 510 can be set as needed, for example, it can be one, two, three or more, preferably multiple, to provide more cooling gas to the first cooling block 520 and the second cooling block 530 to cool the back of the sample 600 faster.

[0048] The connecting pipe between the gas spray gun 310 and the hydrogen generator may be provided with a first valve and a first flow meter, and the first flow meter is used to measure the flow of the gas. The gas flow delivered to the gas spray gun 310 can be determined by the first flow meter, and the temperature that the front of the sample 600 can reach can be determined according to the gas flow. When the flow reaches a preset value, the first valve can be closed to keep the sample 600 at the preset temperature. In other words, the temperature of the high-temperature environment in which the sample 600 is located can be controlled by the first flow meter and the first valve.

[0049] The air inlet pipe 510 may be provided with a second valve and a second flowmeter, and the second flowmeter is used to measure the flow rate of the cooling gas. The flow rate of the cooling gas delivered to the back of the sample 600 can be determined by the second flowmeter, and the back temperature of the sample 600 is determined by the flow rate of the cooling gas and the front temperature of the sample 600. Therefore, the back temperature of the sample 600 can be controlled by the second flowmeter and the second valve. For example, when the front temperature of the sample 600 is 1100°C, the flow rate of the cooling gas can be controlled to 6SLPM (standard liters per minute); when the front temperature of the sample 600 is 1200°C, the flow rate of the cooling gas can be controlled to 12.5SLPM; when the front temperature of the sample 600 is 1300°C, the flow rate of the cooling gas can be controlled to 21.5SLPM.

[0050] In some embodiments, the in-situ experimental device may also include a control device (not shown in the figure), which is respectively connected to the temperature measuring device 700, the thermocouple, the first valve, the first flow meter, the second valve, and the second flow meter. The control device can obtain the real-time temperature of the front and back of the sample 600 according to the temperature measuring device 700 and the thermocouple, and can obtain the real-time flow of the fuel gas and the cooling gas according to the first flow meter and the second flow meter. The control device can be set to control the opening degree of the first valve and the second valve according to the above-mentioned real-time temperature and the above-mentioned real-time flow, so that the front and back of the sample 600 reach their respective preset temperatures.

[0051] In some embodiments, the outer frame 210 of the stretching instrument 200 is provided with a first side opening 212 (eg, Figure 3 as shown) and a second side opening 213 (as shown Figure 2 As shown in FIG. 2 , the first side opening 212 and the second side opening 213 lead to the mounting cavity 211, so that the X-rays can enter the mounting cavity 211 through the first side opening 212 and irradiate the sample 600, and then leave the mounting cavity 211 from the second side opening 213 after passing through the sample 600, thereby realizing the synchronous X-ray diffraction (i.e., XRD) of the sample 600. XRD measurement needs to be carried out on a synchrotron radiation high-energy diffraction line station, and the base 100 can be placed on the displacement stage of the line station so that the position of the sample 600 can be adjusted by the displacement stage; the energy that can be used is 88.4keV The high-energy X-ray beam enters the mounting cavity 211 from the first side opening 212 and directly penetrates the sample 600. A detector can be placed about 2 meters away from the sample 600 on a path perpendicular to the X-ray. Before starting the XRD test, the height and horizontal position of the detector can be adjusted so that the center of the beam is roughly located at the center of the detector, thereby obtaining a complete sample diffraction ring on the detector. At the same time, the angle of the sample 600 is adjusted by gradually cutting the light using the stage so that its upper surface is parallel to the incident X-ray. During the measurement process, the spot size of the incident X-ray and the height of the sample 600 are accurately adjusted to achieve layer-by-layer scanning of the sample 600 (for example, the step of the translation stage is controlled to be 30um, and line scanning is performed from top to bottom). During high-temperature heating and loading, the coating may expand and creep, causing the center of the sample 600 to deviate from the predetermined position. Therefore, the diffraction information at the predetermined position needs to be obtained by accurately moving the sample center to correct the offset. During the strain measurement process, the YSZ (101) and NiAl (110) diffraction rings were used to calculate the strain, and the e 22 and the outer surface 11 Strain information. The collected diffraction rings at different positions of the coating can be used to analyze the spatially resolved phase structure and strain information of the coating. By continuously performing vertical XRD line scans from the surface of TC to the interface between BC and the substrate, the diffraction information of the coating at different depths and the interface that is most important for coating failure can be collected.

[0052] In some embodiments, the outer frame 210 may also be provided with a top opening and a bottom opening, and the nozzle 311, the ignition head 321 and the powder outlet pipe 430 can enter the installation cavity 211 through the top opening and be located above the sample 600; the base 100 is also provided with an opening connected to the bottom opening of the outer frame 210, and the air inlet pipe 510 can enter the installation cavity 211 through the opening on the base 100 and the bottom opening of the outer frame 210 and be connected to the first cooling block 520.

[0053] In the thermal-mechanical coupled field synchrotron radiation in-situ characterization device for thermal barrier coatings of the embodiment of the present invention, a tensile load can be applied to a sample 600 through a tensile tester 200, the sample 600 can be heated to a high temperature state through a heating device 300, the back of the sample 600 can be cooled through a cooling device 400 to achieve a thermal gradient inside the sample 600, and the sample 600 can be placed in a powder corrosion environment through a powder feeding device 500, so that the environment in which the sample 600 is located is very close to the actual service environment. A failure experiment of the sample in this environment can obtain a result that is more in line with reality (i.e., more accurate); a first side opening 212 and a second side opening 213 for X-rays to pass through are provided on the outer frame 210 of the tensile tester 200, so that the in-situ experimental device can simultaneously realize XRD measurement, that is, XRD measurement is performed on the sample 600 in an environment close to the actual service environment, and the diffraction information of the coating in different depth directions and the interface that is most important for the failure of the coating is obtained.

[0054] The above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. The above embodiment of the present invention can also be modified in various ways. That is, all simple, equivalent changes and modifications made according to the claims and the description of the present invention fall within the scope of protection of the claims of the present invention. The contents not described in detail in the present invention are all conventional technical contents.

Claims

1. A thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device, characterized in that: The invention comprises a base and a tensile tester, a heating device, a cooling device and a powder feeding device arranged on the base. The tensile tester is used to apply a tensile load to a sample. The heating device is used to heat the sample. The cooling device is used to cool the back side of the sample so that the temperature of the back side of the sample is lower than the temperature of the front side of the sample and a temperature gradient is provided inside the sample. The powder feeding device is used to provide powder to the sample so that the sample is in a corroded state of the powder.

2. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 1, characterized in that: The tensile tester includes an outer frame and a driving mechanism. The outer frame has an installation cavity. A slide plate, a first clamp and a second clamp are arranged in the installation cavity. The slide plate is slidably connected to the outer frame, the first clamp is fixedly connected to the outer frame, and the second clamp is fixedly connected to the slide plate. Two ends of the sample are respectively fixed to the first clamp and the second clamp. The driving mechanism is fixed to the outer frame and connected to the slide plate, and is used to drive the slide plate to slide relative to the outer frame to apply a tensile load to the sample.

3. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 2, characterized in that: The second fixture is provided with a force sensor, which is coaxial with the sample and is used to measure the magnitude of the tensile load applied to the sample.

4. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 2, characterized in that: The driving mechanism includes a motor and at least one ball screw structure, the ball screw structure includes a screw rod and a nut, the motor is connected to the screw rod, the screw rod is installed on the outer frame, the nut is threadedly connected to the screw rod, and the slide plate is fixedly connected to the nut.

5. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 4, characterized in that: The driving mechanism includes a belt transmission mechanism and three ball screw structures, the belt transmission mechanism includes a first pulley, a second pulley, a third pulley and a belt, the belt is respectively wound around the first pulley, the second pulley and the third pulley, the motor is connected to the first pulley, and the first pulley, the second pulley and the third belt are each connected to a screw of the ball screw structure.

6. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 1, characterized in that: It also includes a temperature measuring device, which is used to measure the front temperature of the sample; a thermocouple is provided on the back of the sample, which is used to measure the back temperature of the sample.

7. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 1, characterized in that: The heating device includes a gas spray gun and an igniter. The nozzle of the gas spray gun is aimed at the front of the sample and is used to spray gas to the sample. The ignition head of the igniter is close to the front of the sample and is used to ignite the gas sprayed from the nozzle to form a jet flame.

8. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 7, characterized in that: The outlet of the nozzle is a long strip-shaped microhole.

9. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 7, characterized in that: The fuel gas is hydrogen, and the heating device further comprises a hydrogen generator, which is connected to the inlet of the gas spray gun via a connecting pipe and is used to generate hydrogen and transport the hydrogen to the gas spray gun; a first valve and a first flow meter are provided on the connecting pipe.

10. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 1, characterized in that: The powder feeding device includes a powder feeder, a mixer, a powder inlet pipe and a powder outlet pipe. The powder feeder is connected to the mixer via the powder inlet pipe, and the powder outlet pipe is connected to the mixer for providing different powders to the mixer. The mixer is used to mix the different powders and transport the mixed powder to the sample via the powder outlet pipe.

11. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 1, characterized in that: The cooling device includes a cooling gas supply device, an air inlet pipe, a first cooling block and a second cooling block, the two ends of the air inlet pipe are respectively connected to the cooling gas supply device and the first cooling block, the cooling gas supply device is used to transport cooling gas to the first cooling block, the second cooling block is fixed on the first cooling block, the first cooling block is used to guide the cooling gas to the second cooling block, and the second cooling block is used to guide the cooling gas to the back of the sample.

12. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 11, characterized in that: An air outlet portion is provided on the second cooling block, the air outlet portion is located below the sample, and a plurality of air outlet holes are provided on the air outlet portion.

13. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 12, characterized in that: The first cooling block has a first guide cavity, the second cooling block has a second guide cavity, the second guide cavity is connected to the first guide cavity, the air outlet is connected to the second guide cavity, and the cooling gas passes through the first guide cavity and the second guide cavity in sequence and is discharged from the air outlet.

14. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 13, characterized in that: A plurality of guide columns are arranged in the first guide cavity.

15. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 11, characterized in that: The air intake pipe is provided with a second valve and a second flow meter.

16. The thermal barrier coating thermal coupling field synchrotron radiation in-situ characterization device according to claim 2, characterized in that: The outer frame is provided with a first side opening and a second side opening, the first side opening and the second side opening lead to the mounting cavity, the first side opening is used for allowing X-rays to pass through to enter the mounting cavity and irradiate the sample, and the second side opening is used for allowing X-rays that penetrate the sample to pass through to leave the mounting cavity.

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