CN113484020B - Thermal power coupling test device for simulating high-temperature service environment of aircraft engine - Google Patents
Thermal power coupling test device for simulating high-temperature service environment of aircraft engine Download PDFInfo
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- CN113484020B CN113484020B CN202110766353.2A CN202110766353A CN113484020B CN 113484020 B CN113484020 B CN 113484020B CN 202110766353 A CN202110766353 A CN 202110766353A CN 113484020 B CN113484020 B CN 113484020B
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Abstract
The invention discloses a thermodynamic coupling test device for simulating a high-temperature service environment of an aircraft engine, which relates to the technical field of thermal barrier coating service environment test devices and comprises a test bench, wherein a heating component, a cooling component and a force application component for fixing two ends of a workpiece and applying axial force to the workpiece are arranged on the test bench; the workpiece is fixed on the force application assembly, then the heating end of the heating assembly is aligned to the heating surface of the workpiece to be heated, and the cooling port of the cooling assembly is aligned to the cooling surface of the workpiece to be cooled, so that a temperature gradient can be formed between the heating surface and the cooling surface of the workpiece, and meanwhile, the force application assembly is utilized to apply alternating stress to the workpiece, so that the service environment of an actual aircraft engine can be fully simulated, and the accurate failure process of the thermal barrier coating in the high temperature gradient and alternating stress state can be obtained.
Description
Technical Field
The invention relates to the technical field of thermal barrier coating service environment experiment devices, in particular to a thermal power coupling test device for simulating a high-temperature service environment of an aircraft engine.
Background
The aero-engine has been known as "pearl on crown" for a long time, and the development level thereof represents a national comprehensive technological level and national defense strength. The thrust-weight ratio of an aircraft engine is one of important indexes for measuring the performance of the engine, and is closely related to the maneuverability and the economy of an airplane. According to the carnot cycle principle, increasing the turbine front intake air temperature is the most important and feasible way to increase the thrust-to-weight ratio of the engine. At present, three common methods for increasing the front inlet air temperature of the turbine are as follows: develops a novel high-temperature structural material, an air film cooling technology and a thermal barrier coating technology. At present, the development of the traditional single crystal high-temperature alloy and air film cooling technology is close to the limit of materials and processes, and the thermal barrier coating technology and the research and development of novel high-temperature structural materials become more feasible methods for further increasing the temperature before the turbine.
The working environment of the aeroengine is extremely complex and severe, and comprises the effects of more than 20 loads such as high temperature, stress, corrosion environment and the like. Research shows that high-temperature oxidation, ablation, thermal expansion mismatch, particle erosion, corrosive substance erosion and the like are main reasons causing the failure of the thermal barrier coating. The early failure caused by various reasons is a key bottleneck for limiting the application development of the thermal barrier coating and the novel high-temperature structural material, so that an engine service environment simulation platform is established, the failure mechanism of the thermal barrier coating and the high-temperature structural material under various conditions is deeply researched, and the improvement and development of the thermal barrier coating and the high-temperature structural material are necessary.
At present, the work of simulating the service environment of some aircraft engines is carried out at home and abroad, and mainly comprises the simulation of the coating thermal cycle, thermal gradient, corrosion environment, thermal, mechanical and environmental coupling environment and the like. The invention patent with the application number of '201510033169.1' and the name of 'thermal barrier coating thermal shock life evaluation test device' provides a thermal shock test device of a thermal barrier coating of an oxygen propane gas heating gun in a high-temperature, thermal gradient and CMAS coupling service environment; the invention has the application number of ' 200610024973.4 ', and is named as a thermal barrier coating thermal shock resistance testing device ', the heat source mounting system can be provided with different heat sources, different heating temperature ranges can be generated by adjusting the distance between the heat sources and a sample, meanwhile, the cooling medium input port is fixed at the lower part of the bracket, and different cooling media can be externally connected to cool the sample, so as to realize the circulating heating of the sample. However, the devices do not form a temperature gradient in the sample, so that the simulated working environment is far from the actual working environment of the aeroengine, and the failure process of the thermal barrier coating is inaccurate.
Therefore, the complex thermal coupling simulation device capable of realizing the high temperature gradient and alternating stress state is provided, and has scientific significance and engineering significance for deeply researching the failure mechanism of the thermal barrier coating and the novel high-temperature structural material.
Disclosure of Invention
The invention aims to provide a thermal power coupling test device for simulating a high-temperature service environment of an aircraft engine, which is used for solving the problems in the prior art, can fully simulate the service environment of the actual aircraft engine, and obtains the change failure process of a thermal barrier coating in the high-temperature gradient and alternating stress state, so that the failure analysis of the thermal barrier coating is more accurate.
In order to achieve the purpose, the invention provides the following scheme: the invention provides a thermal power coupling test device for simulating a high-temperature service environment of an aircraft engine, which comprises a test bench, wherein a heating component, a cooling component and a force application component for fixing two ends of a workpiece and applying axial force to the workpiece are arranged on the test bench, the workpiece comprises a heating surface and a cooling surface, the heating component is used for heating the heating surface of the workpiece, and the cooling component is used for cooling the cooling surface.
Preferably, a heat insulation plate for preventing the force application assembly from being heated is arranged between the heating assembly and the force application assembly, a notch is formed in the heat insulation plate, and heating flame of the heating assembly penetrates through the notch to heat the heating surface of the workpiece.
Preferably, the notch is provided with two blocking pieces in a sliding manner, and the size of the notch is adjusted by changing the relative positions of the two blocking pieces.
Preferably, the heat insulation plate is internally provided with a cavity, two ends of the heat insulation plate are respectively provided with an inlet and an outlet which are communicated with the cavity, the inlet is communicated with a medium supply part in the cooling assembly, the outlet is communicated with a pipeline, and the medium acts on a cooling surface of the workpiece through the pipeline.
Preferably, the medium supply part is an air pump.
Preferably, a movable baffle is arranged on the experiment table and can move to a position between the heating end head and the notch to shield the notch.
Preferably, the movable baffle is rotatably fixed at the bottom of the heat insulation plate.
Preferably, a first sliding table and a second sliding table are also vertically arranged on the experiment table, the heating assembly comprises a base and a heating main body arranged on the base in a sliding manner, the base is arranged on the first sliding table in a sliding manner, and the sliding direction of the heating main body is perpendicular to that of the base; the second slides and still is provided with vertical track on the platform, the application of force subassembly slides and sets up on the vertical track.
Preferably, the heating assembly is a plasma heater.
The invention provides a thermodynamic coupling test method for simulating a high-temperature service environment of an aircraft engine, which comprises the following steps of:
1) fixing the workpiece on the force application assembly, adjusting the size of the notch on the heat insulation plate according to the size of the workpiece, and adjusting the positions of the heating assembly and the force application assembly to enable the heating end, the notch and the workpiece to be on the same straight line;
2) starting the heating assembly to heat the workpiece, cooling the workpiece by using the first ventilation pipeline or the second ventilation pipeline to form a temperature gradient inside the workpiece, applying axial force to the workpiece by using the force application assembly, and respectively measuring tension and temperature gradient distribution conditions of the workpiece by using the tension sensor and the thermocouple;
3) when the heating time reaches a set value, the force application assembly releases force, and meanwhile, the movable baffle plate rotates upwards to a position between the notch and the heating end head to block heating flame, and meanwhile, the workpiece is cooled by the first ventilation pipeline and the second ventilation pipeline;
4) after the workpiece is cooled to room temperature, the movable baffle rotates downwards, the movable baffle is withdrawn from the front of the notch, and the heating end head performs the next heating period on the workpiece.
Compared with the prior art, the invention achieves the following technical effects:
1. according to the invention, a workpiece is fixed on the force application assembly, then the heating end of the heating assembly is aligned to the heating surface of the workpiece to be heated, and the cooling port of the cooling assembly is aligned to the cooling surface of the workpiece to be cooled, so that a temperature gradient can be formed between the heating surface and the cooling surface of the workpiece, and meanwhile, the force application assembly is utilized to apply alternating stress to the workpiece, so that the service environment of an actual aero-engine can be fully simulated, the change failure process of the thermal barrier coating in the high temperature gradient and alternating stress state is obtained, and the failure process analysis of the thermal barrier coating is more accurate;
2. the heat insulation plate is provided with the cavity, and in the experiment, the cooling medium is firstly introduced into the heat insulation plate for heating and then is used as the cooling surface of the workpiece to simulate the cooling temperature of the actual cooling surface of the aircraft engine, so that more real temperature gradient distribution is formed, and the accuracy of the experiment result is facilitated;
3. the movable baffle is arranged, so that the workpiece can be cooled without extinguishing fire, and when the next heating period is carried out, the workpiece can be rapidly heated, thereby not only avoiding the influence of repeated flameout on the service life of the heating assembly, but also obviously improving the heating efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of a heating assembly;
FIG. 3 is a schematic view of the construction of the heat shield;
FIG. 4 is a schematic view of the back side structure of the heat shield
Wherein, 1, a laboratory bench; 2. a heating assembly; 3. a cooling assembly; 4. a force application assembly; 5. a workpiece; 6. a heat insulation plate; 7. a notch; 8. a baffle plate; 9. a movable baffle; 10. a first sliding table; 11. a second sliding table; 12. a vertical track; 13. a crawler belt.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a thermal power coupling test device for simulating a high-temperature service environment of an aircraft engine, which is used for solving the problems in the prior art, can fully simulate the service environment of the actual aircraft engine, obtains the change process of a thermal barrier coating in the high-temperature gradient and alternating stress state, and is more accurate in analysis of the change process of the thermal barrier coating.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1:
as shown in fig. 1-2, the present embodiment provides a thermal-power coupling test device for simulating a high-temperature service environment of an aircraft engine, which includes a test bench 1, wherein the test bench 1 is provided with a heating assembly 2, a cooling assembly 3, and a force application assembly 4 for fixing two ends of a workpiece 5 and applying an axial force to the workpiece 5, the workpiece 5 includes a heating surface and a cooling surface, the heating assembly 2 is used for heating the heating surface of the workpiece 5, and the cooling assembly 3 is used for cooling the cooling surface.
In the experimental process, firstly, two ends of a workpiece 5 are fixed on a force application component 4, heating parameters of the heating component 2 for the workpiece 5 are set, then a heating end of the heating component 2 is aligned with a heating surface of the workpiece 5 for heating, a cooling port of a cooling component 3 is aligned with a cooling surface of the workpiece 5 for cooling, so that a temperature gradient is formed between the heating surface and the cooling surface of the workpiece 5, alternating stress is applied to the workpiece 5 by using the force application component 4 according to a set program while the workpiece 5 is heated, the simulation of high-temperature, high-heat-flow-density, gradient temperature and thermal coupling service environment is realized, the failure process of the thermal barrier coating in the high-temperature-gradient and alternating stress state can be obtained through the detection of the workpiece, and the failure analysis of the thermal barrier coating in the real service environment process is more accurate.
It should be noted that, the workpiece 5 in this embodiment may be generally selected to be a sheet or a cylinder, the structure of the cylinder is more similar to that of an actual aero-engine blade, the forming mechanism of the formed temperature gradient and the actual temperature gradient is also closer, the manufacturing process of the sheet structure is simpler, and the failure process of the thermal barrier coating in the simulated service environment can also be obtained; when the workpiece 5 is in a sheet shape or a sheet shape, one side surface of the workpiece is coated with a thermal barrier coating, the side surface is a heating surface, the other side surface is a metal matrix surface, the side surface is a cooling surface, and at the moment, a cooling port in the cooling component 3 directly acts a cooling medium on the metal matrix surface to cool the metal matrix surface; when the workpiece 5 is in a columnar shape, in order to fully simulate the structure of an aircraft engine blade, a cavity is arranged inside the workpiece 5, the outer surface of the workpiece 5 is coated with a thermal barrier coating, the surface is a heating surface, the inner surface (namely the wall surface of the cavity) is the surface of a metal matrix, the surface is a cooling surface, at the moment, a cooling port in the cooling assembly 3 introduces a cooling medium into the cavity to cool the surface of the metal matrix, and preferably, cooling pipelines in the cooling assembly 3 are connected to two ends of the workpiece 5 and are communicated with the inner cavity of the workpiece. Therefore, in order to fit workpieces 5 of different shapes, the cooling module 3 in this embodiment may be provided with two sets of cooling pipes at the same time, wherein one set of cooling pipes is used to connect two ends of the cylindrical workpiece 5, the ports of the other set of cooling pipes are directly aligned with the surface of the metal substrate of the sheet-shaped workpiece 5, and valves are provided on both sets of cooling pipes, and when in use, the corresponding cooling pipes are selected to be cooled according to the shape of the workpiece 5.
In the embodiment, the heating component 2 can adopt a common plasma heater, the heating temperature is high, the temperature of the workpiece 5 can reach more than 1000 ℃, and the heating speed is obviously higher compared with the existing flame heater; and the plasma heater can perform thermal cycle simulation under a certain temperature heating gradient condition, such as the target temperature of the workpiece 5 of 1200 ℃, the first section: the temperature is between room temperature and 800 ℃, and the adjustment is carried out at a high speed, so that large overshoot is allowed; and a second stage: 800-1100 ℃, adjusted at a moderate speed, allowing a small overshoot; a third stage: 1100 ℃ -1200 ℃, and low speed adjustment is adopted, so that extremely small overshoot is allowed; the structure of the plasma heater or other heating devices is well known to those skilled in the art, and the detailed structure of the plasma heater is not described in this embodiment; similarly, the cooling module 3 is also a common module in the art.
The skilled person should know that, this embodiment is further provided with a detection system, the detection system includes an infrared thermometer, an infrared thermal imager, a CCD camera, etc., the infrared thermometer can detect the surface temperature change of the material in real time, the infrared thermal imager can know the change of the internal structure of the material through the analysis of the material temperature field, the CCD camera is mainly used for detecting the surface topography change of the material, and several online detection devices cooperate to help the worker to master the surface topography of the workpiece and the change of the internal structure in the thermal coupling service environment in real time. The infrared thermometer, the infrared thermal imager, the CCD camera, etc. are all common detection devices in the art, and the using method and the fixing manner on the experiment table 1 are well known to those skilled in the art, so the embodiment is not particularly limited to this, and the detection device is not limited to the above-mentioned devices.
In the experimental process, the surface temperature of the workpiece 5 does not need to be guaranteed to be uniform, for example, when the workpiece 5 is in a sheet shape, the surface temperature of the heating surface and the temperature gradient between the heating surface and the cooling surface are relatively uniform, but when the workpiece 5 is in a columnar shape, the temperature of the cylindrical surface facing the heating assembly 2 is relatively high, and the temperature of the cylindrical surface on the other side is relatively low.
In this embodiment, the force application assembly 4 can select a tensile machine, and can provide axial tension or pressure to the workpiece 5 according to experimental requirements, and a fixture for fixing the workpiece 5 on the tensile machine is provided with a stress sensor for measuring the stress of the workpiece 5, and the fixture is a water-cooled fixture, and has a circulating cooling water loop inside to prevent the fixture from overheating, and the circulating cooling water loop of the fixture and the cooling loop of the cooling assembly are independent from each other.
Since the heating temperature of the heating assembly 2 is high, in order to prevent the force application assembly 4 from being affected by the heating of the heating assembly 2, and also in order to prevent the flame of the heating surface and the cooling medium of the cooling surface from interfering with each other when the workpiece 5 is in a sheet structure, in this embodiment, a heat insulation plate 6 is disposed between the heating assembly 2 and the force application assembly 4, and in order to heat the workpiece 5 smoothly by the heating assembly 2, a notch 7 is disposed on the heat insulation plate 6, and the heating flame of the heating assembly 2 penetrates through the notch 7 to heat the heating surface of the workpiece 5, as shown in fig. 3 to 4. It should be understood by those skilled in the art that the heat insulating plate 6 mainly shields the heating flame, so that the heating flame can only penetrate through the notch 7 to heat the workpiece 5, thereby reducing the heating effect of the heating assembly 2 on the force application assembly 4, avoiding overheating of the force application assembly 4, causing large pressure to the water cooling of the members such as the clamp, etc., and simultaneously being not beneficial to the service life of the force application assembly 4, but the heat insulating plate 6 cannot completely avoid the temperature rise of the force application assembly 4.
In order to adapt to workpieces 5 with different sizes, the two blocking pieces 8 are arranged at the notch 7 in a sliding mode, and the size of the notch 7 can be changed by changing the relative positions of the two blocking pieces 8.
In the embodiment, a cavity is arranged in the heat insulating plate 6, an inlet and an outlet which are communicated with the cavity are respectively arranged at two ends of the heat insulating plate 6, the inlet is communicated with a medium supply part in the cooling assembly 3, the outlet is communicated with a pipeline, in the cooling process, a cooling medium is introduced into the cavity of the heat insulating plate 6, the heat insulating plate 6 directly faces the heating assembly 2, the temperature of the cooling medium can rise under the action of the heating assembly 2, and then the cooling medium is discharged and acts on a cooling surface of the workpiece 5 under the action of the pipeline; the reason why the cooling medium is firstly introduced into the heat insulation plate 6 is that in the actual service environment of the aircraft engine, the medium entering the cavity of the engine blade is obviously higher than the room temperature and can usually reach about 200 ℃, so that the requirement of fully simulating the service environment of the aircraft engine cannot be met by adopting room-temperature gas or liquid, and the cooling medium is firstly introduced into the heat insulation plate 6 for heating, so that the service environment of the aircraft engine can be fully simulated, more real temperature gradient distribution is formed, and the accuracy of an experimental result is facilitated; the connection of the inlet and outlet openings of the heat shield 6 to the cooling module 3 is well known to those skilled in the art and is therefore not shown in the drawings.
Specifically, in the present embodiment, the medium supply portion is an air pump, and the cooling circulation medium is air.
Further, in this embodiment, the experiment table 1 is provided with a movable baffle 9, and the movable baffle 9 can move to a position between the heating end and the notch 7 to shield the notch 7; therefore, after a heating cycle of the workpiece 5 is completed, the notch 7 is shielded by the movable baffle 9, the heating assembly 2 can be stopped from heating the workpiece 5, at the moment, the workpiece 5 can be cooled to prepare for the next heating cycle, the ignition process of the heating assembly 2 is usually complicated, repeated flameout and ignition can reduce the service life of the heating assembly 2, the workpiece 5 can be cooled without flameout by arranging the movable baffle 9, and the workpiece 5 can be rapidly heated when the next heating cycle is performed, so that the influence of repeated flameout on the service life of the heating assembly 2 is avoided, and the heating efficiency can be obviously improved; specifically, the movable baffle 9 is fixed at the bottom of the heat insulation board 6 in a rotating way in the embodiment.
It should be noted that, in this embodiment, a cooling device for the workpiece 5 after heating is not limited, and the cooling device may be a cooling assembly 3 for generating a temperature gradient, and after heating is completed, under the shielding effect of the movable baffle 9 on the heating flame, the temperature of the cooling medium introduced into the heat insulation plate 6 is not significantly increased, and the cooling assembly 3 may be used for cooling the workpiece 5; moreover, other cooling pipelines may be disposed on the cooling module 3 to cool the workpiece 5, which is well known to those skilled in the art, and the embodiment is not limited thereto.
In order to facilitate alignment and adjustment of the positions of the heating assembly 2 and the workpiece 5, in this embodiment, a first sliding table 10 and a second sliding table 11 are further vertically arranged on the experiment table 1, the heating assembly 2 includes a base and a heating body slidably arranged on the base, the base is slidably arranged on the first sliding table 10, and the sliding direction of the heating body is perpendicular to the sliding direction of the base; still be provided with vertical track 12 on the second platform 11 that slides, application of force subassembly 4 slides and sets up on vertical track 12, and heating element 2 and its application of force subassembly 4 all include a plurality of circuits, pipeline simultaneously, and the pipeline of this embodiment with heating element 2, application of force subassembly 4, the circuit all sets up in track 13, prevents that it from producing the interference to heating element 2, application of force subassembly 4's removal. The first sliding table 10 and the second sliding table 11 each include a high-precision screw rod and a servo motor, and the specific structure thereof is well known to those skilled in the art.
Example 2:
the embodiment provides a thermal power coupling test method for simulating a high-temperature service environment of an aircraft engine, which comprises the following steps:
1) fixing a workpiece 5 on a force application component 4, adjusting the size of a notch 7 on a heat insulation plate 6 according to the size of the workpiece 5, and adjusting the positions of a heating component 2 and the force application component 4 to enable a heating end, the notch 7 and the workpiece 5 to be on the same straight line;
2) starting the heating assembly 2, heating the workpiece 5, cooling the workpiece 5 by using the first ventilation pipeline or the second ventilation pipeline simultaneously, forming a temperature gradient in the workpiece 5, applying an axial force to the workpiece 5 by using the force application assembly 4, and measuring the tension and the temperature gradient distribution condition of the workpiece 5 by using the tension sensor and the thermocouple respectively;
3) when the heating time reaches a set value, the force application assembly 4 releases force, and meanwhile, the movable baffle 9 rotates upwards to a position between the notch 7 and the heating end to block heating flame, and meanwhile, the workpiece 5 is cooled by using the first ventilation pipeline and the second ventilation pipeline;
4) after the workpiece 5 is cooled to room temperature, the movable baffle 9 rotates downwards, the workpiece is withdrawn from the front of the notch 7, and the heating end head carries out the next heating period on the workpiece 5.
The adaptation according to the actual needs is within the scope of the invention.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. A thermal power coupling test device for simulating a high-temperature service environment of an aircraft engine is characterized by comprising a test bench, wherein a heating assembly, a cooling assembly and a force application assembly for fixing two ends of a workpiece and applying axial force to the workpiece are arranged on the test bench, the workpiece comprises a heating surface and a cooling surface, the heating assembly is used for heating the heating surface of the workpiece, and the cooling assembly is used for cooling the cooling surface;
a heat insulation plate for preventing the force application assembly from being heated is arranged between the heating assembly and the force application assembly, a notch is formed in the heat insulation plate, and heating flame of the heating assembly penetrates through the notch to heat a heating surface of a workpiece; the notch is provided with two blocking pieces in a sliding manner, and the size of the notch is adjusted by changing the relative positions of the two blocking pieces;
the heat insulation plate is internally provided with a cavity, the two ends of the heat insulation plate are respectively provided with an inlet and an outlet which are communicated with the cavity, the inlet is communicated with a medium supply part in the cooling assembly, the outlet is communicated with a pipeline, and a medium acts on a cooling surface of a workpiece through the pipeline.
2. The device for simulating a thermodynamic coupling test in an aircraft engine high temperature service environment according to claim 1, wherein the medium supply part is an air pump.
3. The device for simulating the thermodynamic coupling test of the high-temperature service environment of the aircraft engine according to claim 1 or 2, wherein a movable baffle is arranged on the test bench and can move to a position between the heating end and the notch to shield the notch.
4. The device for simulating a thermodynamic coupling test in an aircraft engine high-temperature service environment according to claim 3, wherein the movable baffle is rotatably fixed at the bottom of the heat insulation plate.
5. The device for simulating a thermodynamic coupling test in an aircraft engine high-temperature service environment according to claim 1, wherein a first sliding table and a second sliding table are further disposed on the test bench perpendicularly to each other, the heating assembly includes a base and a heating body slidably disposed on the base, the base is slidably disposed on the first sliding table, and a sliding direction of the heating body is perpendicular to a sliding direction of the base; the second slides and still is provided with vertical track on the platform, the application of force subassembly slides and sets up on the vertical track.
6. The device for simulating a thermodynamic coupling test in an aircraft engine high temperature service environment according to claim 1, wherein the heating component is a plasma heater.
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| CN100456014C (en) * | 2006-03-23 | 2009-01-28 | 上海交通大学 | Measuring device for heat-barrier coating heat-shock resisting performance |
| CN103091189B (en) * | 2013-01-10 | 2014-09-24 | 湘潭大学 | Tester for simulating service environment of thermal barrier coating and detecting failure of thermal barrier coating in real time |
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