Thermal barrier coating testing device and method with cooling gas circuit and combined double-high-temperature box

Abstract

The invention discloses a double-high-temperature-box combined thermal barrier coating test device and method with a cooling gas circuit, and the device comprises a first high-temperature test box which is used for generating high-temperature cooling gas required by a test in the first high-temperature test box; the second high-temperature test box is used for generating high-temperature fuel gas required by the test in the second high-temperature test box; the gas path communication system is used for conveying cooling gas into the test piece in the second high-temperature test box through the test loading platform according to test requirements; the air pressure balancing device is used for keeping dynamic balance of air pressure in the first high-temperature test box and the second high-temperature test box; and the test loading platform is mounted in the second high-temperature test box and is used for mounting a test piece with a thermal barrier coating. According to the invention, a high-temperature gas and cooling gas environment is simulated through the combination of the two high-temperature boxes, and the actual working environment of the turbine blade in a gas turbine is restored more truly, so that the accuracy and reliability of the thermal barrier coating test are improved, and the deviation of the performance of the thermal barrier coating under the real working condition is reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal barrier coating testing, and in particular relates to a thermal barrier coating testing device and method combined with a double high-temperature box having a cooling air path. Background Art

[0002] Gas turbines are a new generation of power plants, following steam and internal combustion engines. Advanced gas turbine technology is a measure of a country's industrial prowess and capabilities. Based on the Brayton cycle principle employed by gas turbines, increasing the turbine inlet temperature can improve power and thermal efficiency. However, simply increasing the initial gas temperature can lead to degradation of turbine blade performance and shortened lifespan. Thermal barrier coatings (TBCs), a key thermal protection technology for turbine blades, utilize high-temperature, corrosion-resistant, and highly insulating ceramic materials sprayed onto the surface of a base alloy to enhance the alloy's resistance to high-temperature oxidative corrosion. Current experimental research methods for TBCs primarily utilize sintering, oxidation, and thermal cycling / thermal shock testing in high-temperature chambers to investigate the coating's material evolution and failure degradation.

[0003] Because the current experimental research on thermal barrier coatings uses a high-temperature box that is only a single heating and insulation device and cannot be used for the actual working environment of turbine blades (with film cooling technology and internal and external temperature gradients), the final test results deviate from the thermal barrier coating under the final actual working conditions. Summary of the Invention

[0004] The purpose of the present invention is to address the shortcomings of the above-mentioned background technology and provide a thermal barrier coating test device and method combined with a dual high-temperature box with a cooling air path, which can simulate the dynamic temperature difference on both sides of the thermal barrier coating and accurately test its performance.

[0005] The technical solution adopted by the present invention is: a thermal barrier coating test device combined with a double high temperature box with a cooling gas path, comprising

[0006] A first high-temperature test chamber is used to generate high-temperature cooling gas required for the test internally;

[0007] The second high-temperature test chamber is used to generate high-temperature gas required for the test internally;

[0008] An air communication system is connected between the first high-temperature test chamber and the second high-temperature test chamber, and is used to deliver cooling gas to the interior of the test piece in the second high-temperature test chamber through the test loading platform according to test requirements;

[0009] An air pressure balancing device is installed in the first high temperature test chamber and the second high temperature test chamber, and is used to maintain a dynamic balance of air pressure in the first high temperature test chamber and the second high temperature test chamber;

[0010] The test loading platform is installed in the second high-temperature test chamber and is used to install test pieces with thermal barrier coatings.

[0011] Furthermore, the first high-temperature test box includes a first box door and a first box body, the first box door is provided with a first through hole and a second through hole, the first through hole is connected to the air path communication system, the air pressure balancing device is installed in the second through hole, and a heating system is provided in the first box body.

[0012] Furthermore, the second high-temperature test box includes a second box door and a second box body, the second box door is provided with a third through hole and a fourth through hole, the test loading platform is installed in the third through hole, the air pressure balance device is installed in the fourth through hole, and a heating system is provided in the second box body.

[0013] Furthermore, the gas path connection system includes an gas path pipeline and an gas path control valve arranged on the gas path pipeline. One end of the gas path pipeline is connected to the interior of the first high-temperature test box, and the other end is connected to the interior of the test loading platform in the second high-temperature test box. The gas path control valve is internally provided with an air pump, a flow control valve and a temperature compensation module. The air pump is used to transport the cooling gas to the interior of the test piece in the second high-temperature test box through the gas path pipeline. The flow control valve is used to control the flow rate of the cooling gas. The temperature compensation module is used to compensate for the heat loss during the transmission of the cooling gas.

[0014] Furthermore, the air pressure balancing device is installed on the doors of the first high temperature test box and the second high temperature test box, and one end of the air pressure balancing device is connected to the outside of the test box, and the other end is connected to the inside of the test box.

[0015] Furthermore, the air pressure balancing device includes a coaxially arranged ventilation pipe and a ventilation pipe opening, the end of the ventilation pipe away from the ventilation pipe opening is connected to the outside of the test box, and the end of the ventilation pipe opening away from the ventilation pipe is connected to the inside of the test box, the length of the ventilation pipe is greater than the length of the ventilation pipe opening, and the diameter of the ventilation pipe is smaller than the diameter of the ventilation pipe opening.

[0016] Furthermore, the test loading platform includes a conducting pipe, a clamping interface and an installation platform. The conducting pipe and the clamping interface are both installed on the second door of the second high-temperature test chamber. One end of the conducting pipe is connected to the air path communication system and the other end is connected to the clamping interface. The installation platform is fixed on the clamping interface and is located inside the second high-temperature test chamber. The installation platform is used to install test pieces with thermal barrier coatings.

[0017] Further, the installation platform includes a first platform, which includes a first clamping plate, a connecting plate, and a second clamping plate. The first clamping plate, the connecting plate, and the second clamping plate are connected in sequence to form a U-shaped structure for installing the vane test piece. Cold air channels communicating with the air film holes on the test piece and pin holes connected to the pin shafts on the test piece are provided on both the first clamping plate and the second clamping plate.

[0018] Furthermore, the installation platform includes a second platform, which includes four connecting flat plates. The four connecting flat plates are connected in sequence to form a square structure for installing the flat test piece.

[0019] A test method for the above-mentioned thermal barrier coating test device with a combined double high-temperature box with a cooling gas path includes the following steps:

【说明:原文本中

[0020] 处无具体内容,翻译时保留原标签】

[0020] Arrange a number of temperature detection modules and stress detection modules on the test piece;

[0021] Install the test piece on the test loading platform;

[0022] Start the heating systems of the first high-temperature test box and the second high-temperature test box to heat the internal gases to the set temperatures respectively;

[0023] Start the gas path connection system to transport the high-temperature cooling gas in the first high-temperature test box to the inside of the test piece in the second high-temperature test box;

[0024] Simulate the high-temperature gas environment during the operation of the test piece through high-temperature gas and simulate the cooling gas environment during the operation of the test piece through high-temperature cooling gas to test the thermal barrier coating on the surface of the test piece;

[0025] Analyze the performance of the thermal barrier coating based on the data detected by the temperature detection module and the stress detection module.

[0026] The beneficial effects of the present invention are as follows:

[0027] The present invention combines a double high-temperature box to simulate the high-temperature gas and cooling gas environments, more realistically restoring the actual working environment of the turbine blade in the gas turbine, thereby improving the accuracy and reliability of the thermal barrier coating test and reducing the deviation of the thermal barrier coating performance under real working conditions.

[0028] The gas path connection system of the present invention can accurately control the transportation of the cooling gas, including flow rate and temperature compensation, ensuring that the cooling gas can reach the inside of the test piece stably and accurately, further simulating the cooling effect in actual operation and improving the accuracy of the test.

[0029] The air pressure balancing device of the present invention can maintain a dynamic balance of air pressure in two high-temperature test chambers, prevent test errors caused by air pressure differences, and ensure the stability and accuracy of the test; through the coaxial arrangement of the ventilation pipe and ventilation pipe opening, as well as the specific length and diameter design, the air pressure balancing device can more effectively regulate the air pressure while reducing the impact of external interference on the test.

[0030] The design of the test loading platform of the present invention facilitates the installation and removal of test pieces while ensuring smooth access of cooling gas to the test pieces, improving the convenience and efficiency of testing. The mounting platform designed for blade-type test pieces more accurately simulates the actual operating conditions of turbine blades, including the effects of film cooling, thereby enhancing the relevance and accuracy of the test. Another mounting platform, suitable for flat-plate test pieces, increases the versatility and flexibility of the test apparatus, meeting the needs of different test pieces.

[0031] The design of the first high-temperature test chamber of the present invention enables the cooling gas to be heated to a set temperature therein and transported to the second high-temperature test chamber through the gas path connection system, providing a stable source of cooling gas for the test; the design of the second high-temperature test chamber enables the high-temperature fuel gas and cooling gas to act on the test piece simultaneously, simulating the actual working environment of the turbine blades in the gas turbine, and providing more realistic conditions for testing the performance of thermal barrier coatings.

[0032] By arranging temperature detection modules and stress detection modules, the present invention can monitor the performance changes of thermal barrier coatings in real time during the test, providing accurate data support for the research and optimization of thermal barrier coatings. At the same time, the method can more realistically simulate the actual working environment of turbine blades, improving the accuracy and reliability of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 Schematic diagram of heat transfer on the surface of turbine blades when no air film cooling technology is used.

[0034] Figure 2 Schematic diagram of heat exchange on the surface of turbine blades when film cooling technology is used.

[0035] Figure 3 It is a schematic diagram of the structural principle of the present invention.

[0036] Figure 4 Schematic diagram of the interior of the second high temperature test chamber of the present invention.

[0037] Figure 5 It is a schematic diagram of the internal principle of the gas circuit control valve of the present invention.

[0038] Figure 6 Schematic diagram of the air pressure balancing device of the present invention.

[0039] Figure 7 It is a partial schematic diagram of the test loading platform of the present invention.

[0040] Figure 8 This is a schematic diagram of installing a blade-type test piece on the first platform of the present invention.

[0041] Figure 9 It is a partial cross-sectional view of a blade-type test piece installed on the first platform of the present invention.

[0042] Figure 10 Schematic diagram of the blade-type test piece of the present invention.

[0043] Figure 11 Schematic diagram of the flow of cooling gas inside the blade-type test piece of the present invention.

[0044] Figure 12 This is a schematic diagram of installing a flat test piece on the second platform of the present invention.

[0045] Figure 13 Schematic diagram of the flow of cooling gas inside the flat test piece of the present invention.

[0046] In the figure, 1-first high-temperature test chamber; 1.1-first chamber door; 1.2-first chamber body; 1.3-first through hole; 1.4-second through hole; 2-second high-temperature test chamber; 2.1-second chamber door; 2.2-second chamber body; 2.3-third through hole; 2.4-fourth through hole; 3-air path connection system; 3.1-air path pipeline; 3.2-air path control valve; 3.3-air pump; 3.4-flow control valve; 3.5-temperature compensation module; 4-air pressure balancing device; 4.1-ventilation pipeline; 4.2-ventilation pipe opening ;5-test loading platform; 5.1-conducting pipeline; 5.2-clamping interface; 5.3-first platform; 5.31-first clamping plate; 5.32-connecting plate; 5.33-second clamping plate; 5.34-cold air channel; 5.35-pin hole; 5.36-transition cavity; 5.4-second platform; 5.41-connecting plate; 6-blade type test piece; 6.1-cooling cavity; 6.2-first air film hole; 6.3-pin shaft; 6.4-temperature detection module; 7-flat plate test piece; 7.1-second air film hole. DETAILED DESCRIPTION

[0047] The following is a further description of specific embodiments of the present invention in conjunction with the accompanying drawings. It should be noted that the description of these embodiments is intended to facilitate understanding of the present invention and does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0048] Figure 1 、 Figure 2The following are schematic diagrams of heat transfer on the surface of turbine blades with and without film cooling technology. It can be seen from the figure that the heat transfer effect of the blade surface with film hole cooling technology is significantly stronger than that without film cooling technology.

[0049] Cooling efficiency is an important evaluation index of film cooling technology and is defined as follows:

[0050]

[0051] Where T g , h0 is the mainstream gas temperature and mainstream heat exchange intensity, T w is the leaf temperature, T c is the cooling gas temperature, T aw is the adiabatic wall temperature (the temperature of the air flow after the mainstream air and the cold air are mixed), and h is its heat transfer intensity.

[0052] The theoretical basis for the operation of the thermal barrier coating test device of the present invention, which is combined with a dual high-temperature box and a cooling air path, is that the film cooling efficiency is similar to that of actual turbine blades, thereby simulating the actual working conditions and conducting experimental research on thermal barrier coatings. The implementation plan of the test device is as follows: Figure 3-13 Shown, including

[0053] The first high temperature test chamber 1 is used to generate high temperature cooling gas required for the test inside;

[0054] The second high temperature test chamber 2 is used to generate high temperature gas required for the test inside;

[0055] The gas communication system 3 is connected between the first high-temperature test chamber 1 and the second high-temperature test chamber 2 and is used to deliver cooling gas to the interior of the test piece in the second high-temperature test chamber 2 through the test loading platform 5 according to test requirements;

[0056] The air pressure balancing device 4 is installed in the first high temperature test chamber 1 and the second high temperature test chamber 2, and is used to maintain the dynamic balance of the air pressure in the first high temperature test chamber 1 and the second high temperature test chamber 2;

[0057] A test loading platform 5 is installed in the second high-temperature test chamber 2 and is used to install a test piece with a thermal barrier coating;

[0058] The control module is electrically connected to the corresponding controlled components inside the first high-temperature test chamber, the second high-temperature test chamber and the gas path connection system, and is used to control the corresponding equipment parameters. The control module can be an independently set control system or a control device that comes with the corresponding test chamber and the gas path connection system (therefore not shown in the figure).

[0059] The present invention combines two high-temperature chambers and cooperates with an air path connection system, an air pressure balancing device and a test loading platform to simulate high-temperature fuel gas and cooling gas environments, more realistically restoring the actual working environment of turbine blades in a gas turbine, thereby improving the accuracy and reliability of thermal barrier coating tests and reducing deviations from thermal barrier coating performance under actual working conditions.

[0060] In some embodiments, the first and second high-temperature test chambers 1 and 2 are essentially identical in structure, differing in that the test specimen is mounted in the second high-temperature test chamber 2 , requiring a corresponding test loading platform 5 . The two independent high-temperature test chambers simulate the internal cooling gas environment (the first high-temperature test chamber) and the external high-temperature combustion gas environment (the second high-temperature test chamber), respectively, with an adjustable temperature difference (e.g., 200°C to 1500°C). Depending on actual test requirements, the first and second high-temperature test chambers 1 and 2 can each be filled with different gas media, such as air or nitrogen.

[0061] Specifically, the first high-temperature test chamber 1 includes a first door 1.1 and a first housing 1.2. The first door 1.1 is provided with a first through hole 1.3 and a second through hole 1.4. The first through hole 1.1 is connected to one end of the gas path connection system 3. The air pressure balance device 4 is installed in the second through hole 1.3. A heating system is provided in the first housing 1.1. The second high-temperature test chamber 2 includes a second door 2.1 and a second housing 2.2. The second door 2.1 is provided with a third through hole 2.3 and a fourth through hole 2.4. The test loading platform 5 is installed in the third through hole 2.3. The other end of the gas path connection system 3 is connected (connected) to the test loading platform 5. The air pressure balance device 4 is installed in the fourth through hole 2.4. A heating system is provided in the second housing 2.2. The heating systems in the first high-temperature test chamber 1 and the second high-temperature test chamber 2 are the same, which are conventional heating systems and are generally provided in the inner wall of the chamber, so they are not shown in the figure.

[0062] In some embodiments, the gas communication system 3 includes a gas pipeline 3.1 and a gas control valve 3.2 provided on the gas pipeline. One end of the gas pipeline 3.1 is connected to the interior of the first high-temperature test chamber 1 through the first through hole 1.3, and the other end is connected to the interior of the test loading platform 5 in the second high-temperature test chamber 2. The gas control valve 3.2 is used to adjust the gas flow rate and temperature difference between the two test chambers. The gas control valve 3.2 is provided with an air pump 3.3, a flow control valve 3.4 and a temperature compensation module 3.5 in sequence along the gas flow direction. All of these are conventional existing equipment. Figure 5The diagram below shows the internal schematic of the gas control valve. In practice, the gas control valve may also have other structural forms. The air pump 3.3 is used to transport the cooling gas within the first high-temperature test chamber 1 to the test piece within the second high-temperature test chamber 2 via the gas pipeline 3.1. The flow control valve 3.4 is used to control the flow rate of the cooling gas in the gas pipeline 3.1. The temperature compensation module 3.5 is used to compensate for heat loss during the cooling gas transmission process, ensuring that heat loss during gas transmission is controllable.

[0063] The temperature compensation module 3.5 operates as follows: It contains a PID controller, a temperature sensor, and an electric heating wire. Assuming the cooling gas flowing to the test piece is required to be at a temperature of 500°C during the test, the first high-temperature test chamber is set to 500°C. During the test, the temperature sensor measures the cooling gas temperature flowing through it in real time. Due to transmission losses, the actual value measured by the temperature sensor may be less than 500°C. In this case, the measured value is fed back to the PID controller. Based on the received temperature value, the PID controller controls the power of the electric heating wire, causing it to heat and regulate the gas in the pipeline. This ensures that the cooling gas temperature flowing to the test piece is maintained at 500°C (with an error of ≤±5°C), improving test accuracy. Because the pipeline material, dimensions, and external environment parameters are all the same, the temperature loss per unit length can be calculated, and the required heating temperature at the monitoring point of the temperature detection module can be set. The PID control process is as follows: proportional action, immediately outputting high-power heating (when the temperature difference between the detected value and the required temperature is large); integral action, accumulating the temperature difference over time, eliminating steady-state errors, and gradually compensating for insufficient heating efficiency; differential action, when the temperature approaches 500°C, reducing the power in advance to prevent overshoot.

[0064] In some embodiments, the air pressure balancing device 4 is installed in the second through hole 1.4 and the fourth through hole 2.4 on the doors of the first high-temperature test chamber 1 and the second high-temperature test chamber 2. One end of the air pressure balancing device 4 is connected to the outside of the test chamber, and the other end is connected to the inside of the test chamber. The air pressure balancing device 4 includes a coaxially arranged ventilation pipe 4.1 and a ventilation pipe opening 4.2. The end of the ventilation pipe 4.1 away from the ventilation pipe opening 4.2 is connected to the outside of the test chamber, and the end of the ventilation pipe opening 4.2 away from the ventilation pipe 4.1 is connected to the inside of the test chamber. The length of the ventilation pipe 4.1 is greater than the length of the ventilation pipe opening 4.2, and the diameter of the ventilation pipe 4.1 is smaller than the diameter of the ventilation pipe opening 4.2.

[0065] In some embodiments, the test loading platform 5 includes a conducting pipeline 5.1, a clamping interface 5.2 and a mounting platform. The conducting pipeline 5.1 and the clamping interface 5.2 are both installed on the second door 2.1 of the second high-temperature test chamber 2. One end of the conducting pipeline 5.1 is provided with a thread 5.11 for facilitating connection with the end of the gas pipeline 3.1 of the gas path connection system 3. The other end of the conducting pipeline 5.1 is connected to the clamping interface 5.2, and the inside of the conducting pipeline 5.1 is communicated with the inside of the clamping interface 5.2. The clamping interface 5.2 is a square columnar structure with a hollow interior and one end open. The mounting platform is fixed on the clamping interface 5.2 and is located inside the second high-temperature test chamber 5. The mounting platform is used for mounting a test piece with a thermal barrier coating.

[0066] It can be understood that according to test pieces with different structures, the mounting platform can have different structural forms. Specifically, the mounting platform includes a first platform 5.3. The first platform 5.3 includes a first clamping plate 5.31, a connecting plate 5.32 and a second clamping plate 5.33. The first clamping plate 5.31, the connecting plate 5.32 and the second clamping plate 5.33 are sequentially connected to form a "C" - shaped structure for mounting the vane - type test piece 6. Cold air channels 5.34 for communicating with the air film holes on the test piece are provided on both the first clamping plate 5.31 and the second clamping plate 5.33. The middle of the bottom surface of the connecting plate 5.32 (the side away from the inside of the "C" - shaped structure) is recessed inward, and the positions where the first clamping plate 5.31 and the second clamping plate 5.33 are connected to the recessed part of the connecting plate 5.32 also correspond to be recessed inward, so that a recessed transition cavity 5.36 is formed in the middle of the side where the bottom of the "C" - shaped structure is connected to the clamping interface 5.2. The transition cavity 5.36 is communicated with the cold air channels 5.34. Pin holes 5.35 for connecting with the pin shafts on the test piece are also provided on the first clamping plate 5.31 and the second clamping plate 5.33.

[0067] Pin shafts 6.3 are respectively provided at both ends of the vane - type test piece (turbine vane - type structure) 6. The vane - type test piece 6 is clamped and fixed between the first clamping plate 5.31 and the second clamping plate 5.32 (i.e., inside the "C" - shaped structure) through the cooperation of the pin shafts 6.3 and the pin holes 5.35. When the first platform 5.3 is installed on the clamping interface 5.2, the bottom of the "C" - shaped structure (i.e., around the transition cavity 5.34) is clamped inside the clamping interface 5.2 and is in interference fit with the inner walls on four sides of the clamping interface 5.2. The transition cavity 5.34 faces the bottom of the clamping interface. During the test, the cooling gas transported through the gas path connection system 3 enters the transition cavity 5.36 through the conducting pipeline 5.1 and the clamping interface 5.2, then enters the cooling cavity 6.1 of the vane - type test piece 6 through the cold air channels 5.34, and then flows out from the first air film hole 6.2, realizing the control of the cooling efficiency. The schematic diagram of the flow of the cooling gas in the vane - type test piece 6 is as Figure 11 shown (the dotted line in the figure).

[0068] It is understandable that the installation platform can also include a second platform 5.4, and the second platform 5.4 includes four connecting plates 5.41. The four connecting plates 5.41 are connected in sequence to form a frame-type structure for installing the flat-plate test piece 7, that is, the second platform 5.4 is a structure that is hollow inside, closed on all sides, and penetrated at both ends. The flat-plate test piece 7 is a flat plate with a thermal expansion coating, and an inclined second air film hole 7.1 is provided on the flat plate. During the test, the flat-plate test piece 7 is fixed to one end penetrated by the second platform 5.4, and the other end penetrated by the second platform 5.4 is clamped in the clamping interface 5.2. The cooling gas transported through the gas path connection system 3 enters the interior of the second platform 5.4 through the conducting pipe 5.1 and the clamping interface 5.2, and then flows out from the second air film hole 7.1 of the flat-plate test piece 7 to achieve control of the cooling efficiency. The flow diagram of the cooling gas in the flat-plate test piece 7 is shown as follows. Figure 13 As shown (dashed line in the figure).

[0069] In some embodiments, based on the above-mentioned dual-high-temperature chamber combined thermal barrier coating testing apparatus with cooling gas paths, the present invention further provides a testing method for a test piece having a thermal expansion coating, comprising the following steps:

[0070] 1. Test preparation stage:

[0071] Step 1: Test piece installation and testing equipment installation

[0072] 1.1. Sensor Arrangement: Temperature detection modules 6.4 (high-precision thermocouples) are attached to key areas (such as the leading edge, trailing edge, and around the film holes) on the surface of blade-type test specimen 6 (i.e., turbine blade, nickel-based alloy blade with thermal barrier coating) to monitor the blade surface temperature distribution in real time. Strain gauges (not shown) are installed at the interface between the thermal barrier coating and the substrate to detect the blade stress crack growth rate.

[0073] 1.2. Fixing the test piece: Fix the blade-type test piece 6 to be tested on the clamping interface 5 . 2 of the test piece loading platform 5 through the first platform 5 . 3 .

[0074] Step 2: Device Status Check

[0075] 2.1. Verification of gas line tightness: Close the flow control valve 3.4 of the gas line connection system 3, start the air pump 3.3 to pressurize the pipeline to the set value (e.g., 0.5 MPa), and observe whether the pressure gauge is stable to ensure that there is no gas leakage.

[0076] 2.2. Temperature control system calibration: Conduct no-load temperature rise tests on the first high-temperature test chamber 1 and the second high-temperature test chamber 2 respectively to verify the temperature control accuracy (error ≤ ±5°C).

[0077] 2.3. Safety protection confirmation: Check the integrity of the test chamber's insulation layer and the redundant backup of the data acquisition system.

[0078] 2. Test parameter initialization

[0079] Step 3: Temperature difference and airflow parameter setting

[0080] 3.1. Dual-chamber temperature setting: Set the temperature of the first high-temperature test chamber 1 (simulating the cooling gas environment inside the blade) to 500°C (adjust according to the specific cooling medium requirements), and set the temperature of the second high-temperature test chamber 2 (simulating the external high-temperature fuel gas environment) to 1200°C (close to the fuel gas temperature of an aircraft engine).

[0081] 3.2. Temperature difference control: The target temperature difference (700℃) is maintained through linkage adjustment of two independent PID temperature control modules (control devices).

[0082] 3.3、Air film cooling parameter setting, gas flow rate: set the cooling gas flow rate to 2m through the flow control valve 3 / min (corresponding to typical engine operating conditions);

[0083] 3. Test operation and dynamic adjustment

[0084] Step 4: Start dual temperature zones simultaneously

[0085] 4.1. Heating stage: Start the heating systems of the first high-temperature test chamber 1 and the second high-temperature test chamber 2 at the same time, and heat them to the target temperature at a rate of 10°C / min.

[0086] 4..2. Steady-state maintenance: When the temperature of the two test chambers reaches the set value, they enter the constant temperature mode and last for 30 minutes to ensure a stable thermal environment.

[0087] Step 5: Film cooling cycle starts

[0088] 5.1. Cooling gas delivery: Start the air pump 3.3 to deliver the high-temperature cooling gas (such as air or nitrogen) in the first high-temperature test chamber 1 to the cooling cavity of the turbine blade in the second high-temperature test chamber 2 through the gas pipeline 3.1.

[0089] 5.2. The temperature compensation module monitors the gas temperature in the gas path in real time and dynamically adjusts the heating power through the PID controller to offset the heat loss during gas transmission (for example, the temperature drop in the pipeline from the first high-temperature test chamber to the blade is ≤3°C).

[0090] 4. Data Collection and Effect Evaluation

[0091] Step 6: Multi-parameter simultaneous monitoring

[0092] 6.1. Temperature field monitoring: Use thermocouples to record the blade surface temperature distribution and analyze the film cooling efficiency η.

[0093] 6.2. Stress Failure Analysis: Utilizing strain gauge data and high-speed camera footage of the thermal barrier coating crack growth process, the crack growth rate and critical stress threshold are calculated.

[0094] 6.3. Gas parameter recording: Collect data on gas flow, pressure and temperature compensation module in the gas circuit to evaluate system stability.

[0095] Step 7: Test termination and device reset

[0096] 7.1. Gradually cool down: Reduce the temperature of the two test chambers to below 200°C at a rate of 5°C / min and turn off the heating system.

[0097] 7.2. Stop gas circulation: Turn off the air pump 3.3 to release the residual pressure in the pipeline.

[0098] 7.3. Disassembly of test piece: dismantle the test loading platform 5, remove the test piece and clean the test loading platform 5 to prepare for subsequent tests.

[0099] The above-mentioned test method of the present invention can also be used for thermal fatigue testing of combustion chamber liners. The method steps are basically the same, except that only some parameters are adjusted, such as setting the temperature of the first test box to 800°C (simulating the cooling airflow inside the liner) and the second test box to 1100°C (simulating the high temperature of the outer wall of the combustion chamber).

[0100] The dual-high-temperature chamber combined test apparatus with cooling air circuits in this invention features temperature coordinated control and dynamic air circuit compensation technologies, enabling precise simulation of dual ambient temperatures. Through independently temperature-controlled dual test chambers and dynamic air circuit compensation, it achieves high-precision (±5°C) reproduction of the internal and external temperature difference of turbine blades for the first time, breaking through the limitations of single-field simulations in traditional test equipment. It also enables automated closed-loop control and real-time parameter adjustment based on sensor feedback, ensuring high consistency between test conditions and actual operating conditions. In addition to turbine blades, it also has other application scenarios (such as spacecraft thermal protection structure testing, which requires studying material failure tests caused by temperature differences), demonstrating its technical versatility.

[0101] The above are only specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be covered by the scope of protection of the present invention. Matters not described in detail in this specification belong to the prior art known to those skilled in the art.

Claims

1. A thermal barrier coating test device with dual high-temperature chambers and cooling air paths, characterized by: include A first high-temperature test chamber (1) is used to generate high-temperature cooling gas required for the test inside; A second high-temperature test chamber (2) is used to generate high-temperature combustion gas required for the test inside; An air path communication system (3) is connected between the first high-temperature test chamber (1) and the second high-temperature test chamber (2) and is used to transport cooling gas to the interior of the test piece in the second high-temperature test chamber (2) via the test loading platform (5) according to test requirements; An air pressure balancing device (4) is installed in the first high temperature test box (1) and the second high temperature test box (2) and is used to maintain a dynamic balance of air pressure in the first high temperature test box (1) and the second high temperature test box (2); A test loading platform (5) is installed in the second high-temperature test box (2) and is used for installing a test piece with a thermal barrier coating.

2. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 1 is characterized in that: The first high-temperature test box (1) comprises a first box door (1.1) and a first box body (1.2); a first through hole (1.3) and a second through hole (1.4) are provided on the first box door (1.1); the first through hole (1.1) is connected to the air path communication system (3); the air pressure balancing device (4) is installed in the second through hole (1.4); and a heating system is provided in the first box body (1.2).

3. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 1 is characterized in that: The second high-temperature test chamber (2) comprises a second chamber door (2.1) and a second chamber body (2.2); a third through hole (2.3) and a fourth through hole (2.4) are provided on the second chamber door (2.1); the test loading platform (5) is installed in the third through hole (2.3); the air pressure balancing device (4) is installed in the fourth through hole (2.4); and a heating system is provided in the second chamber body (2.2).

4. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 1 is characterized in that: The gas path communication system (3) comprises a gas path pipeline (3.1) and a gas path control valve (3.2) arranged on the gas path pipeline; one end of the gas path pipeline (3.1) is connected to the interior of the first high-temperature test chamber (1), and the other end is connected to the interior of the test loading platform in the second high-temperature test chamber (2); an air pump (3.3), a flow control valve (3.4) and a temperature compensation module (3.5) are arranged inside the gas path control valve (3.2); the air pump (3.3) is used to transport cooling gas to the interior of the test piece in the second high-temperature test chamber through the gas path pipeline; the flow control valve (3.4) is used to control the flow rate of the cooling gas; and the temperature compensation module (3.5) is used to compensate for heat loss during the transmission of the cooling gas.

5. The thermal barrier coating test device with dual high temperature chambers and cooling gas path according to claim 1 is characterized in that: The air pressure balancing device (4) is installed on the doors of the first high temperature test box (1) and the second high temperature test box (2), and one end of the air pressure balancing device (4) is connected to the outside of the test box and the other end is connected to the inside of the test box.

6. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 5 is characterized in that: The air pressure balancing device (4) comprises a coaxially arranged ventilation pipe (4.1) and a ventilation pipe opening (4.2); the end of the ventilation pipe (4.1) away from the ventilation pipe opening is in communication with the outside of the test box; the end of the ventilation pipe opening (4.2) away from the ventilation pipe is in communication with the inside of the test box; the length of the ventilation pipe (4.1) is greater than the length of the ventilation pipe opening (4.2); and the diameter of the ventilation pipe (4.1) is smaller than the diameter of the ventilation pipe opening (4.2).

7. The thermal barrier coating test device with dual high temperature chambers and cooling gas path according to claim 1 is characterized in that: The test loading platform (5) includes a conduction pipeline (5.1), a clamping interface (5.2) and a mounting platform. The conduction pipeline (5.1) and the clamping interface (5.2) are both installed on the second door of the second high-temperature test chamber (2). One end of the conduction pipeline (5.1) is connected to the gas path connection system (3), and the other end is connected to the clamping interface (5.2). The mounting platform is fixed on the clamping interface (5.2) and is located inside the second high-temperature test chamber (2). The mounting platform is used to mount the test piece with a thermal barrier coating.

8. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 7 is characterized in that: The mounting platform includes a first platform (5.3). The first platform (5.3) includes a first clamping plate (5.31), a connecting plate (5.32) and a second clamping plate (5.33). The first clamping plate (5.31), the connecting plate (5.32) and the second clamping plate are connected in sequence to form a U-shaped structure for mounting the blade-type test piece (6). Cold air channels (5.34) for connecting the cooling cavities on the test piece and pin holes (5.35) for connecting with the pins on the test piece are provided on both the first clamping plate (5.31) and the second clamping plate (5.33).

9. The thermal barrier coating test device with dual high-temperature chambers and cooling gas path according to claim 7, characterized in that: The mounting platform includes a second platform (5.4). The second platform (5.4) includes four connecting flat plates (5.41). The four connecting flat plates (5.41) are connected in sequence to form a square structure for mounting the flat-type test piece (7).

10. A test method for a thermal barrier coating test device with a combined double high-temperature chamber with a cooling gas path according to claim 1, characterized in that: A number of temperature detection modules and stress detection modules are arranged on the test piece; The test piece is installed on the test loading platform (5); The heating systems of the first high-temperature test chamber (1) and the second high-temperature test chamber (2) are started to heat the internal gases to the set temperatures respectively; The gas path connection system (3) is started to transport the high-temperature cooling gas in the first high-temperature test chamber (1) into the test piece inside the second high-temperature test chamber (2); The high-temperature gas environment during the operation of the test piece is simulated by high-temperature gas, and the cooling gas environment during the operation of the test piece is simulated by high-temperature cooling gas to test the thermal barrier coating on the surface of the test piece; The performance of the thermal barrier coating is analyzed based on the data detected by the temperature detection module and the stress detection module.

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