Thermal barrier coating service environment simulation device based on rotational flow combustion chamber

Abstract

The embodiment of the invention relates to the technical field of material performance testing, and discloses a thermal barrier coating service environment simulation device based on a rotational flow combustion chamber, the thermal barrier coating service environment simulation device based on the rotational flow combustion chamber comprises an inner cylinder, an outer cylinder and a rotational flow piece, the inner wall of the inner cylinder is used for spraying a thermal barrier coating, the outer cylinder sleeves the outer part of the outer cylinder, and the rotational flow piece sleeves the outer cylinder. The connecting wall of the rotational flow piece is connected with the air inlet end of the outer barrel and the air inlet end of the inner barrel, a cooling space is defined by the connecting wall, the outer wall of the outer barrel and the outer wall of the inner barrel, and a flow dividing cavity is formed in the rotational flow piece. The connecting wall is provided with a rotational flow channel and an air vent, the rotational flow channel is communicated with the flow dividing cavity and the interior of the inner barrel, the air vent is communicated with the flow dividing cavity and the cooling space, an inclination angle exists between the extending direction of the rotational flow channel and the axis of the inner barrel, the rotational flow piece is provided with an air inlet and an oil inlet, the air inlet is communicated with the flow dividing cavity, and the oil inlet is communicated with the interior of the inner barrel. And the actual flow field characteristics of the thermal barrier coating in a complex service environment in the rotational flow combustion chamber are simulated.

Description

Technical Field

[0001] The embodiments of the present application relate to the technical field of material performance testing, and in particular to a thermal barrier coating service environment simulation device based on a swirl combustion chamber. Background Art

[0002] In aircraft engines and gas turbines, the inner wall of the combustion chamber and the surface of the turbine blades are usually coated with thermal barrier coatings (TBCs) to improve their high temperature resistance and extend their service life. The real working environment in the swirl combustion chamber is a combination of many factors, which jointly affect the performance and life of the thermal barrier coating. Therefore, simulating the actual service environment of the thermal barrier coating is crucial to the performance verification of the material.

[0003] In the related art, it is often difficult for the test device to accurately simulate the complex service environment in the swirl combustion chamber, resulting in significant differences between the test results and the conditions under actual service conditions, which reduces the representativeness and reliability of the test results. Summary of the invention

[0004] The present application aims to solve at least one of the technical problems existing in the prior art or related art.

[0005] In view of this, according to the technical solution of the present application, a thermal barrier coating service environment simulation device based on a swirl combustion chamber is proposed, and the thermal barrier coating service environment simulation device based on a swirl combustion chamber includes: a spray gun assembly, and the spray gun assembly includes: an inner tube, an outer tube and a swirl member. The inner wall of the inner tube is used for spraying the thermal barrier coating, and the outer tube is sleeved on the outside of the outer tube. The connecting wall of the swirl member is respectively connected to the air inlet end of the outer tube and the inner tube, and the connecting wall and the outer tube and the outer wall of the inner tube enclose a cooling space, and the interior of the swirl member forms a diversion cavity. Among them, a swirl channel and an air vent are provided on the connecting wall, and the swirl channel connects the diversion cavity and the interior of the inner tube, and the air vent connects the diversion cavity and the cooling space. There is an inclination angle between the extension direction of the swirl channel and the axis of the inner tube, and an air inlet and an oil inlet are provided on the swirl member. The air inlet is connected to the diversion cavity, and the oil inlet is connected to the interior of the inner tube.

[0006] In some technical solutions provided in the present application, optionally, the swirl channel includes: multiple inner channels and multiple outer channels, the multiple inner channels are evenly distributed along the circumference and extend in the axial direction close to the inner tube, the multiple outer channels are evenly distributed along the circumference and extend in the axial direction away from the inner tube, and the outer channels are located on the outer periphery of the inner channels.

[0007] In some technical solutions provided in the present application, optionally, a cooling hole is provided on the wall of the inner cylinder, and the cooling hole connects the interior of the inner cylinder and the cooling space. And / or there are multiple inner cylinders, and any inner cylinder can be detachably connected to the outer cylinder and the swirl member.

[0008] In some technical solutions provided in the present application, optionally, a jet port is provided at the air outlet end of the outer cylinder, and the jet port is connected to the interior of the inner cylinder. The thermal barrier coating service environment simulation device based on the swirl combustion chamber also includes: a sample plate, a gap is provided between the sample plate and the air outlet end of the outer cylinder, a sample surface of the sample plate is opposite to the jet port, and the sample surface is used for spraying the thermal barrier coating.

[0009] In some technical solutions provided in the present application, optionally, the thermal barrier coating service environment simulation device based on the swirl combustion chamber further includes: a fixture and / or a spray gun assembly, the fixture clamps the sample plate and can adjust the angle of the sample plate relative to the axis of the jet nozzle. The spray gun assembly also includes: a base, the base is connected to the outer cylinder, and can adjust the angle of the axis of the outer cylinder relative to the sample plate, and the outer cylinder can slide axially relative to the base.

[0010] In some technical solutions provided in the present application, optionally, a thermal barrier coating service environment simulation device based on a swirl combustion chamber also includes: a compressed air device and a cooling pipeline, the compressed air device is connected to the air inlet, one end of the cooling pipeline is connected to the compressed air device, and the other end is opposite to the back side of the sample surface.

[0011] In some technical solutions provided in the present application, optionally, a thermal barrier coating service environment simulation device based on a swirl combustion chamber also includes: a fuel storage device, a control device, a pressure detection device and / or a temperature detection device, the fuel storage device is connected to the oil inlet, the control device is used to control the delivery status of the fuel storage device and the compressed air device, the pressure detection device is respectively arranged in the fuel storage device and the compressed air device, the pressure detection device is communicatively connected to the control device, the temperature detection device is located in the inner cylinder, and the temperature detection device is communicatively connected to the control device.

[0012] In some technical solutions provided in the present application, optionally, the thermal barrier coating service environment simulation device based on the swirl combustion chamber also includes: a detection device, the detection device can be located between the jet port and the sample plate, the detection device is used to detect the flow field information of the airflow impacting the sample plate, and the detection device includes: at least one of a particle image flow field measurement system and an infrared thermometer.

[0013] In some technical solutions provided in the present application, optionally, the spray gun assembly also includes: a light-transmitting port and a light-transmitting plate, the light-transmitting port is respectively arranged relatively on the walls of the outer tube and the inner tube, the light-transmitting plate is located at the light-transmitting port, and the detection device can also be located on the outside of the light-transmitting plate, and the detection device is used to detect the flow field information inside the inner tube.

[0014] In some technical solutions provided in the present application, optionally, a thermal barrier coating service environment simulation device based on a swirl combustion chamber also includes: a detection control device, which is communicatively connected to the detection device and is used to obtain flow field information collected by the detection device, and the control device is also used to adjust the position and detection angle of the detection device.

[0015] Compared with the prior art, the present invention has at least the following beneficial effects:

[0016] After the compressed air enters the cooling space outside the inner cylinder through the vent, the temperature of the inner wall of the inner cylinder is reduced, so that the inner cylinder simulates the temperature condition of the inner wall of the real combustion chamber under the high-temperature combustion environment, thereby improving the accuracy of the test results.

[0017] By setting up a swirl channel, the airflow forms a rotating flow field inside the inner tube, and the fuel and compressed air are fully mixed, thereby improving the combustion efficiency. The swirl also makes the high-temperature gas generated by the combustion evenly distributed in the main combustion zone, avoiding local overheating and stabilizing the combustion process. In addition, a high-temperature, high-pressure, high-speed swirl and turbulent combustion ring is formed inside the inner tube, so that the thermal barrier coating not only withstands the erosion of high-temperature and high-pressure airflow, but also faces the complex flow phenomena caused by swirl and turbulence. The actual flow field characteristics of the thermal barrier coating in the complex service environment of the swirl combustion chamber are simulated, so that the test results meet the actual service conditions and improve the representativeness and reliability of the test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Also, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0019] Figure 1 A schematic diagram of the structure of a thermal barrier coating service environment simulation device based on a swirl combustion chamber according to an embodiment of the present application;

[0020] Figure 2 One of the structural schematic diagrams of a spray gun assembly of an embodiment provided in the present application;

[0021] Figure 3 The second structural schematic diagram of a spray gun assembly according to an embodiment of the present application;

[0022] Figure 4 The third structural schematic diagram of a spray gun assembly according to an embodiment of the present application;

[0023] Figure 5 A schematic diagram of the surface temperature distribution of a sample plate according to an embodiment of the present application.

[0024] in, Figures 1 to 5 The corresponding relationship between the reference numerals and the component names is as follows:

[0025] 10 A thermal barrier coating service environment simulation device based on a swirl combustion chamber, 100 a spray gun assembly, 110 an inner cylinder, 111 a cooling hole, 112 an air jet, 120 an outer cylinder, 130 a swirl member, 131 a connecting wall, 132 a diversion cavity, 133 an air inlet, 134 an oil inlet, 135 a swirl channel, 1351 an inner channel, 1352 an outer channel, 136 an air vent, 140 a cooling space, 150 a base, 160 a light-transmitting port, 170 a light-transmitting plate, 200 a sample plate, 210 a sample surface, 300 a fixture, 400 a compressed air device, 500 a cooling pipeline, 600 a fuel storage device, 700 a control device, 800 a detection device, and 900 a detection and control device. DETAILED DESCRIPTION

[0026] In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0027] The embodiment of the present application provides a thermal barrier coating service environment simulation device 10 based on a swirl combustion chamber, such as Figure 2 , Figure 3 and Figure 4 As shown, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber includes: a spray gun assembly 100, the spray gun assembly 100 includes: an inner cylinder 110, an outer cylinder 120 and a swirl member 130, the inner wall of the inner cylinder 110 is used for spraying the thermal barrier coating, the outer cylinder 120 is sleeved on the outside of the outer cylinder 120, the connecting wall 131 of the swirl member 130 is respectively connected to the air inlet ends of the outer cylinder 120 and the inner cylinder 110, the connecting wall 131 and the outer wall of the outer cylinder 120 and the inner cylinder 110 enclose a cooling space 140, and the interior of the swirl member 130 forms a diversion cavity 132. Among them, a swirl channel 135 and an air vent 136 are provided on the connecting wall 131, the swirl channel 135 connects the diverter chamber 132 and the interior of the inner cylinder 110, the air vent 136 connects the diverter chamber 132 and the cooling space 140, and there is an inclination angle between the extension direction of the swirl channel 135 and the axis of the inner cylinder 110. The swirl member 130 is provided with an air inlet 133 and an oil inlet 134, the air inlet 133 is connected to the diverter chamber 132, and the oil inlet 134 is connected to the interior of the inner cylinder 110.

[0028] In this embodiment, a thermal barrier coating to be tested is sprayed on the inner wall of the inner cylinder 110, and the thermal barrier coating is used to be sprayed on the inner wall of the combustion chamber and the outer surface of the turbine blades. The outer cylinder 120 is sleeved on the outside of the outer cylinder 120 and is coaxially arranged with the inner cylinder 110. The swirl member 130 includes a connecting wall 131, which simultaneously blocks the air inlet end of the outer cylinder 120 and the air inlet end of the inner cylinder 110. The connecting wall 131 and the outer cylinder 120 are enclosed and then covered on the outer periphery of the inner cylinder 110, so that a cooling space 140 is formed between the inner wall of the outer cylinder 120 and the outer wall of the inner cylinder 110. A diverter chamber 132 is formed inside the swirl member 130, and the diverter chamber 132 and the cooling space 140 are respectively located on both sides of the connecting wall 131.

[0029] An air inlet 133 is provided on the wall of the diversion chamber 132, and the air inlet 133 is used to input compressed air. The compressed air enters the diversion chamber 132 to achieve pressure expansion, the speed of the airflow is slowed down, and part of the dynamic pressure is converted into static pressure, which helps to stabilize the airflow and lay the foundation for subsequent flow control.

[0030] The swirl channel 135 is close to the center of the connecting wall 131 and connects the flow dividing chamber 132 and the inside of the inner cylinder 110. The vent 136 is close to the outer periphery of the connecting wall 131 and connects the flow dividing chamber 132 and the cooling space 140. The compressed air entering the flow dividing chamber 132 is divided into two paths, one part of the compressed air enters the inside of the inner cylinder 110 through the swirl channel 135, and the other part of the compressed air enters the cooling space 140 outside the inner cylinder 110 through the vent 136. Figure 2 The solid arrow in the middle points to the flow direction of the compressed air.

[0031] The fuel inlet 134 on the swirl element 130 is used to input fuel, and for example, the fuel may be atomized aviation kerosene. The fuel inlet 134 may be a pressure atomizing nozzle. Figure 2 The hollow arrow points to the direction of fuel flow. The oil inlet 134 passes through the connecting wall 131 and is connected to the interior of the inner cylinder 110. After the fuel enters the interior of the inner cylinder 110 through the oil inlet 134, it mixes with the compressed air that enters the inner cylinder 110 through the swirl channel 135, and burns inside the inner cylinder 110 to generate high-temperature and high-pressure combustion gas, forming a main combustion zone inside the inner cylinder 110.

[0032] The swirl channel 135 is inclined toward or away from the axis of the inner cylinder 110 during the extension process, so that there is an inclination angle between the extension direction of the swirl channel 135 and the axis of the inner cylinder 110. Figure 4The arrow at Y in the figure points to the extension direction of the swirl channel 135, X is the axis of the inner cylinder 110, and A is the inclination angle. When the compressed air enters the inner cylinder 110, it generates a tangential velocity under the guidance of the swirl channel 135, forming a swirling airflow with a tangential component. The airflow moves in a spiral shape under the action of the swirl channel 135, so that the airflow has both axial velocity and tangential velocity components, and the airflow rotates around the axis of the inner cylinder 110.

[0033] After the compressed air enters the cooling space 140 outside the inner cylinder 110 through the vent 136, the inner wall temperature of the inner cylinder 110 is reduced, so that the inner cylinder 110 simulates the temperature condition of the inner wall of a real combustion chamber under a high-temperature combustion environment, thereby improving the accuracy of the test results.

[0034] By providing the swirl channel 135, the airflow forms a rotating flow field inside the inner tube 110, and the fuel and compressed air are fully mixed, thereby improving the combustion efficiency. The swirl also makes the high-temperature gas generated by the combustion evenly distributed in the main combustion zone, avoiding local overheating and stabilizing the combustion process. In addition, a high-temperature, high-pressure, high-speed swirl and turbulent combustion ring is formed inside the inner tube 110, so that the thermal barrier coating not only withstands the erosion of high-temperature and high-pressure airflow, but also faces the complex flow phenomena caused by swirl and turbulence. The actual flow field characteristics of the thermal barrier coating in the complex service environment in the swirl combustion chamber are simulated, so that the test results meet the actual service conditions and improve the representativeness and reliability of the test results.

[0035] For example, the swirl channel 135 may be formed by a through hole extending obliquely, or by a guide vane provided in a through hole extending along the axis, and the guide vane extends obliquely relative to the axis of the inner cylinder 110. There is an inclination angle between the extension direction of the inclined channel and the axis of the inner cylinder 110, as projected on the horizontal plane and / or the vertical plane, and the inclination angle may be 10° to 50°.

[0036] Exemplarily, there are multiple swirl members 130, and the inclination angles or inclination directions of the multiple swirl members 130 are different. Any swirl member 130 is detachably connected to the inner tube 110 and the outer tube 120. By replacing different swirl members 130, the service conditions of different swirl angles and swirl directions are controlled. The thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes an end cover, which is connected to the outer tube 120 and the inner tube 110. The end cover replaces the swirl member 130, and a comparative experiment on the influence of swirl can be carried out.

[0037] In some embodiments provided in this application, Figure 3 and Figure 4As shown, optionally, the swirl channel 135 includes: a plurality of inner channels 1351 and a plurality of outer channels 1352, the plurality of inner channels 1351 are evenly distributed along the circumferential direction and extend in the axial direction close to the inner cylinder 110, the plurality of outer channels 1352 are evenly distributed along the circumferential direction and extend in the axial direction away from the inner cylinder 110, and the outer channels 1352 are located on the outer periphery of the inner channels 1351.

[0038] In this embodiment, the inner channel 1351 and the outer channel 1352 are evenly distributed along the circumference, and the inner channel 1351 and the outer channel 1352 extend in opposite directions. The inner channel 1351 shrinks and extends inwardly toward the direction close to the axis, and the outer channel 1352 expands and extends outwardly toward the direction away from the axis. Multiple outer channels 1352 surround the outer circumference of multiple inner channels 1351, forming a concentric circular distribution. The swirl channels 135 are evenly distributed to form a symmetrical structure, so that the movement of the fluid is also symmetrical. After the airflow flows through the swirl channels 135, the airflow rotates at a high speed at the periphery. Under the action of the low-pressure area, part of the airflow flows in the opposite direction. The tangential velocity of the swirl airflow is combined with the geometric symmetry of the inner cylinder 110, so that the airflow forms symmetrical rotating vortices on the left and right sides, and then the swirl member 130 forms two symmetrical recirculation zones inside the inner cylinder 110, and can have positive and negative rotation directions. The recirculation zones are located on both sides of the main combustion zone, and the main axial airflow flow area is formed in the middle.

[0039] This reflow airflow circulates in the inner barrel 110, which helps to bring the high-temperature combustion products back to the combustion chamber inlet area to mix with the newly entered air and fuel to maintain the stability of combustion. The complex flow phenomena caused by swirl and turbulence simulate the actual flow field characteristics of the thermal barrier coating under the complex service environment in the swirl combustion chamber, making the test results consistent with the actual service conditions and improving the representativeness and reliability of the test results.

[0040] Exemplarily, the cross-sectional dimension of the outer channel 1352 is greater than the cross-sectional dimension of the inner channel 1351 .

[0041] In some embodiments provided in this application, Figure 2 and Figure 4 As shown, optionally, a cooling hole 111 is provided on the wall of the inner cylinder 110, and the cooling hole 111 communicates with the interior of the inner cylinder 110 and the cooling space 140. And / or the number of the inner cylinder 110 is multiple, and any inner cylinder 110 can be detachably connected to the outer cylinder 120 and the swirl member 130.

[0042] In this embodiment, a cooling hole 111 connecting the inside and outside of the inner cylinder 110 is provided on the cylinder wall of the inner cylinder 110, so that the compressed air in the cooling space 140 can enter the interior of the inner cylinder 110 through the cooling hole 111, and form a cooling air film on the inner wall surface of the inner cylinder 110, thereby further reducing the inner wall temperature of the inner cylinder 110, effectively controlling the temperature of the inner cylinder 110, and allowing the inner cylinder 110 to simulate the temperature condition of the inner wall of a real combustion chamber under a high-temperature combustion environment, thereby improving the accuracy of the test results.

[0043] Exemplarily, there are multiple cooling holes 111 , and the multiple cooling holes 111 are evenly distributed on the wall surface of the inner cylinder 110 to improve the uniformity of cooling.

[0044] When the test piece needs to be replaced, the inner cylinder 110 is disassembled from the outer cylinder 120 and the swirl element 130, and different thermal barrier coatings are sprayed on the replaced inner cylinder 110, so that the performance of different thermal barrier coatings can be tested. The coating can be replaced by simply disassembling and replacing the inner cylinder 110, avoiding large-scale disassembly of the entire spray gun assembly 100, thereby improving the convenience and efficiency of testing the thermal barrier coating.

[0045] In some embodiments provided in this application, Figure 1 As shown, optionally, a jet port 112 is provided at the air outlet end of the outer cylinder 120, and the jet port 112 is connected to the interior of the inner cylinder 110. The thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes: a sample plate 200, and a spacing is provided between the sample plate 200 and the air outlet end of the outer cylinder 120, and a sample surface 210 of the sample plate 200 is opposite to the jet port 112, and the sample surface 210 is used for spraying the thermal barrier coating.

[0046] In this embodiment, the gas outlet end of the outer cylinder 120 is provided with a jet port 112 connected to the inside of the inner cylinder 110, so that the combustion gas in the inner cylinder 110 can be ejected outward through the jet port 112. The sample surface 210 is located at one end of the sample plate 200, and the thermal barrier coating to be tested is sprayed. The sample surface 210 is opposite to the jet port 112, so that the gas sprayed from the spray gun assembly 100 can impact the sample surface 210, thereby testing the thermal barrier coating. The service environment of the thermal barrier coating when located on the turbine blade is simulated by the sample plate 200, and the high temperature resistance and thermal stress resistance of the thermal barrier coating can be accurately evaluated, thereby improving the detection accuracy of the thermal barrier coating.

[0047] In some embodiments provided in this application, Figure 1As shown, optionally, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber further includes: a fixture 300 and / or a spray gun assembly 100, wherein the fixture 300 clamps the sample plate 200 and is capable of adjusting the angle of the sample plate 200 relative to the axis of the jet nozzle 112. The spray gun assembly 100 further includes: a base 150, wherein the base 150 is connected to the outer cylinder 120 and is capable of adjusting the angle of the axis of the outer cylinder 120 relative to the sample plate 200, and the outer cylinder 120 is capable of sliding axially relative to the base 150.

[0048] In this embodiment, the clamp 300 clamps the bottom of the sample plate 200 to provide structural support for the sample plate 200. The sample plate 200 can rotate relative to the clamp 300, so that the clamp 300 can adjust the clamping angle of the sample plate 200, thereby adjusting the placement angle of the sample plate 200.

[0049] The base 150 is connected to the bottom of the outer cylinder 120 to provide structural support for the outer cylinder 120. The outer cylinder 120 can rotate relative to the base 150, so that the base 150 can adjust the supporting angle of the outer cylinder 120, thereby adjusting the placement angle of the outer cylinder 120 and controlling the injection direction of the jet port 112.

[0050] The axis of the air jet 112 is colinear with the axis of the inner tube 110. By controlling the angle of the sample plate 200 relative to the axis of the air jet 112, the impact angle of the airflow ejected from the air jet 112 on the sample plate 200 can be controlled, the angle between the high-temperature flame flow and the surface of the sample to be tested can be adjusted, and the test range of the thermal barrier coating can be expanded.

[0051] The outer cylinder 120 can slide axially relative to the base 150, so as to adjust the distance between the outer cylinder 120 and the sample plate 200, control the impact distance of the airflow ejected from the jet nozzle 112 on the sample plate 200, adjust the impact temperature of the surface of the sample to be tested, and expand the test range of the thermal barrier coating.

[0052] In some embodiments provided in this application, Figure 1 As shown, optionally, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes: a compressed air device 400 and a cooling pipeline 500, the compressed air device 400 is connected to the air inlet 133, one end of the cooling pipeline 500 is connected to the compressed air device 400, and the other end is opposite to the back side of the sample surface 210.

[0053] In this embodiment, the compressed air device 400 is used to generate compressed air. The output end of the compressed air device 400 is respectively connected to the air inlet 133 and the cooling pipeline 500. A part of the compressed air enters the spray gun assembly 100 through the air inlet 133 to cool the thermal barrier coating on the inner cylinder 110. The other part of the compressed air is output to the back side of the sample surface 210 through the cooling pipeline 500 to cool the thermal barrier coating sprayed on the front side of the sample surface 210, thereby simulating the service environment of the thermal barrier coating when it is located on the turbine blade, thereby improving the restoration degree of the thermal barrier coating use scenario and improving the accuracy of the test.

[0054] Exemplarily, the sample plate 200 may be a test piece structure or a hollow blade structure. Figure 5 The surface temperature distribution of the rectangular test piece structure shows the simulation of the hot spot load on the surface of the thermal barrier coating. In the case where the sample plate 200 is a hollow blade structure, the output end of the cooling pipeline 500 extends into the hollow of the hollow blade structure. The compressed air device 400 can be an air compressor.

[0055] In some embodiments provided in this application, Figure 1 As shown, optionally, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes: a fuel storage device 600, a control device 700, a pressure detection component and / or a temperature detection component, the fuel storage device 600 is connected to the oil inlet 134, the control device 700 is used to control the delivery status of the fuel storage device 600 and the compressed air device 400, the pressure detection component is respectively arranged in the fuel storage device 600 and the compressed air device 400, the pressure detection component is communicatively connected to the control device 700, the temperature detection component is located in the inner cylinder 110, and the temperature detection component is communicatively connected to the control device 700.

[0056] In this embodiment, the fuel storage device 600 is used to contain fuel and pressurize and atomize the fuel to obtain atomized fuel. The output end of the fuel storage device 600 is connected to the oil inlet 134 , and the fuel enters the spray gun assembly 100 through the oil inlet 134 .

[0057] The control device 700 is electrically connected to the fuel storage device 600 and the compressed air device 400 respectively, and is capable of controlling the flow rate and pressure of the medium transported to the outside by the fuel storage device 600 and the compressed air device 400.

[0058] The pressure detection components are respectively arranged in the fuel storage device 600 and the compressed air device 400. The pressure detection components can obtain the pressure values ​​in the fuel storage device 600 and the compressed air device 400, and send them to the control device 700, so that the control device 700 can monitor the delivery pressure of compressed air and fuel in real time, control the flow rate and pressure of fuel and compressed air, and adjust the combustion temperature in the inner cylinder 110 by increasing or decreasing the fuel supply when the load changes.

[0059] The temperature detection component is located in the inner cylinder 110, and the pressure detection component can obtain the combustion temperature in the inner cylinder 110 and send it to the control device 700, so that the control device 700 can control the flow and pressure of fuel and compressed air according to the temperature of the inner cylinder 110, and adjust the combustion temperature in the inner cylinder 110.

[0060] The control device 700 can generate the required temperature gradient and pressure conditions on the surface of the thermal barrier coating by controlling temperature and pressure, so as to accurately evaluate the high temperature resistance and thermal stress resistance of the thermal barrier coating. The data acquisition and control device 700 ensures the stability of the experimental process and the reliability of the results by real-time monitoring of various experimental parameters.

[0061] In some embodiments provided in this application, Figure 1 As shown, optionally, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes: a detection device 800, the detection device 800 can be located between the jet port 112 and the sample plate 200, the detection device 800 is used to detect the flow field information of the airflow impacting the sample plate 200, and the detection device 800 includes: at least one of a particle image flow field measurement system and an infrared meter.

[0062] In this embodiment, when the detection device 800 is between the air jet 112 and the sample plate 200, the detection end of the detection device 800 is opposite to the sample surface 210, and can detect the flow field information of the sample plate 200 when the jet airflow from the air jet 112 impacts the sample plate 200, thereby facilitating the monitoring of the performance of the thermal barrier coating during the experiment.

[0063] The particle image flow field measurement system may be a high-speed particle image PIV (Particle Image Velocimetry) measurement system, and the particle image flow field measurement system is used to obtain airflow velocity field information. The infrared thermometer is used to obtain temperature information of the flow field, and specifically, the infrared thermal imager measures the inner wall temperature of the inner cylinder 110.

[0064] In some embodiments provided in this application, Figure 4 As shown, optionally, the spray gun assembly 100 also includes: a light-transmitting port 160 and a light-transmitting plate 170, the light-transmitting port 160 is respectively arranged on the walls of the outer tube 120 and the inner tube 110 relative to each other, the light-transmitting plate 170 is located at the light-transmitting port 160, and the detection device 800 can also be located on the outside of the light-transmitting plate 170, and the detection device 800 is used to detect the flow field information inside the inner tube 110.

[0065] In this embodiment, light-transmitting openings 160 are provided on the cylinder wall of the outer cylinder 120 and the cylinder wall of the inner cylinder 110, and the light-transmitting openings 160 are opposite to each other. A light-transmitting plate 170 is provided on any light-transmitting opening 160. When the detection device 800 is located on the outside of the light-transmitting plate 170, the detection device 800 can detect the flow field information of the airflow inside the inner cylinder 110 through the light-transmitting plate 170, so as to facilitate monitoring the performance of the thermal barrier coating during the experiment.

[0066] Exemplarily, traceable tiny particles are added to the fuel or compressed air to facilitate the detection device 800 to measure the flow field information of the airflow.

[0067] Exemplarily, the inner cylinder 110 may be a multi-section structure for testing the performance of the thermal barrier coating under different swirl conditions. Any section of the inner cylinder 110 is provided with a light-transmitting port 160 to ensure that the coating test results of each section can be effectively monitored.

[0068] In some embodiments provided in this application, Figure 1 As shown, optionally, the thermal barrier coating service environment simulation device 10 based on the swirl combustion chamber also includes: a detection control device 900, which is communicated with the detection device 800 and is used to obtain the flow field information collected by the detection device 800, and the control device 700 is also used to adjust the position and detection angle of the detection device 800.

[0069] In this embodiment, the detection control device 900 can obtain the flow field information collected by the detection device 800, so as to monitor the performance of the thermal barrier coating and collect experimental data.

[0070] The control device 700 is also used to adjust the position and detection angle of the detection device 800, so as to control the detection position of the detection device 800 and make the detection device 800 face the sample plate 200 or the light-transmitting plate 170, thereby improving the detection accuracy and convenience of the detection device 800.

[0071] Exemplarily, the detection control device 900 includes a display, and the display is used to display the flow field information collected by the detection device 800.

[0072] In one possible embodiment, a device is provided that can simulate the service environment of a thermal barrier coating under critical loads such as combustion chamber swirl, and the device can simultaneously evaluate the service environment of the thermal barrier coating on the inner wall of the combustion chamber and the thermal barrier coating on the turbine blades.

[0073] After the compressed air passes through the air inlet 133, it is guided to the connecting wall 131 at the head of the inner tube 110 and is divided into two paths. A part of the air enters the main combustion zone through the swirl channel 135. Under the action of the swirl channel 135, the axial airflow generates a tangential velocity, forming two symmetrical recirculation zones in the main combustion zone. The swirl member 130 guides the axial airflow entering the combustion chamber into a rotating airflow with a tangential component through a group of inclined channels or blades. Under the action of the swirl member 130, the airflow exhibits a spiral motion. In addition to the axial velocity, that is, the velocity along the axis of the combustion tube, the airflow also has a significant tangential velocity component, that is, the rotational velocity around the axis of the combustion tube. After the high-speed rotating airflow at the periphery is guided into the combustion chamber, part of the airflow flows in the opposite direction under the action of the low-pressure zone to form a recirculation zone. The aviation kerosene atomized by the centrifugal nozzle is quickly mixed with the turbulent air, burned in the main combustion zone, and produces high-temperature combustion gas. Another part of the air enters the channel between the combustion chamber outer tube 120 and the flame inner tube 110 to reduce the temperature of the inner tube 110.

[0074] The air inlet portion of the swirl combustion chamber simulation spray gun assembly 100 can be replaced with a swirl component 130 having different swirl angles and swirl directions.

[0075] The temperature and flow characteristics of the generated high-temperature combustion gas can be controlled by adjusting the geometric parameters, gas flow velocity and fuel injection parameters of the swirl element 130. This adjustment enables the simulation spray gun to flexibly adapt to different experimental conditions and simulate the service environment of the thermal barrier coating of turbine blades under various working conditions. The precise temperature and flow field control makes it highly reliable and repeatable in the material performance assessment.

[0076] In the present invention, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance; the term "plurality" refers to two or more, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0077] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by terms such as “upper”, “lower”, “left”, “right”, “front” and “back” are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific orientation, and therefore, cannot be understood as a limitation on the present invention.

[0078] In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0079] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A thermal barrier coating service environment simulation device based on a swirl combustion chamber, characterized in that: include: A spray gun assembly, the spray gun assembly comprising: An inner cylinder, the inner wall of which is used for spraying a thermal barrier coating; An outer cylinder, sleeved on the outside of the outer cylinder; A swirl element, wherein the connecting wall of the swirl element is connected to the air inlet ends of the outer cylinder and the inner cylinder respectively, the connecting wall and the outer walls of the outer cylinder and the inner cylinder enclose a cooling space, and a diverter cavity is formed inside the swirl element; In which, a swirl channel and an air vent are provided on the connecting wall, the swirl channel connects the diverter chamber and the interior of the inner tube, the air vent connects the diverter chamber and the cooling space, there is an inclination angle between the extension direction of the swirl channel and the axis of the inner tube, and the swirl component is provided with an air inlet and an oil inlet, the air inlet is connected to the diverter chamber, and the oil inlet is connected to the interior of the inner tube.

2. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 1 is characterized in that: The swirl channel comprises: A plurality of inner channels are evenly distributed along the circumferential direction and extend toward the axial direction close to the inner cylinder; A plurality of outer channels are evenly distributed along the circumferential direction and extend in the axial direction away from the inner tube. The outer channels are located at the outer circumference of the inner channel.

3. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 1 is characterized in that: A cooling hole is provided on the wall of the inner cylinder, and the cooling hole communicates with the interior of the inner cylinder and the cooling space; and / or There are multiple inner cylinders, and any one of the inner cylinders can be detachably connected to the outer cylinder and the swirl member.

4. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 1 is characterized in that: The air outlet end of the outer tube is provided with an air jet, and the air jet is communicated with the interior of the inner tube. The thermal barrier coating service environment simulation device based on the swirl combustion chamber also includes: A sample plate is spaced apart from the gas outlet end of the outer cylinder, a sample surface of the sample plate is opposite to the gas jet port, and the sample surface is used for spraying thermal barrier coating.

5. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 4 is characterized in that: Also includes: A fixture, clamping the sample plate and capable of adjusting the angle of the sample plate relative to the axis of the air jet; and / or The spray gun assembly also includes: The base is connected to the outer cylinder and can adjust the angle of the axis of the outer cylinder relative to the sample plate. The outer cylinder can slide axially relative to the base.

6. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 4 is characterized in that: Also includes: a compressed air device, connected to the air inlet; A cooling pipeline, one end of which is connected to the compressed air device, and the other end of which is opposite to the back side of the sample surface.

7. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 6 is characterized in that: Also includes: a fuel storage device, connected to the fuel inlet; A control device, the control device is used to control the delivery state of the fuel storage device and the compressed air device; a pressure detection member, which is respectively arranged in the fuel storage device and the compressed air device, and the pressure detection member is communicatively connected with the control device; and / or A temperature detection component is located in the inner cylinder, and the temperature detection component is communicatively connected with the control device.

8. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 4 is characterized in that: Also includes: A detection device, which can be located between the air jet and the sample plate, and is used to detect flow field information of the airflow impacting the sample plate; The detection device comprises: at least one of a particle image flow field measurement system and an infrared thermometer.

9. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 8, characterized in that: The spray gun assembly also includes: Light-transmitting ports are respectively arranged opposite to each other on the walls of the outer tube and the inner tube; A light-transmitting plate is located at the light-transmitting port. The detection device can also be located outside the light-transmitting plate. The detection device is used to detect the flow field information inside the inner tube.

10. The thermal barrier coating service environment simulation device based on the swirl combustion chamber according to claim 8, characterized in that: Also includes: A detection control device is connected to the detection device for communication and is used to obtain the flow field information collected by the detection device. The control device is also used to adjust the position and detection angle of the detection device.

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