Gas turbine component cooling efficiency testing device and system

Abstract

The invention discloses a gas turbine component cooling efficiency testing device and system, the gas turbine component cooling efficiency testing device comprises a box body, an air inlet assembly, an air outlet assembly and a cooling housing, the box body is provided with an inner cavity, and the side wall of the box body is provided with a first air inlet, an air outlet and a cooling port which are communicated with the inner cavity. The air inlet assembly and the air outlet assembly are connected with the box body; the cooling housing is provided with a cavity, the cooling housing is connected with the cooling opening of the box body, a second air inlet, a third air inlet and a fourth air inlet are formed in the side wall of the cooling housing, the second air inlet and the cooling opening are coaxially arranged in the first direction, the third air inlet and the fourth air inlet are coaxially arranged in the second direction, and the first direction and the second direction are orthogonal to each other. According to the invention, air can enter and exit through different air inlets on the cooling housing for different to-be-tested parts so as to adjust the flow direction of cold air, so that the test of different to-be-tested parts can be satisfied, the test measurement of different purposes can be satisfied, and the compatibility and universality can be improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbines, and particularly relates to a test device and system for the cooling efficiency of gas turbine components. Background Art

[0002] At present, gas turbines play an irreplaceable important role in the fields of energy, aviation, and ships. One of the main development directions for improving the efficiency of gas turbines is to increase the turbine inlet temperature. As the turbine inlet temperature increases, the operating temperatures of the combustion chamber and turbine blades become more severe. Therefore, the cooling performance of the combustion chamber and turbine components determines the performance stability of the gas turbine.

[0003] In related technologies, there are a certain amount of devices for measuring and testing the cooling efficiency of the combustion chamber and turbine stator blades, but most of them are for specific gas turbines or components, such as those specifically for turbine stator blades or specifically for simplified flat plates of the combustion chamber flame tube wall, etc., and cannot meet the compatibility requirements for the installation and testing of various different types of test pieces. For example, the test box of the test platform specifically for the simplified flat plate test piece of the flame tube is too thin to accommodate other types of test pieces. This results in poor compatibility and versatility of the equipment. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems in the related technologies to some extent.

[0005] To this end, an embodiment of the present invention provides a test device and system for the cooling efficiency of gas turbine components with good compatibility, low test cost, and simple process.

[0006] The test device for the cooling efficiency of gas turbine components according to the embodiment of the present invention includes: A box body having an inner cavity. A first air inlet, an air outlet, and a cooling port communicating with the inner cavity are provided on the side wall of the box body. The inner cavity of the box body is used to place the component to be tested; An air intake assembly connected to the first air inlet of the box body to deliver hot air into the box body; An air outlet assembly connected to the air outlet of the box body to discharge the gas in the box body; A cooling shroud having a cavity. The cooling shroud is connected to the cooling port of the box body to communicate the cooling port with the cavity. A second air inlet, a third air inlet, and a fourth air inlet are provided on the side wall of the cooling shroud. The second air inlet and the cooling port are coaxially arranged in a first direction, and the third air inlet and the fourth air inlet are coaxially arranged in a second direction; Wherein, the first direction and the second direction are perpendicular to each other.

[0007] The gas turbine component cooling efficiency test device according to the embodiments of the present invention arranges a plurality of air inlets on the cooling housing. For different components to be tested, the cold air flow direction can be adjusted by the air inlet and outlet of different positions on the cooling housing, so as to meet the tests of different components to be tested, meet the test measurements of different uses, and improve the compatibility and versatility of the test device.

[0008] In some embodiments, the box body has a viewing window, and a transparent glass plate is provided at the viewing window so that the detection device can perform data measurement through the glass plate.

[0009] In some embodiments, the number of the viewing windows is multiple, and the multiple viewing windows are arranged on multiple sides of the box body; And / or, the glass plate is detachably connected to the box body, and the light transmission wavelength ranges of at least part of the glass plates are different.

[0010] In some embodiments, the first air inlet and the air outlet are coaxially arranged along the second direction; And / or, it further includes a first heating component, and the first heating component is arranged in the box body. The first heating component is used to heat the gas in the box body, or the first heating component is used to contact the component to be tested to heat the component to be tested; And / or, an installation part corresponding to the component to be tested is arranged in the inner cavity, and the size of the inner cavity is larger than that of the component to be tested.

[0011] In some embodiments, the air inlet assembly includes a coaxially arranged air inlet cylinder body and a rectifying cylinder body. The outlet end of the air inlet cylinder body is connected to the inlet end of the rectifying cylinder body, and the outlet end of the rectifying cylinder body is connected to the first air inlet of the box body; The cross-sectional size of the air inlet cylinder body gradually decreases from the end far away from the rectifying cylinder body to the end close to the rectifying cylinder body. A rectifying plate, a first detection component and a PIV particle sower are arranged in the rectifying cylinder body.

[0012] In some embodiments, the air outlet assembly includes a coaxially arranged post-measurement cylinder body and an exhaust cylinder body. The inlet end of the post-measurement cylinder body is connected to the exhaust port of the box body, and the outlet end of the post-measurement cylinder body is connected to the inlet end of the exhaust cylinder body; The cross-sectional size of the exhaust cylinder body gradually decreases from the end close to the post-measurement cylinder body to the end far away from the post-measurement cylinder body. A second detection component is arranged in the post-measurement cylinder body.

[0013] In some embodiments, it further includes an exhaust pipe, and the exhaust pipe is connected to the outlet end of the exhaust cylinder body. A back pressure regulating valve and a silencing component are arranged on the exhaust pipe.

[0014] The gas turbine component cooling efficiency test system according to an embodiment of the present invention includes: A test device, which is the gas turbine component cooling efficiency test device described in the above embodiment; A gas supply device, which includes a gas source, a main gas supply component, and a cold gas supply component. One end of the main gas supply component is connected to the gas source, and the other end is connected to the intake component. One end of the cold gas supply component is connected to the gas source, and the other end is connected to one of the second intake port, the third intake port, and the fourth intake port; A detection device, which is used to obtain data parameters in the test device; The main gas supply component is used to convey hot gas with a preset temperature and a preset flow rate into the box body, and the cold gas supply component is used to convey a cooling working medium with a preset flow rate into the cooling shroud to simulate the working conditions of the component to be tested under the working state.

[0015] In some embodiments, it further includes a carbon dioxide supply component, which is connected to one of the second intake port, the third intake port, and the fourth intake port of the cold gas supply component; And / or, the gas source includes a compressor and a gas storage tank. The compressed air generated by the compressor is stored in the gas storage tank, and the gas storage tank is connected to the main gas supply component and the cold gas supply component; And / or, the main gas supply component includes a main gas supply pipeline, a first valve group, and a second heating component. Both the first valve group and the second heating component are connected to the main gas supply pipeline. The first valve group includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the main gas supply pipeline according to the working conditions; And / or, the cold gas supply component includes a cold gas supply pipeline and a second valve group. The second valve group is connected to the cold gas supply pipeline. The second valve group includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the cold gas supply pipeline according to the working conditions; And / or, the detection device includes at least one of a thermocouple, a pneumatic scanning valve, a pressure sensitive paint measurement device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimetry device, and a laser Doppler velocimeter.

[0016] In some embodiments, the cold gas supply component further includes a first flow meter, a first on-off valve, and a third heating component, and the main gas supply component further includes a second flow meter; And / or, the carbon dioxide supply component includes a carbon dioxide storage tank, a carbon dioxide supply pipeline, a pressure reducing valve, a fourth heating component, and a second switching valve, and the pressure reducing valve, the fourth heating component, and the second switching valve are all connected to the carbon dioxide supply pipeline. Brief Description of the Drawings

[0017] Figure 1 is a schematic diagram of a gas turbine component cooling efficiency test device according to an embodiment of the present invention.

[0018] Figure 2 is a schematic diagram of a gas turbine component cooling efficiency test system according to an embodiment of the present invention.

[0019] Figure 3 is a schematic diagram of the air flow of a cooling shroud according to an embodiment of the present invention.

[0020] Figure 4 is a schematic diagram of the air flow of a cooling shroud according to another embodiment of the present invention.

[0021] Figure 5 is a schematic diagram of the air flow of a cooling shroud according to still another embodiment of the present invention.

[0022] Figure 6 is a schematic diagram of the layout of a simplified flat test piece of a combustion chamber according to an embodiment of the present invention.

[0023] Figure 7 is a schematic diagram of the layout of a stationary and rotating blade cooling test piece according to an embodiment of the present invention.

[0024] Figure 8 is a schematic diagram of the layout of a test piece of the actual structure of a combustion chamber according to an embodiment of the present invention.

[0025] Reference Signs: 100, gas turbine component cooling efficiency test device; 200, gas turbine component cooling efficiency test system; 1, box body; 11, first air inlet; 12, air outlet; 13, cooling port; 14, installation part; 15, window; 16, glass plate; 2, air inlet component; 21, air inlet cylinder; 22, rectifying cylinder; 23, rectifying plate; 3, air outlet component; 31, rear measurement cylinder; 32, exhaust cylinder; 33, exhaust pipe; 34, back pressure regulating valve; 35, silencing component; 4, cooling shroud; 41, second air inlet; 42, third air inlet; 43, fourth air inlet; 5, main gas supply component; 51, main gas supply pipeline; 52, first valve group; 53, second heating component; 54, second flowmeter; 6. Cold air supply assembly; 61. Cold air supply pipeline; 62. Second valve group; 63. First flowmeter; 64. First on-off valve; 65. Third heating component; 7. Carbon dioxide supply assembly; 71. Carbon dioxide supply pipeline; 72. Pressure reducing valve; 73. Fourth heating component; 74. Second on-off valve; 75. Carbon dioxide storage tank; 81. Compressor; 82. Air storage tank; 91. Simplified flat test piece of combustion chamber liner; 92. Cooling test piece of stator vane; 93. Test piece of actual structure of combustion chamber liner; 10. Detection equipment. Detailed implementation manners

[0026] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as a limitation to the present invention.

[0027] Refer to Figures 1 to 8 , the gas turbine component cooling efficiency test device 100 of the embodiment of the present invention includes a box body 1, an air inlet assembly 2, an air outlet assembly 3 and a cooling housing 4.

[0028] The box body 1 has an inner cavity. A first air inlet 11, an air outlet 12 and a cooling port 13 communicating with the inner cavity are provided on the side wall of the box body 1. The inner cavity of the box body 1 is used to place the component to be tested. The component to be tested in the embodiment of the present invention can be applicable to the stator vane cooling test piece 92 of a gas turbine, the actual structure test piece 93 of the combustion chamber liner of a combustion chamber, the simplified flat test piece 91 of the combustion chamber liner of a combustion chamber, etc. The spatial dimension in the box body 1 is larger than the dimension requirement of the component to be tested, so as to ensure that different components to be tested can be placed in the inner cavity. An installation part 14 corresponding to the component to be tested can also be provided in the inner cavity, which is convenient for fixing the component to be tested and avoiding shaking or toppling due to the influence of air flow.

[0029] After the component to be tested is placed in the box body 1, it corresponds to the cooling port 13, so that the component to be tested can be cooled by the cold air at the cooling port 13. According to different testing methods of different components to be tested, the component to be tested can be abutted against the circumference of the cooling port 13, so that the cooling surface, flow channel and other cooling areas of the component to be tested are opposite to the cooling port 13. The cold air at the cooling port 13 can impact the component to be tested for impingement cooling test, or the cold air can flow through the component to be tested and then enter the box body 1 and be discharged from the air outlet 12, or the cold air at the cooling port 13 contacts and exchanges heat with the cooling surface of the component to be tested.

[0030] The intake assembly 2 is connected to the first intake port 11 of the box body 1 to convey hot air into the box body 1. The exhaust assembly 3 is connected to the exhaust port 12 of the box body 1 to discharge the gas in the box body 1. The hot air can be hot air after heating the air. According to the actual working conditions, parameters such as the flow rate, flow velocity, and temperature of the hot air can be adjusted. When the hot air flows through the component to be tested, the environmental state of the component to be tested under actual working conditions can be simulated. The gas in the box body 1 flows out of the box body 1 through the exhaust port 12 and is discharged through the exhaust assembly 3.

[0031] In the embodiment of the present invention, the first intake port 11 and the exhaust port 12 of the box body 1 can be arranged coaxially and oppositely. The first intake port 11 and the exhaust port 12 can be arranged coaxially and oppositely along the second direction, so as to avoid the airflow in the box body 1 being blocked and improve the smooth flow of the airflow in the box body 1.

[0032] The cooling housing 4 has a cavity. The cooling housing 4 is connected to the cooling port 13 of the box body 1 so that the cooling port 13 is communicated with the cavity. The side wall of the cooling housing 4 is provided with a second intake port 41, a third intake port 42, and a fourth intake port 43. The second intake port 41 and the cooling port 13 are arranged coaxially along the first direction, and the third intake port 42 and the fourth intake port 43 are arranged coaxially along the second direction. Among them, the first direction and the second direction are orthogonal to each other. The first direction is the up-down direction shown in the figure, and the second direction is the left-right direction shown in the figure.

[0033] Any one of the second intake port 41, the third intake port 42, and the fourth intake port 43 can be used as the inlet of the cold air to introduce the cold air into the cooling housing 4. Flange plates are provided at the second intake port 41, the third intake port 42, and the fourth intake port 43 to facilitate connection with the corresponding intake and exhaust pipes. Of course, when the corresponding intake port on the cooling housing 4 is not required, it can be blocked by a flange blind cover.

[0034] For example, when the second intake port 41 is used as the inlet of the cold air, the cold air entering the cooling housing 4 can directly flow to the cooling port 13 and impact the component to be tested for impact cooling test. Another example, as Figure 3 shown, when the third intake port 42 is used as the inlet of the cold air and the fourth intake port 43 is used as the outlet of the cold air, the cold air flows through the cooling housing 4, then the cold air contacts and exchanges heat with the cooling surface of the component to be tested for cooling, and the flow direction of the cold air is the same as the flow direction of the hot air in the box body 1, which is used to simulate the cooling of the axial flow combustor. Another example, as Figure 5 shown, when the fourth intake port 43 is used as the inlet of the cold air and the third intake port 42 is used as the outlet of the cold air, the cold air flows through the cooling housing 4, then the cold air contacts and exchanges heat with the cooling surface of the component to be tested for cooling, and the flow direction of the cold air is opposite to the flow direction of the hot air in the box body 1, which is used to simulate the cooling of the heavy-duty burner annular combustor or the turboprop return combustor. Another example, as Figure 4As shown, the second air inlet 41, the third air inlet 42 or the fourth air inlet 43 serves as the inlet of the cold air. The cold air flows through the component to be tested and enters the box body 1, and then flows out through the air outlet 12 of the box body 1.

[0035] The gas turbine component cooling efficiency test device 100 according to the embodiment of the present invention arranges a plurality of air inlets on the cooling housing 4. For different components to be tested, the air can enter and exit through different air inlets on the cooling housing 4 to adjust the flow direction of the cold air, so as to meet the tests of different components to be tested, meet the test measurements for different purposes, and improve the compatibility and versatility of the test device.

[0036] Some specific embodiments of the gas turbine component cooling efficiency test device 100 according to the embodiment of the present invention will be described below.

[0037] As Figures 1 to 8 shown, the gas turbine component cooling efficiency test device 100 according to the embodiment of the present invention includes a box body 1, an air inlet assembly 2, an air outlet assembly 3 and a cooling housing 4.

[0038] The box body 1 has an inner cavity. A first air inlet 11, an air outlet 12 and a cooling port 13 communicating with the inner cavity are provided on the side wall of the box body 1. The inner cavity of the box body 1 is used to place the component to be tested. The component to be tested in the embodiment of the present invention can be applicable to the turbine stator blade cooling test piece 91 of the gas turbine, the real structure test piece 93 of the combustion chamber flame tube, the simplified flat test piece 91 of the combustion chamber flame tube, etc. The spatial dimension in the box body 1 is larger than the dimension requirement of the component to be tested, so as to ensure that different components to be tested can be placed in the inner cavity. An installation part 14 corresponding to the component to be tested can also be provided in the inner cavity. The component to be tested can be fixed in the box body 1 through connecting pieces such as bolts, which is convenient for fixing the component to be tested and avoids shaking or toppling due to the influence of the air flow.

[0039] The box body 1 has a viewing window 15, and a transparent glass plate 16 is provided at the viewing window 15 so that the detection device can perform data measurement through the glass plate 16.

[0040] The number of the viewing windows 15 is multiple, and the multiple viewing windows 15 are arranged on multiple side surfaces of the box body 1. For example, the box body 1 is a hexahedron, and three of the side surfaces are respectively provided with the first air inlet 11, the air outlet 12 and the cooling port 13, and the other three side surfaces can be provided with the viewing windows 15.

[0041] The glass plate 16 is detachably connected to the box body 1, and at least part of the light transmission wavelength ranges of the glass plate 16 are different. The detection device can be at least one of a thermocouple, a pneumatic scanning valve, a pressure sensitive paint measurement device, a thermochromic liquid crystal device, an infrared thermal imager, a particle image velocimetry device, and a laser Doppler velocimeter. In order to facilitate measurement by different optical measurement means, different glass plates 16 can be replaced to adapt to the use of lasers with different wavelengths.

[0042] Embodiments of the present invention can be compatible with various testing means such as thermosensitive liquid crystal (TLC), pressure sensitive paint (PSP), infrared thermal imager, particle image velocimetry (PIV), laser Doppler velocimeter (LDV), thermocouple, etc., and have better practicability.

[0043] After the component to be tested is placed in the box body 1, it corresponds to the cooling port 13, so that the cold air of the cooling port 13 can be used to cool the component to be tested. According to the different testing means of different components to be tested, the component to be tested can be abutted against the circumference of the cooling port 13, so that the cooling areas such as the cooling surface and the flow channel of the component to be tested are opposite to the cooling port 13. The cold air at the cooling port 13 can impact the component to be tested for impingement cooling test, or the cold air can flow through the component to be tested and then enter the box body 1 and be discharged from the air outlet 12, or the cold air at the cooling port 13 contacts and exchanges heat with the cooling surface of the component to be tested.

[0044] The air inlet assembly 2 is connected to the first air inlet 11 of the box body 1 to convey hot air into the box body 1. Specifically, the air inlet assembly 2 includes an air inlet cylinder body 21 and a rectifying cylinder body 22 arranged coaxially. The outlet end of the air inlet cylinder body 21 is connected to the inlet end of the rectifying cylinder body 22, and the outlet end of the rectifying cylinder body 22 is connected to the first air inlet 11 of the box body 1. The cross-sectional dimension of the air inlet cylinder body 21 gradually decreases from the end far away from the rectifying cylinder body 22 to the end close to the rectifying cylinder body 22. The air inlet cylinder body 21 is generally in the shape of a frustum of a cone, and the air flow can increase its flow velocity when flowing through the air inlet cylinder body 21. The rectifying cylinder body 22 is in the shape of a cylinder with an equal cross-section. A rectifying plate 23, a first detection component and a PIV particle sower are arranged in the rectifying cylinder body 22. The rectifying plate 23 can be a rectifying grid plate, and the rectifying grid plate can rectify the air flow flowing through the rectifying cylinder body 22. By changing the flow velocity and direction of the fluid, the occurrence of turbulence is reduced, thereby reducing the energy loss and improving the quality of the hot air flowing into the inner cavity of the box body 1. The first detection component can be sensors such as temperature, flow rate, pressure, etc., for detecting the parameters of the gas. The PIV particle sower can sow tracer particles in the fluid so as to measure the flow field velocity by particle image velocimetry (PIV).

[0045] The air outlet assembly 3 is connected to the air outlet 12 of the box body 1 to discharge the gas in the box body 1. Specifically, the air outlet assembly 3 includes a rear measurement cylinder body 31 and an exhaust cylinder body 32 arranged coaxially. The inlet end of the rear measurement cylinder body 31 is connected to the air outlet of the box body 1, and the outlet end of the rear measurement cylinder body 31 is connected to the inlet end of the exhaust cylinder body 32. The cross-sectional dimension of the exhaust cylinder body 32 gradually decreases from the end close to the rear measurement cylinder body 31 to the end far from the rear measurement cylinder body 31. A second detection component is provided in the rear measurement cylinder body 31. The second detection component can be sensors such as temperature, flow rate, and pressure sensors, and is used to detect the parameters of the gas flowing out of the box body 1. The rear measurement cylinder body 31 can be in the shape of a cylinder with a constant cross-section, and the exhaust cylinder body 32 is in the shape of a frustum of a cone. The cross-sectional dimension of the exhaust cylinder body 32 gradually increases along the gas flow direction, which can reduce the exhaust speed and reduce the noise.

[0046] The hot gas can be hot air after heating the air. According to the actual working conditions, parameters such as the flow rate, flow velocity, and temperature of the hot air can be adjusted. When the hot air flows through the component to be measured, the environmental state of the component to be measured under actual working conditions can be simulated. The gas in the box body 1 flows out of the box body 1 through the air outlet 12 and is discharged through the air outlet assembly 3.

[0047] The gas turbine component cooling efficiency test device 100 according to the embodiment of the present invention includes a first heating component. The first heating component is an electric heater. The first heating component is arranged in the box body 1. The first heating component is used to heat the gas in the box body 1, or the first heating component is used to contact the component to be measured to heat the component to be measured. Thereby, the working condition temperature can be better simulated, and the accuracy and reliability of the test can be improved.

[0048] The air outlet assembly 3 further includes an exhaust pipe 33. The exhaust pipe 33 is connected to the outlet end of the exhaust cylinder body 32. A back pressure regulating valve 34 and a silencing component 35 are provided on the exhaust pipe 33. The back pressure regulating valve 34 can effectively control and stabilize the air pressure parameters in the box body 1. The silencing component 35 can reduce the exhaust noise and avoid causing sound pollution to the surrounding environment.

[0049] In the embodiment of the present invention, the first air inlet 11 and the air outlet 12 of the box body 1 can be arranged coaxially and oppositely. The first air inlet 11 and the air outlet 12 can be arranged coaxially and oppositely along the second direction, so as to avoid the air flow in the box body 1 being blocked and improve the smoothness of the air flow in the box body 1.

[0050] The cooling housing 4 has a cavity. The cooling housing 4 is connected to the cooling port 13 of the box body 1 so that the cooling port 13 is in communication with the cavity. A second air inlet 41, a third air inlet 42 and a fourth air inlet 43 are provided on the side wall of the cooling housing 4. The second air inlet 41 and the cooling port 13 are coaxially arranged in a first direction. The third air inlet 42 and the fourth air inlet 43 are coaxially arranged in a second direction. Among them, the first direction and the second direction are orthogonal to each other. The first direction is the up-down direction shown in the figure, and the second direction is the left-right direction shown in the figure.

[0051] Any one of the second air inlet 41, the third air inlet 42 and the fourth air inlet 43 can be used as the inlet of the cold air, for introducing the cold air into the cooling housing 4. Flange plates are provided at the second air inlet 41, the third air inlet 42 and the fourth air inlet 43, which is convenient for connecting with the corresponding air inlet and outlet pipes. Of course, when the corresponding air inlet on the cooling housing 4 is not needed, it can be blocked by a flange blank cover.

[0052] For example, when the second air inlet 41 is used as the inlet of the cold air, the cold air entering the cooling housing 4 can directly flow to the cooling port 13 and impact the component to be tested, for performing the impact cooling test.

[0053] Also for example, as Figure 3 shown, when the third air inlet 42 is used as the inlet of the cold air and the fourth air inlet 43 is used as the outlet of the cold air, the cold air flows through the cooling housing 4, then the cold air contacts and exchanges heat with the cooling surface of the component to be tested for cooling, and the flow direction of the cold air is the same as the flow direction of the hot air in the box body 1, for simulating the cooling of the axial flow combustor.

[0054] Also for example, as Figure 5 shown, when the fourth air inlet 43 is used as the inlet of the cold air and the third air inlet 42 is used as the outlet of the cold air, the cold air flows through the cooling housing 4, then the cold air contacts and exchanges heat with the cooling surface of the component to be tested for cooling, and the flow direction of the cold air is opposite to the flow direction of the hot air in the box body 1, for simulating the cooling of the heavy-duty burner annular combustor or the turboprop return combustor.

[0055] Again for example, as Figure 4 shown, when the second air inlet 41, the third air inlet 42 or the fourth air inlet 43 is used as the inlet of the cold air, the cold air flows through the component to be tested and enters the box body 1, and then flows out through the air outlet 12 of the box body 1.

[0056] The gas turbine component cooling efficiency test device 100 according to the embodiment of the present invention, through the arrangement of multiple air inlets on the cooling housing 4, for different components to be tested, the flow direction of the cold air can be adjusted by the air inlet and outlet of different air inlets on the cooling housing 4, so as to meet the tests for different components to be tested, meet the test measurements for different purposes, and improve the compatibility and versatility of the test device.

[0057] As Figures 2 to 8, the gas turbine component cooling efficiency test system 200 according to an embodiment of the present invention includes a test device, a gas supply device, and a detection device 10.

[0058] The test device is the gas turbine component cooling efficiency test device 100 as described in the above embodiment.

[0059] The gas supply device includes a gas source, a main gas supply component 5, and a cold gas supply component 6. One end of the main gas supply component 5 is connected to the gas source, and the other end is connected to the intake component 2. One end of the cold gas supply component 6 is connected to the gas source, and the other end is connected to one of the second intake port 41, the third intake port 42, and the fourth intake port 43.

[0060] The gas source includes a compressor 81 and a gas storage tank 82. The compressed air generated by the compressor 81 is stored in the gas storage tank 82, and the gas storage tank 82 is connected to the main gas supply component 5 and the cold gas supply component 6. The gas storage tank 82 has a pressure stabilizing effect, which can avoid the problem of unstable air pressure caused by the working fluctuation of the compressor 81.

[0061] The detection device 10 is used to obtain the data parameters in the test device. The detection device 10 may include at least one of a thermocouple, a pneumatic scanning valve, a pressure sensitive paint measurement device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimetry device, and a laser Doppler velocimeter. According to different test purposes, the airflow parameters and airflow directions of the test device can be adjusted, and the corresponding detection device 10 can be selected.

[0062] The main gas supply component 5 is used to transport hot gas with a preset temperature and a preset flow rate into the box body 1, and the cold gas supply component 6 is used to transport a preset flow rate of cooling working medium into the cooling housing 4 to simulate the working conditions of the component to be tested in the working state.

[0063] The following describes the gas turbine component cooling efficiency test system 200 according to some specific embodiments of the present invention.

[0064] As Figures 2 to 8 shown, a gas turbine component cooling efficiency test system 200 includes a test device, a gas supply device, a detection device 10, and a carbon dioxide supply component 7.

[0065] The test device is the gas turbine component cooling efficiency test device 100 as described in the above embodiment.

[0066] The gas supply device includes a gas source, a main gas supply component 5, and a cold gas supply component 6. One end of the main gas supply component 5 is connected to the gas source, and the other end is connected to the intake component 2. One end of the cold gas supply component 6 is connected to the gas source, and the other end is connected to one of the second intake port 41, the third intake port 42, and the fourth intake port 43.

[0067] The air source includes a compressor 81 and a gas storage tank 82. The compressed air generated by the compressor 81 is stored in the gas storage tank 82, and the gas storage tank 82 is connected to the main air supply assembly 5 and the cold air supply assembly 6. The gas storage tank 82 has a pressure stabilizing effect, which can avoid the problem of unstable air pressure caused by the working fluctuation of the compressor 81.

[0068] The main air supply assembly 5 includes a main air supply pipeline 51, a first valve group 52, a second heating component 53, and a second flowmeter 54. The first valve group 52 and the second heating component 53 are both connected to the main air supply pipeline 51. The first valve group 52 includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the main air supply pipeline 51 according to the working conditions.

[0069] The number of the second heating components 53 can be multiple. The multiple second heating components 53 are connected in series with a plurality of control valves and then arranged in parallel to form a main air heating assembly.

[0070] The cold air supply assembly 6 includes a cold air supply pipeline 61, a second valve group 62, a first flowmeter 63, a first on-off valve 64, and a third heating component 65. The second valve group 62 is connected to the cold air supply pipeline 61. The second valve group 62 includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the cold air supply pipeline 61 according to the working conditions.

[0071] The third heating component 65 can be connected in series with one of the regulating valves in the second valve group 62 to heat the gas in one of the branches in the second valve group 62 as needed, so as to adjust the temperature of the gas transported to the cooling housing 4 to make it more compatible with the actual working conditions and improve the applicable range.

[0072] Both the first valve group 52 and the second valve group 62 include three regulating valves of large, medium, and small sizes to accurately control the intake air flow rate, and accurate adjustment can be achieved under different flow conditions, with good practicability.

[0073] The carbon dioxide supply assembly 7 is connected to one of the second intake port 41, the third intake port 42, and the fourth intake port 43 of the cold air supply assembly 6. The carbon dioxide supply assembly 7 includes a carbon dioxide storage tank 75, a carbon dioxide supply pipeline 71, a pressure reducing valve 72, a fourth heating component 73, and a second on-off valve 74. The carbon dioxide storage tank 75 is connected to the carbon dioxide supply pipeline 71. The pressure reducing valve 72, the fourth heating component 73, and the second on-off valve 74 are all connected to the carbon dioxide supply pipeline 71. The fourth heating component 73 can adjust the temperature of the carbon dioxide working medium.

[0074] The second heating component 53, the third heating component 65, and the fourth heating component 73 in the embodiments of the present invention can all be electric heaters, and they work independently to adjust the temperature of the working medium in the corresponding pipelines.

[0075] In the embodiments of the present invention, carbon dioxide and air are used as two cooling working fluids. Carbon dioxide as the working gas can be used for PSP pressure sensitive paint measurement, and cold air can be used for measurement by other means, which has better compatibility with the detection device 10 in applications.

[0076] The cold air supply pipeline 61 merges with the carbon dioxide supply pipeline 71 through a tee pipeline before accessing the cooling housing 4 and then supplies gas. The first switching valve 64 and the second switching valve 74 are used to select whether to supply air or carbon dioxide. When performing PSP measurement, the second switching valve 74 is opened to select to supply carbon dioxide into the cooling housing 4. When performing other tests, the first switching valve 64 is opened to supply air into the cooling housing 4. The second air inlet 41, the third air inlet 42, and the fourth air inlet 43 on the cooling housing 4 can all be used as cold air inlets and cold air outlets. Of course, a cold air outlet may not be provided on the cooling housing 4, and the cold air enters the box body 1 and then is discharged. For example, when performing film cooling or transpiration cooling tests, one of the three air inlets on the cooling housing 4 is used as the cold air inlet, and the other two air inlets are blocked by flange blind covers. All the cold air enters the box body 1 through the film holes of the test piece (the component to be measured) and is discharged together with the main gas. Another example is when performing impingement cooling tests, the second air inlet 41 is used as the cold air inlet, and the third air inlet 42 and / or the fourth air inlet 43 are used as the cold air outlets. The cold air is discharged through the outlet after cooling the test piece.

[0077] The detection device 10 is used to obtain the data parameters in the test device. The detection device 10 may include at least one of a thermocouple, a pneumatic scanning valve, a pressure sensitive paint measurement device, a thermochromic liquid crystal device, an infrared thermal imager, a particle image velocimetry device, and a laser Doppler velocimeter. According to different test purposes, the airflow parameters and the airflow direction of the test device are adjusted, and the corresponding detection device 10 is selected.

[0078] The main gas supply assembly 5 is used to supply hot gas with a preset temperature and a preset flow rate into the box body 1, and the cold air supply assembly 6 is used to supply a cooling working fluid with a preset flow rate into the cooling housing 4 to simulate the working conditions of the component to be measured in the working state.

[0079] The embodiments of the present invention are compatible with different types of component test pieces and testing means on the same test platform, simplifying the test cost and process. The embodiments of the present invention provide a test box 1 with good compatibility, which can be compatible with the turbine stator vane cooling test piece 92, the simplified flat test piece 91 of the combustion chamber flame tube, the real structure test piece 93 of the flame tube, etc. Through the replaceable interface cold gas supply component 6, the direction of the replaceable cold gas interface and the working medium can meet different test requirements, and carbon dioxide, cold air or closed can be connected to be compatible with various testing means such as thermochromic liquid crystal (TLC), pressure sensitive paint (PSP), infrared thermal imager, particle image velocimetry (PIV), laser Doppler velocimeter (LDV), thermocouple, etc. without replacing the main test platform equipment.

[0080] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the 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 element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

[0081] In addition, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0082] In the present invention, unless otherwise clearly specified and limited, the terms "mounted", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. 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.

[0083] In the present invention, unless otherwise clearly defined or limited, a first feature being "on" or "under" a second feature may mean that the first and second features are in direct contact, or the first and second features are indirectly in contact via an intermediate medium. Moreover, a first feature being "above", "over" and "on top of" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature has a higher level height than the second feature. A first feature being "under", "below" and "beneath" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature has a lower level height than the second feature.

[0084] In the present invention, the terms "an embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0085] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine component cooling efficiency test device, characterized in that, Comprising: A box body having an inner cavity, wherein a first air inlet, an air outlet and a cooling port communicating with the inner cavity are provided on a side wall of the box body, and the inner cavity of the box body is used for placing a component to be tested; An air inlet assembly connected to the first air inlet of the box body to convey hot air into the box body; An air outlet assembly connected to the air outlet of the box body to discharge the gas in the box body; A cooling housing having a cavity, the cooling housing being connected to the cooling port of the box body to communicate the cooling port with the cavity, and a second air inlet, a third air inlet and a fourth air inlet being provided on a side wall of the cooling housing, the second air inlet and the cooling port being coaxially arranged in a first direction, and the third air inlet and the fourth air inlet being coaxially arranged in a second direction; Wherein the first direction and the second direction are orthogonal to each other.

2. The gas turbine component cooling efficiency test device according to claim 1, wherein The box body has a viewing window, and a transparent glass plate is provided at the viewing window so that the detection device can perform data measurement through the glass plate.

3. The gas turbine component cooling efficiency test device according to claim 2, characterized in that, The number of the viewing windows is multiple, and the multiple viewing windows are provided on multiple side surfaces of the box body; And / or, the glass plate is detachably connected to the box body, and the light transmission wavelength ranges of at least part of the glass plates are different.

4. The gas turbine component cooling efficiency test device according to claim 1, characterized in that The first air inlet and the air outlet are coaxially arranged in the second direction; And / or, further comprising a first heating component provided in the box body, the first heating component being used for heating the gas in the box body, or the first heating component being used for contacting the component to be tested to heat the component to be tested; And / or, a mounting portion corresponding to the component to be tested is provided in the inner cavity, and the size of the inner cavity is larger than that of the component to be tested.

5. The gas turbine component cooling efficiency test device according to claim 1, characterized in that, The air inlet assembly includes a coaxially arranged air inlet cylinder and a rectifying cylinder, an outlet end of the air inlet cylinder is connected to an inlet end of the rectifying cylinder, and an outlet end of the rectifying cylinder is connected to the first air inlet of the box body; A cross-sectional dimension of the air inlet cylinder gradually decreases from an end far from the rectifying cylinder to an end close to the rectifying cylinder, and a rectifying plate, a first detection component and a PIV particle sower are provided in the rectifying cylinder.

6. The gas turbine component cooling efficiency test device according to claim 1, wherein The air outlet assembly includes a coaxially arranged post-measurement cylinder and an exhaust cylinder, an inlet end of the post-measurement cylinder is connected to the exhaust port of the box body, and an outlet end of the post-measurement cylinder is connected to an inlet end of the exhaust cylinder; A cross-sectional dimension of the exhaust cylinder gradually decreases from an end close to the post-measurement cylinder to an end far from the post-measurement cylinder, and a second detection component is provided in the post-measurement cylinder.

7. The gas turbine component cooling efficiency test device according to claim 6, characterized in that, Further comprising an exhaust pipe connected to an outlet end of the exhaust cylinder, and a back pressure regulating valve and a silencing component are provided on the exhaust pipe.

8. A gas turbine component cooling efficiency test system, characterized in that, Comprising: A testing device, which is a gas turbine component cooling efficiency testing device according to any one of claims 1 to 7; Gas supply device, the gas supply device includes a gas source, a main gas supply component and a cold gas supply component, one end of the main gas supply component is connected to the gas source, and the other end is connected to the intake component, one end of the cold gas supply component is connected to the gas source, and the other end is connected to one of the second intake port, the third intake port, and the fourth intake port; Detection device, the detection device is used to obtain data parameters in the test device; The main gas supply component is used to transport hot gas with a preset temperature and a preset flow rate into the box body, and the cold gas supply component is used to transport a cooling working medium with a preset flow rate into the cooling housing to simulate the working conditions of the component to be tested under the working state.

9. The gas turbine component cooling efficiency test system according to claim 8, wherein It further includes a carbon dioxide supply component, and the carbon dioxide supply component is connected to one of the second intake port, the third intake port, and the fourth intake port of the cold gas supply component; And / or, the gas source includes a compressor and a gas storage tank, the compressed air generated by the compressor is stored in the gas storage tank, and the gas storage tank is connected to the main gas supply component and the cold gas supply component; And / or, the main gas supply component includes a main gas supply pipeline, a first valve group and a second heating component, both the first valve group and the second heating component are connected to the main gas supply pipeline, and the first valve group includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the main gas supply pipeline according to the working conditions; And / or, the cold gas supply component includes a cold gas supply pipeline and a second valve group, the second valve group is connected to the cold gas supply pipeline, and the second valve group includes a plurality of regulating valves arranged in parallel with different specifications to adjust the air flow parameters in the cold gas supply pipeline according to the working conditions; And / or, the detection device includes at least one of a thermocouple, a pneumatic scanning valve, a pressure sensitive paint measuring device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimetry device, and a laser Doppler velocimeter.

10. The gas turbine component cooling efficiency test system according to claim 9, wherein The cold gas supply component further includes a first flow meter, a first on-off valve and a third heating component, and the main gas supply component further includes a second flow meter; And / or, the carbon dioxide supply component includes a carbon dioxide storage tank, a carbon dioxide supply pipeline, a pressure reducing valve, a fourth heating component and a second on-off valve, and the pressure reducing valve, the fourth heating component and the second on-off valve are all connected to the carbon dioxide supply pipeline.

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