Gas turbine component cooling efficiency test device and system

Abstract

The present invention discloses a gas turbine component cooling efficiency test device and system. The gas turbine component cooling efficiency test device includes a housing, an air inlet assembly, an air outlet assembly, and a cooling cover. The housing has an inner cavity, and the side walls of the housing are provided with a first air inlet, an air outlet, and a cooling port that are connected to the inner cavity. The air inlet assembly and the air outlet assembly are connected to the housing; the cooling cover has a cavity, and the cooling cover is connected to the cooling port of the housing. The side walls of the cooling cover are provided with a second air inlet, a third air inlet, and a fourth air inlet. The second air inlet and the cooling port are coaxially arranged along a first direction, and the third air inlet and the fourth air inlet are coaxially arranged along a second direction, and the first direction and the second direction are orthogonal to each other. The present invention can adjust the flow direction of cold air by letting air in and out of different components to be tested through different air inlets on the cooling cover, thereby meeting the testing of different components to be tested and meeting the test measurements for different purposes, thereby improving its compatibility and versatility.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbines, and in particular relates to a gas turbine component cooling efficiency testing device and system. Background Art

[0002] Gas turbines currently play an irreplaceable and important role in energy, aviation, and marine applications. Raising turbine inlet temperature is one of the primary development directions for improving gas turbine efficiency. As turbine inlet temperature increases, the operating temperatures of the combustion chamber and turbine blades become increasingly severe. Therefore, the cooling performance of the combustion chamber and turbine components determines the performance stability of the gas turbine.

[0003] There is a limited amount of equipment available in the related art for measuring and testing the cooling efficiency of combustion chamber and turbine vane components. However, most are designed for specific gas turbines or components, such as turbine vanes or simplified flat panels on the combustion chamber liner wall. These devices lack compatibility with a wide variety of test pieces. For example, the test platform specifically designed for simplified flat panels on the liner wall has a thin test chamber that cannot accommodate other types of test pieces. This results in poor compatibility and versatility. Summary of the Invention

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

[0005] To this end, embodiments of the present invention provide a gas turbine component cooling efficiency testing device and system with good compatibility, low testing cost, and simple process.

[0006] A gas turbine component cooling efficiency testing device according to an embodiment of the present invention comprises:

[0007] A box body, the box body having an inner cavity, a first air inlet, an air outlet and a cooling port connected to the inner cavity are provided on the side wall of the box body, and the inner cavity of the box body is used to place the component to be tested;

[0008] an air intake assembly connected to the first air inlet of the box body to transport hot air into the box body;

[0009] an air outlet component connected to the air outlet of the box body to discharge the gas in the box body;

[0010] a cooling cover having a cavity, the cooling cover being connected to the cooling port of the box so that the cooling port communicates with the cavity, a second air inlet, a third air inlet, and a fourth air inlet being provided on a side wall of the cooling cover, the second air inlet being coaxially arranged with the cooling port along a first direction, and the third air inlet and the fourth air inlet being coaxially arranged along a second direction;

[0011] The first direction and the second direction are orthogonal to each other.

[0012] The gas turbine component cooling efficiency test device of an embodiment of the present invention is arranged through multiple air inlets on the cooling cover. For different components to be tested, air can be introduced and exhausted through different air inlets on the cooling cover to adjust the flow direction of the cold air, thereby meeting the testing of different components to be tested, meeting test measurements for different purposes, and improving the compatibility and versatility of the test device.

[0013] In some embodiments, the box has a window, and a transparent glass plate is provided at the window, so that the detection device can measure data through the glass plate.

[0014] In some embodiments, the number of the windows is multiple, and the multiple windows are arranged on multiple sides of the box;

[0015] And / or, the glass plates are detachably connected to the box body, and at least some of the glass plates have different light transmission wavelength ranges.

[0016] In some embodiments, the first air inlet and the air outlet are coaxially arranged along the second direction;

[0017] And / or, further comprising a first heating component, the first heating component being disposed in the box body, the first heating component being used to heat the gas in the box body, or the first heating component being used to contact with a component to be tested to heat the component to be tested;

[0018] And / or, a mounting portion corresponding to the component to be measured is provided in the inner cavity, and a size of the inner cavity is larger than the component to be measured.

[0019] In some embodiments, the air intake assembly includes a coaxially arranged air intake cylinder and a rectifying cylinder, the outlet end of the air intake cylinder is connected to the inlet end of the rectifying cylinder, and the outlet end of the rectifying cylinder is connected to the first air inlet of the box;

[0020] The cross-sectional size of the air intake cylinder gradually decreases from one end away from the rectification cylinder to one end close to the rectification cylinder. A rectification plate, a first detection component and a PIV particle spreader are arranged in the rectification cylinder.

[0021] In some embodiments, the gas outlet assembly includes a coaxially arranged rear measuring cylinder and an exhaust cylinder, the inlet end of the rear measuring cylinder is connected to the exhaust port of the box, and the outlet end of the rear measuring cylinder is connected to the inlet end of the exhaust cylinder;

[0022] The cross-sectional size of the exhaust cylinder gradually decreases from one end close to the rear measuring cylinder to one end away from the rear measuring cylinder, and a second detection component is provided in the rear measuring cylinder.

[0023] In some embodiments, an exhaust pipe is further included, wherein the exhaust pipe is connected to the outlet end of the exhaust cylinder, and a back pressure regulating valve and a silencer are provided on the exhaust pipe.

[0024] A gas turbine component cooling efficiency testing system according to an embodiment of the present invention includes:

[0025] A testing device, wherein the testing device is the gas turbine component cooling efficiency testing device described in the above embodiment;

[0026] an air supply device, the air supply device comprising an air source, a main air supply assembly, and a cold air supply assembly, wherein one end of the main air supply assembly is connected to the air source and the other end is connected to the air inlet assembly, and one end of the cold air supply assembly is connected to the air source and the other end is connected to one of the second air inlet, the third air inlet, and the fourth air inlet;

[0027] A detection device, the detection device is used to obtain data parameters in the test device;

[0028] The main air supply assembly is used to deliver hot air of preset temperature and preset flow into the box, and the cold air supply assembly is used to deliver cooling medium of preset flow into the cooling cover to simulate the working conditions of the component to be tested in the working state.

[0029] In some embodiments, a carbon dioxide supply assembly is further included, wherein the carbon dioxide supply assembly is connected to one of the second air inlet, the third air inlet, and the fourth air inlet of the cold air supply assembly;

[0030] And / or, the air source includes a compressor and an air storage tank, the compressed air generated by the compressor is stored in the air storage tank, and the air storage tank is connected to the main air supply assembly and the cold air supply assembly;

[0031] And / or, the main gas supply assembly includes a main gas supply pipeline, a first valve group and a second heating component, the first valve group and the second heating component are both connected to the main gas supply pipeline, and the first valve group includes a plurality of regulating valves arranged in parallel and of different specifications to adjust the airflow parameters in the main gas supply pipeline according to working conditions;

[0032] And / or, the cold air supply assembly includes a cold air supply pipeline and a second valve group, the second valve group is connected to the cold air supply pipeline, and the second valve group includes a plurality of regulating valves arranged in parallel and of different specifications to adjust airflow parameters in the cold air supply pipeline according to working conditions;

[0033] And / or, the detection device includes at least one of a thermocouple, an air pressure scanning valve, a pressure sensitive paint measuring device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimeter, and a laser Doppler velocimeter.

[0034] In some embodiments, the cold air supply assembly further comprises a first flow meter, a first switch valve and a third heating component, and the main air supply assembly further comprises a second flow meter;

[0035] And / or, the carbon dioxide supply assembly includes a carbon dioxide storage tank, a carbon dioxide supply pipeline, a pressure reducing valve, a fourth heating component and a second switch valve, and the pressure reducing valve, the fourth heating component and the second switch valve are all connected to the carbon dioxide supply pipeline. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 Schematic diagram of a gas turbine component cooling efficiency testing device according to an embodiment of the present invention.

[0037] Figure 2 Schematic diagram of a gas turbine component cooling efficiency testing system according to an embodiment of the present invention.

[0038] Figure 3 Schematic diagram of the airflow of the cooling cover in an embodiment of the present invention.

[0039] Figure 4 FIG. 4 is a schematic diagram of airflow in a cooling casing according to another embodiment of the present invention.

[0040] Figure 5 FIG. 1 is a schematic diagram of the airflow of the cooling cover in another embodiment of the present invention.

[0041] Figure 6 Schematic diagram of the arrangement of a simplified flat-plate test piece of a flame tube in an embodiment of the present invention.

[0042] Figure 7 Schematic diagram of the layout of the turbine stator blade cooling test piece in an embodiment of the present invention.

[0043] Figure 8 It is a schematic diagram of the layout of the actual structure test piece of the flame tube in an embodiment of the present invention.

[0044] Reference numerals:

[0045] 100. Gas turbine component cooling efficiency test device; 200. Gas turbine component cooling efficiency test system;

[0046] 1. Box body; 11. First air inlet; 12. Air outlet; 13. Cooling port; 14. Mounting portion; 15. Window; 16. Glass plate;

[0047] 2. Air intake assembly; 21. Air intake cylinder; 22. Rectifier cylinder; 23. Rectifier plate;

[0048] 3. Air outlet assembly; 31. Rear measuring cylinder; 32. Exhaust cylinder; 33. Exhaust pipe; 34. Back pressure regulating valve; 35. Silencer component;

[0049] 4. Cooling cover; 41. Second air inlet; 42. Third air inlet; 43. Fourth air inlet;

[0050] 5. Main gas supply assembly; 51. Main gas supply pipeline; 52. First valve group; 53. Second heating component; 54. Second flow meter;

[0051] 6. Cooling air supply assembly; 61. Cooling air supply pipeline; 62. Second valve group; 63. First flow meter; 64. First switch valve; 65. Third heating component;

[0052] 7. Carbon dioxide gas supply assembly; 71. Carbon dioxide gas supply pipeline; 72. Pressure reducing valve; 73. Fourth heating component; 74. Second on-off valve; 75. Carbon dioxide storage tank;

[0053] 81. Compressor; 82. Gas storage tank;

[0054] 91. Simplified flat plate test piece for flame tube; 92. Turbine vane cooling test piece; 93. Real structure test piece for flame tube;

[0055] 10. Testing equipment. DETAILED DESCRIPTION

[0056] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0057] See also Figures 1 to 8 The gas turbine component cooling efficiency testing device 100 according to an embodiment of the present invention includes a box body 1, an air inlet assembly 2, an air outlet assembly 3 and a cooling cover 4.

[0058] The housing 1 has an inner cavity. The side walls of the housing 1 are provided with a first air inlet 11, an air outlet 12, and a cooling port 13 communicating with the inner cavity. The inner cavity of the housing 1 is used to house components to be tested. The components to be tested in the embodiments of the present invention can be suitable for gas turbine turbine vane cooling test pieces 92, combustion chamber flame tube actual structure test pieces 93, and combustion chamber flame tube simplified flat plate test pieces 91. The space within the housing 1 is larger than the required dimensions of the components to be tested, ensuring that different components to be tested can be placed within the inner cavity. A mounting portion 14 corresponding to the components to be tested can also be provided within the inner cavity to facilitate securing the components to be tested and prevent them from shaking or tipping over due to airflow.

[0059] After the component to be tested is placed in the box 1, it corresponds to the cooling port 13, so that the cold air from the cooling port 13 can be used to cool the component to be tested. According to different testing methods for 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 impact cooling test, or the cold air can flow through the component to be tested into the box 1 and then be discharged from the air outlet 12, or the cold air at the cooling port 13 can contact the cooling surface of the component to be tested for heat exchange.

[0060] The air inlet assembly 2 is connected to the first air inlet 11 of the housing 1 to deliver hot air into the housing 1. The air outlet assembly 3 is connected to the air outlet 12 of the housing 1 to exhaust the gas within the housing 1. The hot air can be heated air. The flow rate, flow velocity, temperature, and other parameters of the hot air can be adjusted according to the actual operating conditions. When the hot air flows through the component under test, the environmental conditions of the component under actual operating conditions can be simulated. The gas within the housing 1 flows out of the housing 1 through the air outlet 12 and is discharged through the air outlet assembly 3.

[0061] In the embodiment of the present invention, the first air inlet 11 and the air outlet 12 of the box body 1 can be coaxially arranged relative to each other, and the first air inlet 11 and the air outlet 12 can be coaxially arranged relative to each other along the second direction, thereby avoiding obstruction of the airflow in the box body 1 and improving the smooth flow of the airflow in the box body 1.

[0062] The cooling housing 4 has a cavity and is connected to the cooling port 13 of the housing 1 so that the cooling port 13 communicates with the cavity. A second air inlet 41, a third air inlet 42, and a fourth air inlet 43 are provided on the sidewalls of the cooling housing 4. The second air inlet 41 and the cooling port 13 are coaxially arranged along a first direction, while the third air inlet 42 and the fourth air inlet 43 are coaxially arranged along a second direction. The first and second directions are orthogonal to each other. The first direction is the vertical direction shown in the figure, and the second direction is the horizontal direction shown in the figure.

[0063] Any of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43 can be used as an inlet for cold air to enter the cooling housing 4. Each of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43 is provided with a flange plate to facilitate connection with the corresponding inlet and outlet pipes. Of course, when the corresponding air inlet on the cooling housing 4 is not needed, it can be blocked with a flange blind cover.

[0064] For example, the second air inlet 41 is used as the inlet of cold air, so that the cold air entering the cooling cover 4 can flow directly to the cooling port 13 and impact the component to be tested, thereby performing an impact cooling test. Figure 3As shown, the third air inlet 42 serves as the inlet of cold air, and the fourth air inlet 43 serves as the outlet of cold air. When the cold air flows through the cooling cover 4, the cold air contacts the cooling surface of the component to be tested for heat exchange and cooling. The flow direction of the cold air is the same as that of the hot air in the box 1, which is used to simulate the cooling of the axial flow combustion chamber. For another example, Figure 5 As shown, the fourth air inlet 43 serves as the inlet of cold air, and the third air inlet 42 serves as the outlet of cold air. When the cold air flows through the cooling cover 4, the cold air contacts the cooling surface of the component to be tested for heat exchange and cooling. The flow direction of the cold air is opposite to the flow direction of the hot air in the box 1, which is used to simulate the cooling of the annular tube combustion chamber or the turboprop recirculation combustion chamber of a heavy-duty burner. For another example, Figure 4 As shown, the second air inlet 41 , the third air inlet 42 or the fourth air inlet 43 serves as an inlet for cold air. The cold air flows through the component to be tested into the box 1 and then flows out through the air outlet 12 of the box 1 .

[0065] The gas turbine component cooling efficiency test device 100 of the embodiment of the present invention is arranged through multiple air inlets on the cooling cover 4. For different components to be tested, air can be introduced and exhausted through different air inlets on the cooling cover 4 to adjust the flow direction of the cold air, thereby meeting the testing of different components to be tested, meeting test measurements for different purposes, and improving the compatibility and versatility of the test device.

[0066] The following describes a gas turbine component cooling efficiency testing device 100 according to some specific embodiments of the present invention.

[0067] like Figures 1 to 8 As shown, a gas turbine component cooling efficiency testing device 100 according to an embodiment of the present invention includes a housing 1 , an air inlet assembly 2 , an air outlet assembly 3 and a cooling cover 4 .

[0068] The housing 1 has an inner cavity. The side walls of the housing 1 are provided with a first air inlet 11, an air outlet 12, and a cooling port 13 that are in communication with the inner cavity. The inner cavity of the housing 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 a turbine stator cooling test piece 91, a combustion chamber flame tube real structure test piece 93, a combustion chamber flame tube simplified flat plate test piece 91, etc. of a gas turbine. The spatial dimensions within the housing 1 are larger than the size requirements of the component to be tested, thereby ensuring that different components to be tested can be placed in the inner cavity. A mounting portion 14 corresponding to the component to be tested can also be provided in the inner cavity. The component to be tested can be fixed to the housing 1 by bolts or other connecting parts, which facilitates the fixation of the component to be tested and prevents shaking or tipping due to the influence of airflow.

[0069] 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 measure data through the glass plate 16 .

[0070] There are multiple windows 15, and multiple windows 15 are arranged on multiple sides of the box body 1. For example, the box body 1 is a hexahedron, three of which are respectively arranged with the first air inlet 11, the air outlet 12 and the cooling port 13, and the other three sides can be arranged with windows 15.

[0071] Glass plates 16 are detachably attached to housing 1, with at least some of the glass plates 16 having different transmittance wavelength ranges. The detection device can be at least one of a thermocouple, a pressure scanner, a pressure-sensitive paint measurement device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimeter, or a laser Doppler velocimeter. To facilitate different optical measurement methods, different glass plates 16 can be replaced to accommodate lasers of different wavelengths.

[0072] The embodiment of the present invention is compatible with various testing methods such as thermosensitive liquid crystal (TLC), pressure sensitive paint (PSP), infrared thermal imager, particle image velocimetry (PIV), laser Doppler velocimetry (LDV), thermocouple, etc., and has better practicality.

[0073] After the component to be tested is placed in the box 1, it corresponds to the cooling port 13, so that the cold air from the cooling port 13 can be used to cool the component to be tested. According to different testing methods for 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 impact cooling test, or the cold air can flow through the component to be tested into the box 1 and then be discharged from the air outlet 12, or the cold air at the cooling port 13 can contact the cooling surface of the component to be tested for heat exchange.

[0074] The air intake assembly 2 is connected to the first air intake port 11 of the housing 1 to deliver hot air into the housing 1. Specifically, the air intake assembly 2 includes a coaxially arranged air intake cylinder 21 and a rectifying cylinder 22. The outlet end of the air intake cylinder 21 is connected to the inlet end of the rectifying cylinder 22, and the outlet end of the rectifying cylinder 22 is connected to the first air intake port 11 of the housing 1. The cross-sectional dimensions of the air intake cylinder 21 gradually decrease from the end away from the rectifying cylinder 22 to the end closer to the rectifying cylinder 22. The air intake cylinder 21 has a generally frustum-shaped shape, which increases the airflow velocity as it flows through the air intake cylinder 21. The rectifying cylinder 22 is in the shape of a column with a uniform cross-section. A rectifying plate 23, a first detection component, and a PIV particle spreader are provided inside the rectifying cylinder 22. The rectifying plate 23 may be a rectifying grid plate, which can rectify the airflow passing through the rectifying cylinder 22. By changing the flow velocity and direction of the fluid, the occurrence of turbulence is reduced, thereby reducing energy loss and improving the quality of the hot air flowing into the inner cavity of the box 1. The first detection component may be a temperature, flow, pressure, or other sensor used to detect gas parameters. The PIV particle spreader can spread tracer particles in the fluid to measure the flow field velocity using particle image velocimetry (PIV).

[0075] The gas outlet assembly 3 is connected to the gas outlet 12 of the housing 1 to discharge the gas in the housing 1. Specifically, the gas outlet assembly 3 includes a coaxially arranged rear measuring cylinder 31 and an exhaust cylinder 32. The inlet end of the rear measuring cylinder 31 is connected to the exhaust port of the housing 1, and the outlet end of the rear measuring cylinder 31 is connected to the inlet end of the exhaust cylinder 32. The cross-sectional size of the exhaust cylinder 32 gradually decreases from the end close to the rear measuring cylinder 31 to the end away from the rear measuring cylinder 31. A second detection component is provided in the rear measuring cylinder 31. The second detection component can be a sensor such as temperature, flow, and pressure, which is used to detect the parameters of the gas flowing out of the housing 1. The rear measuring cylinder 31 can be a cylindrical shape with a uniform cross-section, and the exhaust cylinder 32 can be a frustum-shaped. The cross-sectional size of the exhaust cylinder 32 gradually increases along the airflow direction, which can reduce the exhaust speed and reduce noise.

[0076] The hot air can be heated air. Parameters such as the flow rate, flow velocity, and temperature of the hot air can be adjusted according to actual operating conditions. When the hot air flows through the component under test, it simulates the environmental conditions of the component under actual operating conditions. The gas within the housing 1 flows out of the housing 1 through the outlet 12 and is discharged through the outlet assembly 3.

[0077] The gas turbine component cooling efficiency testing apparatus 100 according to an embodiment of the present invention includes a first heating element, which is an electric heater and is disposed within the housing 1. The first heating element is used to heat the gas within the housing 1 or to contact the component under test to heat the component under test. This better simulates operating temperatures and improves the accuracy and reliability of the test.

[0078] The exhaust assembly 3 also includes an exhaust pipe 33, which is connected to the outlet end of the exhaust cylinder 32. The exhaust pipe 33 is provided with a back-pressure regulating valve 34 and a silencer 35. The back-pressure regulating valve 34 can effectively control and stabilize the air pressure parameters within the box 1, and the silencer 35 can reduce exhaust noise to avoid sound pollution to the surrounding environment.

[0079] In the embodiment of the present invention, the first air inlet 11 and the air outlet 12 of the box body 1 can be coaxially arranged relative to each other, and the first air inlet 11 and the air outlet 12 can be coaxially arranged relative to each other along the second direction, thereby avoiding obstruction of the airflow in the box body 1 and improving the smooth flow of the airflow in the box body 1.

[0080] The cooling housing 4 has a cavity and is connected to the cooling port 13 of the housing 1 so that the cooling port 13 communicates with the cavity. A second air inlet 41, a third air inlet 42, and a fourth air inlet 43 are provided on the sidewalls of the cooling housing 4. The second air inlet 41 and the cooling port 13 are coaxially arranged along a first direction, while the third air inlet 42 and the fourth air inlet 43 are coaxially arranged along a second direction. The first and second directions are orthogonal to each other. The first direction is the vertical direction shown in the figure, and the second direction is the horizontal direction shown in the figure.

[0081] Any of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43 can be used as an inlet for cold air to enter the cooling housing 4. Each of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43 is provided with a flange to facilitate connection with the corresponding inlet and outlet pipes. Of course, when the corresponding air inlet on the cooling housing 4 is not needed, it can be blocked with a flange blind cover.

[0082] For example, the second air inlet 41 serves as an inlet for cold air, and the cold air entering the cooling housing 4 can flow directly to the cooling port 13 and impact the component to be tested, thereby performing an impact cooling test.

[0083] For example, Figure 3 As shown, the third air inlet 42 serves as the inlet of cold air, and the fourth air inlet 43 serves as the outlet of cold air. When the cold air flows through the cooling cover 4, the cold air contacts the cooling surface of the component to be tested for heat exchange cooling. The flow direction of the cold air is the same as the flow direction of the hot air in the box 1, which is used to simulate the cooling of the axial flow combustion chamber.

[0084] For example, Figure 5 As shown, the fourth air inlet 43 serves as the inlet of cold air, and the third air inlet 42 serves as the outlet of cold air. When the cold air flows through the cooling cover 4, the cold air contacts the cooling surface of the component to be tested for heat exchange and cooling. The flow direction of the cold air is opposite to the flow direction of the hot air in the box 1, which is used to simulate the cooling of the annular tube combustion chamber or the turboprop recirculation combustion chamber of a heavy-duty burner.

[0085] For example, Figure 4 As shown, the second air inlet 41 , the third air inlet 42 or the fourth air inlet 43 serves as an inlet for cold air. The cold air flows through the component to be tested into the box 1 and then flows out through the air outlet 12 of the box 1 .

[0086] The gas turbine component cooling efficiency test device 100 of the embodiment of the present invention is arranged through multiple air inlets on the cooling cover 4. For different components to be tested, air can be introduced and exhausted through different air inlets on the cooling cover 4 to adjust the flow direction of the cold air, thereby meeting the testing of different components to be tested, meeting test measurements for different purposes, and improving the compatibility and versatility of the test device.

[0087] like Figures 2 to 8The gas turbine component cooling efficiency testing system 200 according to an embodiment of the present invention includes a testing device, an air supply device and a detection device 10.

[0088] The test device is the gas turbine component cooling efficiency test device 100 according to the above embodiment.

[0089] The air supply device includes an air source, a main air supply component 5 and a cold air supply component 6. One end of the main air supply component 5 is connected to the air source, and the other end is connected to the air intake component 2. One end of the cold air supply component 6 is connected to the air source, and the other end is connected to one of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43.

[0090] The air source includes a compressor 81 and an air tank 82. The compressed air generated by the compressor 81 is stored in the air tank 82, which is connected to the main air supply assembly 5 and the cold air supply assembly 6. The air tank 82 has a pressure stabilizing effect, which can avoid the problem of unstable air pressure caused by the operating fluctuations of the compressor 81.

[0091] The detection device 10 is used to obtain data parameters from the test device. The detection device 10 can include at least one of a thermocouple, an air pressure scanning valve, a pressure-sensitive paint measuring device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimeter, or a laser Doppler velocimeter. Depending on the test application, the airflow parameters and direction of the test device are adjusted and the corresponding detection device 10 is selected.

[0092] The main air supply assembly 5 is used to deliver hot air of preset temperature and preset flow into the box body 1, and the cold air supply assembly 6 is used to deliver cooling medium of preset flow into the cooling cover 4 to simulate the working conditions of the component to be tested in the working state.

[0093] The following describes a gas turbine component cooling efficiency testing system 200 according to some specific embodiments of the present invention.

[0094] like Figures 2 to 8 As shown, a gas turbine component cooling efficiency testing system 200 includes a testing device, an air supply device, a detection equipment 10 and a carbon dioxide supply assembly 7.

[0095] The test device is the gas turbine component cooling efficiency test device 100 according to the above embodiment.

[0096] The air supply device includes an air source, a main air supply component 5 and a cold air supply component 6. One end of the main air supply component 5 is connected to the air source, and the other end is connected to the air intake component 2. One end of the cold air supply component 6 is connected to the air source, and the other end is connected to one of the second air inlet 41, the third air inlet 42, and the fourth air inlet 43.

[0097] The air source includes a compressor 81 and an air tank 82. The compressed air generated by the compressor 81 is stored in the air tank 82, which is connected to the main air supply assembly 5 and the cold air supply assembly 6. The air tank 82 has a pressure stabilizing effect, which can avoid the problem of unstable air pressure caused by the operating fluctuations of the compressor 81.

[0098] The main gas supply assembly 5 includes a main gas supply pipeline 51, a first valve group 52, a second heating component 53 and a second flow meter 54. The first valve group 52 and the second heating component 53 are both connected to the main gas supply pipeline 51. The first valve group 52 includes a plurality of regulating valves arranged in parallel and of different specifications to adjust the airflow parameters in the main gas supply pipeline 51 according to working conditions.

[0099] There may be multiple second heating components 53 , and multiple second heating components 53 are connected in series with multiple control valves and then arranged in parallel to form a main gas heating assembly.

[0100] The cold air supply assembly 6 includes a cold air supply pipeline 61, a second valve group 62, a first flow meter 63, a first switch 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 and of different specifications to adjust the airflow parameters in the cold air supply pipeline 61 according to working conditions.

[0101] 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 to adjust the temperature of the gas delivered to the cooling cover 4 to make it more compatible with the actual working conditions and improve the scope of application.

[0102] The first valve group 52 and the second valve group 62 each include three regulating valves, large, medium and small, for precisely controlling the intake air flow rate. Precise regulation can be achieved under different flow conditions, and the practicality is good.

[0103] The carbon dioxide supply assembly 7 is connected to one of the second air inlet 41, third air inlet 42, or fourth air inlet 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 element 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 element 73, and the second on-off valve 74 are all connected to the carbon dioxide supply pipeline 71. The fourth heating element 73 can adjust the temperature of the carbon dioxide working medium.

[0104] The second heating element 53, the third heating element 65 and the fourth heating element 73 of the embodiment of the present invention can all be electric heaters, which work independently to adjust the temperature of the working medium in the corresponding pipelines.

[0105] In the embodiment of the present invention, carbon dioxide and air are used as two cooling working fluids. Carbon dioxide as the working fluid 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 equipment 10 in application.

[0106] Before connecting to the cooling housing 4, the cold air supply line 61 is combined with the carbon dioxide supply line 71 through a three-way pipe to supply air. Air or carbon dioxide is selected by the first on-off valve 64 and the second on-off valve 74. When performing PSP measurements, carbon dioxide is introduced into the cooling housing 4 by opening the second on-off valve 74. When performing other tests, air is introduced into the cooling housing 4 by opening the first on-off valve 64. The second air inlet 41, the third air inlet 42, and the fourth air inlet 43 on the cooling housing 4 can all serve as cold air inlets and outlets. Of course, the cooling housing 4 can be equipped with no cold air outlets, allowing cold air to enter the housing 1 and then be discharged. For example, when performing film cooling or divergent cooling tests, one of the three air inlets on the cooling housing 4 serves as the cold air inlet, while the other two are sealed with blind flange covers. All cold air is then introduced into the housing 1 through the film holes of the test piece (part to be tested) and then discharged with the main air. For another example, when performing an impact cooling test, the second air inlet 41 is used as the inlet of cold air, and the third air inlet 42 and / or the fourth air inlet 43 are used as the outlet of cold air. The cold air is discharged through the outlet after cooling the test piece.

[0107] The detection device 10 is used to obtain data parameters from the test device. The detection device 10 can include at least one of a thermocouple, an air pressure scanning valve, a pressure-sensitive paint measuring device, a thermosensitive liquid crystal device, an infrared thermal imager, a particle image velocimeter, or a laser Doppler velocimeter. Depending on the test application, the airflow parameters and direction of the test device are adjusted and the corresponding detection device 10 is selected.

[0108] The main air supply assembly 5 is used to deliver hot air of preset temperature and preset flow into the box body 1, and the cold air supply assembly 6 is used to deliver cooling medium of preset flow into the cooling cover 4 to simulate the working conditions of the component to be tested in the working state.

[0109] The embodiment of the present invention is compatible with different types of component test pieces and test methods on the same test platform, simplifying the test cost and process. The embodiment of the present invention provides a test box 1 with good compatibility, which is compatible with turbine stator cooling test pieces 92, combustion chamber flame tube simplified flat plate test pieces 91, flame tube real structure test pieces 93, etc. Through the cold air supply assembly 6 with replaceable interfaces, the direction of the cold air interface and the working medium can be replaced to meet different test requirements. Carbon dioxide or cold air can be connected or sealed to achieve compatibility with various test methods such as thermosensitive liquid crystal (TLC), pressure sensitive paint (PSP), infrared thermal imager, particle image velocimetry (PIV), laser Doppler velocimetry (LDV), thermocouples, etc. without replacing the main test platform equipment.

[0110] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations 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 element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0111] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0112] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0113] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0114] In the present invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples" mean 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 representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification, as well as features of different embodiments or examples, unless they are mutually inconsistent.

[0115] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A gas turbine component cooling efficiency test device, characterized in that: include: A box body, the box body having an inner cavity, a first air inlet, an air outlet and a cooling port connected to the inner cavity are provided on the side wall of the box body, and 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 transport hot air into the box body; an air outlet component connected to the air outlet of the box body to discharge the gas in the box body; a cooling cover having a cavity, the cooling cover being connected to the cooling port of the box so that the cooling port communicates with the cavity, a second air inlet, a third air inlet, and a fourth air inlet being provided on a side wall of the cooling cover, the second air inlet being coaxially arranged with the cooling port along a first direction, and the third air inlet and the fourth air inlet being coaxially arranged along a second direction; The first direction and the second direction are orthogonal to each other.

2. The gas turbine component cooling efficiency testing device according to claim 1, characterized in that: The box body has a viewing window, and a transparent glass plate is provided at the viewing window so that the detection equipment can measure data through the glass plate.

3. The gas turbine component cooling efficiency testing device according to claim 2, characterized in that: There are multiple viewing windows, and the multiple viewing windows are arranged on multiple sides of the box; And / or, the glass plates are detachably connected to the box body, and at least some of the glass plates have different light transmission wavelength ranges.

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

5. The gas turbine component cooling efficiency testing device according to claim 1, characterized in that: The air intake assembly includes an air intake cylinder and a rectifying cylinder arranged coaxially, the outlet end of the air intake cylinder is connected to the inlet end of the rectifying cylinder, and the outlet end of the rectifying cylinder is connected to the first air inlet of the box; The cross-sectional size of the air intake cylinder gradually decreases from one end away from the rectification cylinder to one end close to the rectification cylinder. A rectification plate, a first detection component and a PIV particle spreader are arranged in the rectification cylinder.

6. The gas turbine component cooling efficiency testing device according to claim 1, characterized in that: The gas outlet assembly includes a coaxially arranged rear measuring cylinder and an exhaust cylinder, the inlet end of the rear measuring cylinder is connected to the exhaust port of the box, and the outlet end of the rear measuring cylinder is connected to the inlet end of the exhaust cylinder; The cross-sectional size of the exhaust cylinder gradually decreases from one end close to the rear measuring cylinder to one end away from the rear measuring cylinder, and a second detection component is provided in the rear measuring cylinder.

7. The gas turbine component cooling efficiency testing device according to claim 6, characterized in that: It also includes an exhaust pipe, which is connected to the outlet end of the exhaust cylinder. The exhaust pipe is provided with a back pressure regulating valve and a silencer component.

8. A gas turbine component cooling efficiency test system, characterized in that: include: A testing device, wherein the testing device is a gas turbine component cooling efficiency testing device according to any one of claims 1 to 7; an air supply device, the air supply device comprising an air source, a main air supply assembly, and a cold air supply assembly, wherein one end of the main air supply assembly is connected to the air source and the other end is connected to the air inlet assembly, and one end of the cold air supply assembly is connected to the air source and the other end is connected to one of the second air inlet, the third air inlet, and the fourth air inlet; A detection device, the detection device is used to obtain data parameters in the test device; The main air supply assembly is used to deliver hot air of preset temperature and preset flow into the box, and the cold air supply assembly is used to deliver cooling medium of preset flow into the cooling cover to simulate the working conditions of the component to be tested in the working state.

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

10. The gas turbine component cooling efficiency testing system according to claim 9, characterized in that: The cold air supply assembly further includes a first flow meter, a first switch valve and a third heating component, and the main air supply assembly further includes a second flow meter; And / or, the carbon dioxide supply assembly includes a carbon dioxide storage tank, a carbon dioxide supply pipeline, a pressure reducing valve, a fourth heating component and a second switch valve, and the pressure reducing valve, the fourth heating component and the second switch valve are all connected to the carbon dioxide supply pipeline.

Images