A turbine blade test apparatus

Abstract

The present application relates to the technical field of aero-engine, and discloses a turbine blade testing device, which comprises a turbine testing piece, a testing bench exhaust pipe coaxially arranged with the turbine testing piece, a moving mechanism in transmission connection with the testing bench exhaust pipe, an adjusting valve core installed in the testing bench exhaust pipe, a plurality of cooling holes formed in the adjusting valve core, and a water supply assembly in fluid communication with the cooling holes and used for providing cooling water. During the testing process, the cooling water provided by the water supply assembly can flow out of the cooling holes in the adjusting valve core and infiltrate the outer surface of the adjusting valve core under the action of high-temperature gas flow, so as to form a cooling protective layer, block the direct contact of the high-temperature gas with the adjusting valve core, and cool the high-temperature gas. The adjusting valve core and the water supply assembly can not be made of high-temperature alloy steel, so that the cost is greatly reduced.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically to a turbine blade testing device. Background Technology

[0002] As a core hot-end component of aero-engines and gas turbines, turbine blades operate in extreme environments of high temperature, high pressure, and high speed. The material properties and cooling effects directly determine the engine's efficiency and reliability. With the development of aero-engine design technology, the temperature and pressure in front of the turbine are constantly increasing. Currently, the turbine inlet temperature of advanced aero-engines has reached 1800K~2000K, far exceeding the material's limit operating temperature. Therefore, extensive experimental verification to meet the turbine inlet / outlet temperature / pressure conditions is required to support the design of turbine blades.

[0003] Both turbine blade performance tests and heat transfer tests require adjustment of the blade outlet back pressure to simulate the inlet and outlet pressure ratio conditions. Currently, the conventional method for adjusting turbine blade outlet back pressure on test benches is to install a regulating valve on the exhaust section. The valve opening changes the flow area at the turbine outlet, thus regulating the back pressure. For high-temperature tests, the high-temperature exhaust gas at the blade outlet needs to be sprayed and cooled before flowing through the exhaust regulating valve. The regulating valve's temperature resistance is generally below 600℃. After the exhaust gas at the turbine blade outlet is cooled to below 600℃ by spraying water, it flows through the regulating valve and is discharged. The valve body and its sealing device are easily damaged by the water-air mixture. Currently, valves in the exhaust section of high-temperature turbine test equipment are generally consumable parts, requiring periodic maintenance or replacement. Regulating valves for 400℃–600℃ are high-temperature valves, requiring custom orders and incurring higher costs.

[0004] It is evident that during high-temperature testing in related technologies, the blade outlet back pressure adjustment components are susceptible to corrosion from high-temperature combustion gases, requiring frequent replacement and incurring high costs. Summary of the Invention

[0005] In view of this, the present invention provides a turbine blade testing device to solve the problem that the blade outlet back pressure regulating component is easily corroded by high-temperature combustion gas during high-temperature testing, resulting in high replacement costs.

[0006] In a first aspect, the present invention provides a turbine blade testing apparatus, comprising:

[0007] A turbine test piece, consisting of a housing and turbine blades;

[0008] The test bench exhaust pipe is coaxially arranged with the turbine test piece, and one end of the test bench exhaust pipe is sleeved around the outer periphery of the housing;

[0009] The moving mechanism is connected to the exhaust pipe of the test bench via a transmission mechanism;

[0010] An adjusting valve core is installed inside the exhaust pipe of the test bench; and the adjusting valve core is provided with multiple cooling holes; the moving mechanism drives the exhaust pipe of the test bench to move axially to adjust the flow area between the adjusting valve core and the housing;

[0011] A water supply assembly, in fluid communication with the cooling holes, is used to provide cooling water.

[0012] Beneficial effects: When the test bench exhaust pipe moves axially via the moving mechanism, the regulating valve core moves along with the test bench exhaust pipe, directly changing the airflow area between the regulating valve core and the housing, achieving precise and convenient adjustment of the turbine blade back pressure. The test bench exhaust pipe is coaxially arranged with the turbine test piece, ensuring the uniformity of the flow area change during adjustment, improving the accuracy of back pressure adjustment, and adapting to the back pressure requirements of different test conditions of the turbine blade. Moreover, during the test, the cooling water provided by the water supply component can flow out from the cooling holes on the regulating valve core and wet the outer surface of the regulating valve core under the action of the high-temperature airflow, forming a cooling protective layer. This effectively absorbs the heat of the high-temperature combustion gas, prevents the high-temperature combustion gas from directly contacting the regulating valve core, continuously cools the regulating valve core, significantly reduces the high-temperature oxidation and erosion wear of the regulating valve core, effectively improves the temperature resistance of the regulating valve core, extends the life of the regulating valve core in high-temperature environments, eliminates the need for frequent replacement, and allows the regulating valve core and water supply component to be made without using high-temperature alloy steel, significantly reducing costs.

[0013] In one optional embodiment, the regulating valve core is provided with a hollow chamber, which is in communication with the cooling hole.

[0014] Beneficial effects: The regulating valve core features a hollow chamber connected to the cooling holes. Cooling water supplied by the water supply assembly first enters the hollow chamber for buffering and pressure equalization before flowing out synchronously from each cooling hole. This avoids uneven water distribution and localized flow interruptions caused by direct supply from a single hole, ensuring that all areas of the valve core's outer surface are wetted with cooling water. This achieves uniform cooling in all directions without dead zones, further improving cooling efficiency and enhancing resistance to high-temperature combustion gases. The hollow chamber allows for water flow distribution to all cooling holes with a single or a small number of water supply lines, eliminating the need for separate water supply lines for each cooling hole. This significantly simplifies the connection structure between the regulating valve core and the water supply assembly, reducing the difficulty of equipment assembly and maintenance.

[0015] In one optional embodiment, the regulating valve core includes:

[0016] The valve core is connected in communication with the water supply assembly;

[0017] A conical structure is disposed at one end of the valve core near the turbine test piece; the cooling hole is at least located in the conical structure.

[0018] Beneficial effects: The conical structure forms a suitable conical surface fit with the exhaust end flow channel of the turbine test piece housing. During axial movement, the flow area between the conical surface of the conical structure and the housing changes linearly and gradually. Compared with planar fit, this allows for stepless and precise fine-tuning of the turbine blade back pressure, adapting to the refined back pressure requirements of turbine blades under different test conditions and improving the accuracy of test data. During the test, the high-temperature combustion gas discharged from the turbine test piece first impacts the end of the regulating valve core closest to the housing, i.e., the conical structure area. This area is the core part where high-temperature erosion and thermal stress concentration occur. By opening cooling holes at least in the conical structure, cooling water can be precisely delivered to the critical area that needs cooling the most, avoiding waste caused by indiscriminate distribution of cooling water, significantly improving the utilization efficiency of cooling resources, and more effectively resisting the erosion and oxidation of the valve core by high-temperature combustion gas. In addition, the streamlined design of the conical structure can guide the high-temperature gas discharged from the turbine test piece, allowing the airflow to smoothly transition along the conical surface into the exhaust pipe of the test bench. This avoids airflow vortices and turbulence caused by the abrupt structure at the end of the valve core, reduces the impact of airflow disturbance on the working state of the turbine blades, ensures the operational stability of the turbine blades during the test, and reduces the deviation of test data caused by airflow disturbance.

[0019] In one alternative embodiment, the conical structure is provided with multiple rings of cooling holes at intervals from the bottom to the top of the cone.

[0020] Beneficial effects: Multiple rings of cooling holes are spaced along the entire conical surface from the apex to the bottom. Combined with the high-temperature core of the cone, this allows the cooling water to form a continuous and complete cooling water film from the apex to the bottom, completely covering all conical areas in contact with the combustion gases. This eliminates localized thermal weaknesses caused by missing cooling holes, effectively preventing direct contact between the high-temperature combustion gases and the conical surface, and comprehensively reducing the oxidation and erosion effects of the combustion gases on the conical structure. After the high-temperature combustion gases are discharged from the turbine test piece, they first rush directly to the apex and then flow along the conical surface to the bottom. The multiple rings of cooling holes arranged from the apex to the bottom allow the cooling water to form a multi-layered cooling water film in the same direction as the combustion gases after flowing out from the apex. This creates a fully contacting heat exchange state between the combustion gases and the water film, extending the contact time and path of gas-liquid heat exchange. In particular, it allows for sufficient heat exchange between the high-temperature combustion gases and cooling water in the core area of ​​the cone, significantly improving the cooling effect in the core area.

[0021] In one alternative implementation, the cooling holes in each ring are evenly distributed along the circumference of the conical structure.

[0022] Beneficial effects: The cooling holes are evenly distributed around the circumference of the conical structure, ensuring that cooling water flows out synchronously from the apex to the bottom of the cone, forming a continuous, uninterrupted cooling water film on the cone surface. This completely prevents direct erosion by high-temperature combustion gases caused by missing cooling holes in certain circumferential areas, ensuring a completely uniform cooling rate and intensity across all circumferential regions of the cone surface. This comprehensively blocks the circumferential erosion and oxidation of the conical structure by high-temperature combustion gases. The apex of the cone is the core area where high-temperature combustion gases directly impact; uneven cooling around the circumference can easily lead to localized temperature differences, resulting in concentrated circumferential thermal stress. The evenly distributed cooling holes around the circumference ensure a synchronous and uniform temperature drop across the cone surface, significantly reducing the circumferential thermal stress difference and preventing deformation or even cracking of the conical structure due to uneven circumferential thermal stress. This enhances the structural stability and fatigue resistance of the conical structure under high-temperature conditions.

[0023] In one optional implementation, the water supply assembly includes:

[0024] Water source;

[0025] An annular water passage is provided around the regulating valve core and connected to the water source;

[0026] A supporting water passage is provided between the annular water passage and the regulating valve core.

[0027] Beneficial effects: The annular water circuit surrounding the regulating valve core ensures uniform pressure and flow of the input cooling water circumferentially. Water is then supplied to the regulating valve core via the supporting water circuit, ensuring synchronous and equal delivery of cooling water to the internal hollow chamber. This works in conjunction with the multiple rings of cooling holes evenly distributed circumferentially on the conical structure, guaranteeing consistent cooling water velocity and flow rate at every circumferential position on the conical surface from the water supply source. This further enhances the uniform cooling effect circumferentially and completely eliminates circumferential cooling deviations. The cooling water output from the water source is first buffered and stabilized by the annular water circuit before being delivered via the supporting water circuit, effectively reducing pressure fluctuations caused by pipeline transport and water pressure changes during the water supply process, thus maintaining stable cooling water pressure input to the regulating valve core.

[0028] In one alternative embodiment, multiple supporting water channels are radially distributed between the regulating valve core and the annular water channel.

[0029] Beneficial effects: Multiple supporting water channels are arranged radially along the regulating valve core, which synchronously delivers the pressure-equalized cooling water in the annular water channel to the inside of the regulating valve core along the circumference, making the water supply pressure and flow rate at all positions around the regulating valve core completely consistent, completely eliminating the local cooling intensity difference in the conical surface, and making the cooling effect on the regulating valve core more uniform.

[0030] In one optional embodiment, an air inlet is formed between the test bench exhaust pipe and the housing, and outside air is adapted to enter the test bench exhaust pipe through the air inlet.

[0031] Beneficial effects: When the high-temperature exhaust gas from the turbine test piece enters the test bench's exhaust pipe, ambient air is simultaneously drawn in through the inlet and thoroughly mixed with the high-temperature gas. This directly reduces the overall temperature of the gas in the exhaust pipe, minimizing thermal erosion of the exhaust pipe's inner wall and reducing thermal radiation and convection on the regulating valve core. This enhances the valve core's cooling effect and further extends the high-temperature service life of the exhaust pipe and regulating valve core. Since the intake volume of ambient air can adaptively adjust to changes in gas flow rate and pressure within the exhaust pipe, when the gas flow rate is high and the back pressure is high, the air drawn in through the inlet can dilute the gas and increase the airflow within the exhaust pipe, enabling auxiliary fine-tuning of the back pressure. Simultaneously, the mixing of air and gas optimizes the airflow within the exhaust pipe, making back pressure adjustment more linear and stable. This complements the active back pressure adjustment of the regulating valve core, improving the overall accuracy and adaptability of back pressure adjustment and meeting the back pressure requirements of different turbine blade test conditions.

[0032] In one alternative implementation, the moving mechanism includes:

[0033] A movable support frame, wherein the exhaust pipe of the test bench is installed on the top of the movable support frame;

[0034] A drive mechanism is connected to the movable support and is used to provide driving force to the movable support.

[0035] Beneficial effects: The movable bracket provides a stable and rigid support for the exhaust pipe of the test bench, making the exhaust pipe and the regulating valve core an integrated load-bearing structure. When the drive mechanism drives the movable bracket, it can drive the exhaust pipe and the regulating valve core of the test bench to move synchronously along the axis, avoiding adjustment deviations caused by loose component connections or uneven force, ensuring precise changes in the flow area between the regulating valve core and the housing, and improving the accuracy and repeatability of back pressure adjustment.

[0036] In one alternative embodiment, the bottom of the movable support is provided with casters.

[0037] Beneficial effects: The rollers can significantly reduce the frictional resistance when the moving bracket moves axially. The drive mechanism only needs a small driving force to drive the moving bracket, the test bench exhaust pipe and the regulating valve core to move smoothly, effectively reducing the power loss of the drive mechanism. At the same time, it makes the axial movement of the back pressure adjustment smoother and avoids adjustment jamming and displacement deviation caused by excessive frictional resistance. Attached Figure Description

[0038] To more clearly illustrate the technical solutions in the specific embodiments or related technologies of the present invention, the drawings used in the description of the specific embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0039] Figure 1 This is a front cross-sectional view of a turbine blade testing device according to an embodiment of the present invention;

[0040] Figure 2 This is a schematic diagram of the working principle of the turbine blade testing device of the present invention;

[0041] Figure 3 for Figure 1 A partially enlarged schematic diagram of the turbine test piece, the test bench exhaust pipe, the regulating valve core, and the water supply assembly;

[0042] Figure 4 This is a three-dimensional structural diagram of a turbine blade testing device according to an embodiment of the present invention.

[0043] Explanation of reference numerals in the attached figures:

[0044] 1. Turbine test specimen;

[0045] 11. Shell;

[0046] 12. Turbine blades;

[0047] 2. Exhaust pipe of the test bench;

[0048] 21. Air intake;

[0049] 3. Moving mechanism;

[0050] 31. Mobile stand;

[0051] 32. Drive mechanism;

[0052] 33. Transmission mechanism;

[0053] 4. Adjusting valve core;

[0054] 41. Valve core body;

[0055] 42. Conical structure;

[0056] 421. Cooling holes;

[0057] 5. Water supply components;

[0058] 51. Circular waterway;

[0059] 52. Support waterways. Detailed Implementation

[0060] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0061] In the description of the invention, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0062] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0063] The following is combined Figures 1 to 4 The following describes embodiments of the present invention.

[0064] According to an embodiment of the present invention, in one aspect, a test apparatus for a turbine blade 12 is provided, comprising:

[0065] Turbine test piece 1, which is provided with a housing 11 and turbine blades 12;

[0066] The test bench exhaust pipe 2 is coaxially arranged with the turbine test piece 1, and one end of the test bench exhaust pipe 2 is sleeved on the periphery of the housing 11;

[0067] The moving mechanism 3 is connected to the exhaust pipe 2 of the test bench via a transmission mechanism;

[0068] The regulating valve core 4 is installed inside the exhaust pipe 2 of the test bench; and the regulating valve core 4 is provided with multiple cooling holes 421; the moving mechanism 3 drives the exhaust pipe 2 of the test bench to move axially to adjust the flow area between the regulating valve core 4 and the housing 11.

[0069] Water supply component 5 is in fluid communication with cooling hole 421 and is used to supply cooling water.

[0070] When the test bench exhaust pipe 2 moves axially via the moving mechanism 3, the regulating valve core 4 moves along with the test bench exhaust pipe 2, directly changing the airflow area between the regulating valve core 4 and the housing 11, achieving precise and convenient adjustment of the back pressure of the turbine blade 12. The test bench exhaust pipe 2 and the turbine test piece 1 are coaxially arranged to ensure the uniformity of the flow area change during the adjustment process, improve the accuracy of back pressure adjustment, and adapt to the back pressure requirements of different test conditions of the turbine blade 12. Moreover, during the test, the cooling water provided by the water supply component 5 can flow out from the cooling hole 421 on the regulating valve core 4 and wet the outer surface of the regulating valve core 4 under the action of the high-temperature airflow, forming a cooling protective layer. This layer effectively absorbs the heat of the high-temperature gas while preventing the high-temperature gas from directly contacting the regulating valve core 4, continuously cooling the regulating valve core 4, significantly reducing the high-temperature oxidation and erosion wear of the regulating valve core 4, effectively improving the temperature resistance of the regulating valve core 4, extending the life of the regulating valve core 4 in high-temperature environments, eliminating the need for frequent replacement, and because the temperature of the high-temperature gas is reduced, the regulating valve core 4 and the water supply component 5 do not need to be made of high-temperature alloy steel, significantly reducing costs.

[0071] In some embodiments, the regulating valve core 4 is provided with a hollow cavity, which is connected to the cooling hole 421.

[0072] The regulating valve core 4 has a hollow chamber connected to the cooling holes 421. The cooling water input from the water supply assembly 5 first enters the hollow chamber for buffering and pressure equalization, and then flows out synchronously from each cooling hole 421. This avoids uneven water distribution and local flow interruption caused by direct supply from a single hole, ensuring that all areas of the valve core's outer surface are wetted by cooling water, achieving uniform cooling in the entire circumference without dead angles, further improving cooling efficiency and enhancing resistance to high-temperature combustion gases. The hollow chamber can distribute water flow to all cooling holes 421 with a single or a small number of water supply lines, eliminating the need for a separate water supply line for each cooling hole 421. This greatly simplifies the connection structure between the regulating valve core 4 and the water supply assembly 5, reducing the difficulty of equipment assembly and maintenance.

[0073] In some embodiments, the regulating valve core 4 includes:

[0074] The valve core 41 is connected to the water supply component 5;

[0075] A conical structure 42 is disposed at one end of the valve core 41 near the turbine test piece 1; a cooling hole 421 is provided at least in the conical structure 42.

[0076] The conical structure 42 and the exhaust end flow channel of the turbine test piece 1 housing 11 form a suitable conical surface fit. During axial movement, the flow area between the conical surface of the conical structure 42 and the housing 11 changes linearly. Compared with planar fit, this allows for stepless and precise fine-tuning of the back pressure of the turbine blade 12, adapting to the refined back pressure requirements of the turbine blade 12 under different test conditions and improving the accuracy of test data. During the test, the high-temperature gas discharged from the turbine test piece 1 first impacts the end of the regulating valve core 4 closest to the housing 11, namely the area of ​​the conical structure 42. This area is the core part where high-temperature erosion and thermal stress concentration occur. By opening cooling holes 421 at least in the conical structure 42, cooling water can be accurately delivered to the critical area that needs cooling the most, avoiding waste caused by indiscriminate distribution of cooling water, greatly improving the utilization efficiency of cooling resources, and more effectively resisting the erosion and oxidation of the valve core by high-temperature gas. In addition, the streamlined design of the conical structure 42 can guide the high-temperature gas discharged from the turbine test piece 1, so that the airflow smoothly transitions to the exhaust pipe 2 of the test bench along the conical surface, avoiding airflow vortices and turbulence caused by the abrupt structure at the end of the valve core, reducing the impact of airflow disturbance on the working state of the turbine blade 12, ensuring the operational stability of the turbine blade 12 during the test, and reducing the deviation of test data caused by airflow disturbance.

[0077] In some embodiments, the conical structure 42 is provided with multiple rings of cooling holes 421 at intervals from the bottom to the top of the cone.

[0078] Multiple rings of cooling holes 421 are arranged at intervals along the entire conical surface from the apex to the bottom. Considering the high-temperature core at the apex, this arrangement allows cooling water to form a continuous and complete cooling water film from the apex to the bottom, completely covering all conical surface areas in contact with the combustion gases. This eliminates localized thermal weaknesses caused by missing cooling holes 421, effectively blocking direct contact between the high-temperature combustion gases and the conical surface, and comprehensively reducing the oxidation and erosion effects of the combustion gases on the conical structure 42. After the high-temperature combustion gases are discharged from the turbine test piece 1, they first rush directly to the apex and then flow along the conical surface to the bottom. The multiple rings of cooling holes 421 arranged from the apex to the bottom allow cooling water to form a multi-layered cooling water film in the same direction as the combustion gases after flowing out from the apex. This creates a unidirectional, fully contacting heat exchange state between the combustion gases and the water film, extending the contact time and path of gas-liquid heat exchange. In particular, it allows for sufficient heat exchange between the high-temperature combustion gases and cooling water in the core area of ​​the apex, significantly improving the cooling effect in the core area.

[0079] In some embodiments, the cooling holes 421 are evenly distributed along the circumference of the conical structure 42.

[0080] Each ring of cooling holes 421 is evenly distributed around the circumference of the conical structure 42, ensuring that cooling water flows out synchronously from the top to the bottom of the cone at every circumferential position. This forms a continuous, uninterrupted cooling water film on the cone surface, completely preventing direct erosion by high-temperature combustion gases caused by missing cooling holes 421 in certain circumferential locations. This ensures that the cooling rate and intensity are completely consistent across all circumferential areas of the cone surface, comprehensively blocking the circumferential erosion and oxidation of the conical structure 42 by high-temperature combustion gases. The top of the cone is the core area where high-temperature combustion gases directly impact; uneven cooling in the circumferential direction can easily lead to localized temperature differences, resulting in concentrated circumferential thermal stress. The even distribution of cooling holes 421 around the circumference ensures a synchronous and uniform temperature drop across the cone surface, significantly reducing the circumferential thermal stress difference and preventing deformation or even cracking of the conical structure 42 due to uneven circumferential thermal stress. This enhances the structural stability and fatigue resistance of the conical structure 42 under high-temperature conditions.

[0081] In some embodiments, the water supply component 5 includes:

[0082] Water source;

[0083] The annular water passage 51 is located around the regulating valve core 4 and is connected to the water source;

[0084] Support water passage 52 is connected between the annular water passage 51 and the regulating valve core 4.

[0085] The annular water channel 51 surrounds the regulating valve core 4, ensuring uniform pressure and flow of the input cooling water circumferentially. Water is then supplied to the regulating valve core 4 via the supporting water channel 52, allowing the cooling water to be synchronously and equally delivered to the internal hollow chamber circumferentially. This works in conjunction with the multiple rings of cooling holes 421 evenly distributed circumferentially on the conical structure 42, ensuring consistent cooling water velocity and flow rate at every circumferential position on the conical surface from the water supply source. This further enhances the uniform cooling effect circumferentially and completely eliminates circumferential cooling deviations. The cooling water output from the water source is first buffered and stabilized by the annular water channel 51 before being delivered via the supporting water channel 52. This effectively reduces pressure fluctuations caused by pipeline transport and water pressure changes during the water supply process, keeping the cooling water pressure input to the regulating valve core 4 stable.

[0086] In some embodiments, multiple supporting water channels 52 are radially distributed between the regulating valve core 4 and the annular water channel 51.

[0087] Multiple supporting water channels 52 are arranged radially along the regulating valve core 4, and the cooling water after pressure equalization in the annular water channel 51 is synchronously delivered to the interior of the regulating valve core 4 in the circumference of the regulating valve core 4, so that the water supply pressure and flow rate at each position in the circumference of the regulating valve core 4 are completely consistent, completely eliminating the local cooling intensity difference in the circumference of the cone surface, and making the cooling effect of the regulating valve core 4 more uniform.

[0088] In some embodiments, an air inlet 21 is formed between the test bench exhaust pipe 2 and the housing 11, and outside air is suitable to enter the test bench exhaust pipe 2 through the air inlet 21.

[0089] When the high-temperature combustion gas discharged from turbine test piece 1 enters the exhaust pipe 2 of the test bench, ambient air at room temperature is simultaneously drawn in through inlet 21 and fully mixed with the high-temperature combustion gas. This directly reduces the overall temperature of the combustion gas in the exhaust pipe, reducing the thermal erosion of the inner wall of the exhaust pipe 2 by the high-temperature combustion gas and reducing the thermal radiation and convection of the combustion gas on the regulating valve core 4. This helps to improve the cooling effect of the valve core and further extends the high-temperature service life of the exhaust pipe and the regulating valve core 4. Since the intake volume of ambient air can be adaptively adjusted according to the changes in the flow rate and pressure of the combustion gas in the exhaust pipe, when the combustion gas flow rate is large and the back pressure is high, the air drawn in through inlet 21 can dilute the combustion gas and increase the flow rate in the exhaust pipe, achieving auxiliary fine-tuning of the back pressure. At the same time, the mixing of air and combustion gas can optimize the flow state of the airflow in the exhaust pipe, making the back pressure adjustment more linear and stable. This complements the active back pressure adjustment of the regulating valve core 4, improving the accuracy and adaptability of the overall back pressure adjustment and meeting the back pressure requirements of the turbine blade 12 under different test conditions.

[0090] It should be noted that the mobile mechanism 3 includes:

[0091] The movable support 31 has an exhaust pipe 2 for the test bench installed on top of it.

[0092] The drive mechanism 32 is connected to the movable support 31 and is used to provide driving force to the movable support 31.

[0093] The movable bracket 31 provides a stable and rigid support for the test bench exhaust pipe 2, making the test bench exhaust pipe 2 and the regulating valve core 4 form an integrated load-bearing structure. When the drive mechanism 32 drives the movable bracket 31, it can drive the test bench exhaust pipe 2 and the regulating valve core 4 to move synchronously along the axial direction, avoiding adjustment deviations caused by loose component connections or uneven force, ensuring precise changes in the flow area between the regulating valve core 4 and the housing 11, and improving the accuracy and repeatability of back pressure adjustment.

[0094] Specifically, the drive mechanism 32 includes a motor, and the power output end of the motor is connected to the movable support 31 through the transmission mechanism 33.

[0095] In some embodiments, the bottom of the movable support 31 is provided with rollers.

[0096] The rollers can significantly reduce the frictional resistance when the moving bracket 31 moves axially. The drive mechanism 32 only needs a small driving force to drive the moving bracket 31, the test bench exhaust pipe 2 and the regulating valve core 4 to move smoothly, effectively reducing the power loss of the drive mechanism 32. At the same time, it makes the axial movement of the back pressure adjustment smoother and avoids adjustment jamming and displacement deviation caused by excessive frictional resistance.

[0097] In one embodiment, such as Figure 1 , Figure 3 and Figure 4 As shown, a test device is provided for adjusting the back pressure at the outlet of turbine blade 12 under high-temperature conditions, replacing valves. A conical structure 42 is welded and fixed to the exhaust section of the test bench via four hollow support water channels 52, which are connected to an annular water channel 51. The test bench exhaust pipe 2 is supported by a movable bracket 31 with rollers and connected to a high-precision variable frequency motor via a transmission rod. The variable frequency motor, transmission rod, and movable bracket 31 form a moving mechanism 3, which drives the conical structure 42 on the test bench exhaust pipe 2 to move axially. When the moving mechanism 3 moves closer to the turbine test piece 1, the flow area at the turbine blade 12 outlet decreases, and the back pressure increases; when the moving mechanism 3 moves away from the turbine test piece 1, the flow area increases, and the back pressure decreases.

[0098] The cooling principle of this experimental setup is as follows: Figure 2 As shown. Due to the high outlet airflow temperature (1500K~1600K) of turbine test piece 1, a cooling structure needs to be designed at the front end of the exhaust section. First, cooling water enters the inner cavity of the conical structure 42 through the annular water channel 51 and the supporting water channel 52. The conical structure 42 has four rows of cooling holes 421 with a diameter of 3mm as the outlet channels for cooling water. The cooling water can cover the entire conical structure 42 to prevent it from directly contacting the high-temperature combustion gas. After the cooling water flows out of the conical structure 42, it mixes with the high-temperature combustion gas at the outlet of the turbine blade 12, which can reduce the temperature of the high-temperature combustion gas to below 500℃. When the high-temperature gas flows through the conical surface, the acceleration of the airflow reduces its static pressure to below the local atmospheric pressure (according to Bernoulli's equation for compressible fluids, as the gas velocity increases, its static pressure decreases. Reducing the flow area increases the velocity, thus reducing the static pressure). The exhaust section inlet 21 can create an ejector effect to draw in ambient air. While protecting the exhaust section inlet with ambient air, it can also further mix with cooling water and high-temperature gas, ultimately forming a mixed exhaust with a temperature below 400°C. The temperature of the mixed exhaust is monitored in real time by a temperature probe after the supporting water channel 52. If the temperature exceeds 400°C, the cooling water flow can be increased to further reduce the exhaust temperature. Although the high-temperature gas temperature is very high, the cooling design of the experimental device is sufficient. The temperature of the metal surfaces in contact with the high-temperature gas, such as the conical structure and the supporting water channel 52, will not exceed 600°C. Therefore, the materials of the components at the front end of the exhaust section can be made of 316L stainless steel to reduce the cost of using high-temperature alloy steel.

[0099] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by this application.

Claims

1. A turbine blade testing device, characterized in that, include: The turbine test piece (1) is provided with a housing (11) and turbine blades (12). The test bench exhaust pipe (2) is coaxially arranged with the turbine test piece (1), and one end of the test bench exhaust pipe (2) is sleeved around the outer periphery of the housing (11); The moving mechanism (3) is connected to the exhaust pipe (2) of the test bench; The regulating valve core (4) is installed inside the exhaust pipe (2) of the test bench; and the regulating valve core (4) is provided with multiple cooling holes (421); the moving mechanism (3) drives the exhaust pipe (2) of the test bench to move axially to adjust the flow area between the regulating valve core (4) and the housing (11); The water supply assembly (5) is in fluid communication with the cooling hole (421) and is used to provide cooling water.

2. The turbine blade testing apparatus according to claim 1, characterized in that, The regulating valve core (4) is provided with a hollow cavity, which is connected to the cooling hole (421).

3. The turbine blade testing apparatus according to claim 2, characterized in that, The regulating valve core (4) includes: The valve core (41) is connected to the water supply assembly (5); A conical structure (42) is disposed at one end of the valve core (41) near the turbine test piece (1); the cooling hole (421) is at least opened in the conical structure (42).

4. The turbine blade testing apparatus according to claim 3, characterized in that, The conical structure (42) has multiple rings of cooling holes (421) spaced apart from the bottom to the top of the cone.

5. The turbine blade testing apparatus according to claim 4, characterized in that, The cooling holes (421) in each ring are evenly distributed along the circumference of the conical structure (42).

6. The turbine blade testing apparatus according to any one of claims 1 to 5, characterized in that, The water supply component (5) includes: Water source; An annular water channel (51) is located around the regulating valve core (4) and connected to the water source; The supporting water passage (52) is connected between the annular water passage (51) and the regulating valve core (4).

7. The turbine blade testing apparatus according to claim 6, characterized in that, Multiple supporting water channels (52) are radially distributed between the regulating valve core (4) and the annular water channel (51).

8. The turbine blade testing apparatus according to claim 1, characterized in that, An air inlet (21) is formed between the test bench exhaust pipe (2) and the housing (11), and outside air is suitable to enter the test bench exhaust pipe (2) through the air inlet (21).

9. The turbine blade testing apparatus according to claim 1, characterized in that, The moving mechanism (3) includes: The test bench exhaust pipe (2) is installed on the top of the movable support (31); The drive mechanism (32) is connected to the movable support (31) for providing driving force to the movable support (31).

10. The turbine blade testing apparatus according to claim 9, characterized in that, The bottom of the movable support (31) is provided with rollers.

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