High-temperature blade gas-heat-solid rotating test system and method with multi-gas-path collaborative regulation

Abstract

The present application belongs to the technical field of gas turbine blade test equipment, and relates to a high-temperature blade gas-thermal-solid rotating test system with multiple gas paths for collaborative regulation, comprising a test shell, a transmission shaft, a rotating assembly, a high-temperature gas supply assembly, a cooling gas supply assembly and a detection assembly. The present application can drive the transmission shaft to rotate through the rotating assembly, simulate the centrifugal force load in the actual operation process, deliver high-temperature gas into the test shell through the high-temperature gas supply assembly, provide a high-temperature environment for the test turbine blade, simulate the thermal load in the actual operation process, deliver cooling gas into the test turbine blade through the transmission channel of the cooling gas supply assembly, simulate the cooling environment in the actual operation process, and finally detect various data of the test through the detection assembly, so that the flow heat transfer characteristics and strength characteristics of the turbine blade under the actual operation condition can be obtained as much as possible through the test.

Description

Technical Field

[0001] This invention belongs to the technical field of gas turbine blade testing equipment, and relates to a high-temperature blade gas-thermal-solid rotational testing system and method with multi-gas-path coordinated control. Background Technology

[0002] Gas turbines are internal combustion power machines that use continuously flowing gas as the working fluid to drive turbine blades to rotate at high speed, converting the thermal energy of fuel into useful work. The turbine blades are the core hot-end components that convert thermal energy into mechanical energy. Their operating environment is harsh, and in pursuit of greater power and higher efficiency, turbine inlet temperatures are increasingly rising. High thermal loads and high temperature gradients are leading to a growing number of turbine blade failures, seriously affecting the safe and stable operation of gas turbines. Therefore, obtaining relevant operating data on gas turbine blades through experiments, optimizing blade structure, and ensuring the safe and stable operation of turbine blades are of great significance for reducing significant economic losses and preventing catastrophic accidents.

[0003] The actual operating conditions of turbine blades are quite complex. First, they directly bear the high-temperature combustion gases from the combustion chamber, resulting in a large heat load. Second, during rotation, turbine blades are subjected to centrifugal force loads for extended periods. Finally, to prevent blade ablation, turbine blades typically have complex cooling channel structures inside. Therefore, due to the complexity of the actual operating conditions of turbine blades, there is currently no experimental equipment that can effectively simulate these conditions. This makes it difficult to obtain the flow and heat transfer characteristics and strength characteristics of turbine blades under actual operating conditions through experiments, affecting the safe and stable operation of turbine blades. Summary of the Invention

[0004] The purpose of this invention is to provide a high-temperature turbine blade gas-thermal-solid rotation test system and method with multi-channel coordinated control, which can better simulate the actual operating conditions of turbine blades, so as to obtain the flow and heat transfer characteristics and strength characteristics of turbine blades under actual operating conditions through experiments, and ensure the safe and stable operation of turbine blades.

[0005] To achieve the above objectives, the technical solution provided by the present invention is as follows:

[0006] A high-temperature blade gas-thermal-solid rotation test system with multi-channel coordinated control includes:

[0007] Test housing;

[0008] The drive shaft is horizontally installed inside the test housing. Both ends of the drive shaft pass through the inner wall of the test housing and are rotatably sealed to the test housing. The drive shaft has a transmission channel inside. The position on the drive shaft inside the test housing is used to install the test turbine blades. The cooling channel of the test turbine blades is connected to the transmission channel.

[0009] The rotating component, connected to the drive shaft, is used to drive the drive shaft to rotate, providing a rotational environment for the test turbine blades and simulating the centrifugal loads experienced during actual operation.

[0010] The high-temperature gas supply component is connected to the test housing and is used to deliver high-temperature gas into the test housing to provide a high-temperature environment for the test turbine blades and simulate the heat load during actual operation.

[0011] The cooling gas supply assembly, connected to the drive shaft, is used to deliver cooling gas into the test turbine blades through the transmission channel to simulate the cooling environment during actual operation.

[0012] The detection component is used to detect the temperature and stress experienced by the test turbine blades during operation.

[0013] The invention is further characterized by:

[0014] The high-temperature gas supply components include:

[0015] The first compressor has its inlet connected to the atmosphere and is used to compress air;

[0016] The heater, whose inlet is connected to the outlet of the first compressor, is used to heat the air;

[0017] The pressure stabilizing tank has its inlet connected to the outlet of the heater;

[0018] The distributor connects the inlet to the outlet of the pressure stabilizing tank;

[0019] Multiple jet nozzles are located on one side of the test housing. Each jet nozzle corresponds to one of the multiple outlets of the splitter. The jet nozzles are located close to the drive shaft and are evenly distributed around the drive shaft. Each jet nozzle is connected to the interior of the test housing and is detachably connected to the test housing. Each jet nozzle is connected to the corresponding outlet of the splitter through the first bellows.

[0020] Each outlet of the splitter is equipped with a flow controller and a miniature heater in sequence.

[0021] The cooling gas supply components include:

[0022] The second compressor, with its inlet connected to the atmosphere, is used to compress air;

[0023] The gas dryer has its inlet connected to the outlet of the second compressor and is used to remove moisture from the air.

[0024] The thermostat, with its inlet connected to the outlet of the gas dryer, is used to lower the air temperature to the set temperature. The outlet of the thermostat is connected to the drive shaft via a rotary joint, and the outlet of the thermostat is connected to the transmission channel.

[0025] A collector is installed on the side of the test housing away from the multiple jet nozzles. Multiple inlets of the collector are connected to the test housing through second bellows. Multiple second bellows are evenly arranged around the drive shaft. The outlet of the collector is connected to the first inlet of the regenerator. The first outlet of the regenerator is connected to the inlet of the cooler. The outlet of the cooler is connected to the atmosphere. The second inlet of the regenerator is connected to the outlet of the first compressor. The second outlet of the regenerator is connected to the inlet of the heater.

[0026] The detection components include:

[0027] Multiple first thermocouples are disposed on the side of the test housing and located between multiple first corrugated pipes and multiple second corrugated pipes. The multiple first thermocouples are evenly arranged around the drive shaft, and the multiple first thermocouples are used to detect the temperature inside the test housing.

[0028] Multiple second thermocouples are installed on the test turbine blades to detect the temperature on the turbine blades during the test;

[0029] A high-speed thermal imager, installed outside the test housing, is used to detect the temperature of the surface of the turbine blades inside the test housing.

[0030] Multiple strain gauges are installed on the test turbine blade to detect the stress on the turbine blade during the test.

[0031] A strain gauge, connected to multiple strain gauges, is used to acquire the stress detected by the multiple strain gauges.

[0032] A non-contact stress field measurement system is installed outside the test housing to detect the stress on the turbine blades during the test.

[0033] A swirling element is installed between the drive shaft and the test turbine blades. The swirling element is sleeved on the drive shaft and has a swirling channel inside. The swirling channel is connected to the transmission channel and the cooling channel of the test turbine blades. The swirling element is detachably connected to the drive shaft and the test turbine blades.

[0034] A high-temperature blade gas-thermo-solid rotation test method with multi-channel coordinated control includes the following steps:

[0035] Step 1: First, conduct a static test. Turn on the cooling gas supply component to deliver cooling gas into the test turbine blade. Then, turn on the high-temperature gas supply component to deliver high-temperature gas into the test shell. After maintaining the static condition for a certain period of time, simultaneously collect test data from multiple devices, including data from multiple first thermocouples, multiple second thermocouples, strain gauges, non-contact stress field measurement systems, and high-speed thermal imagers.

[0036] Step 2: Based on the test data of multiple devices collected synchronously, compare, analyze and correct the test data of multiple devices under static conditions, and repeat Step 1 to Step 2 to conduct test measurements under different static conditions.

[0037] Step 3: Perform a rotational test. Turn on the cooling gas supply component and the high-temperature gas supply component in sequence. After maintaining the rotational condition for a certain period of time, collect test data from multiple devices simultaneously, including data from multiple first thermocouples, multiple second thermocouples, strain gauges, and high-speed thermal imagers.

[0038] Step 4: Based on the test data of multiple devices collected simultaneously, compare, analyze and correct the test data of multiple devices under rotating conditions, and repeat steps 3 to 4 to conduct test measurements under different rotating conditions.

[0039] Step 5: Replace the test turbine blades, multiple nozzles and swirl elements, and repeat steps 1 to 4 to achieve the test and measurement of different test turbine blades, different nozzles and different swirl elements;

[0040] Step 6: Based on the test results obtained from the experiment, convert the test data into performance parameters that can be applied to actual engineering projects.

[0041] The high-temperature blade gas-thermo-structure rotation test system and method with multi-channel coordinated control of the present invention has the following advantages:

[0042] First, through the cooperation of the test shell, drive shaft, rotating assembly, high-temperature gas supply assembly, cooling gas supply assembly, and detection assembly, the rotating assembly drives the drive shaft to rotate, providing a rotational environment for the test turbine blades and simulating the centrifugal load during actual operation. The high-temperature gas supply assembly delivers high-temperature gas into the test shell, providing a high-temperature environment for the test turbine blades and simulating the thermal load during actual operation. The cooling gas supply assembly delivers cooling gas into the test turbine blades through a transmission channel, simulating the cooling environment during actual operation. Finally, the detection assembly detects various test data, thereby enabling the test to obtain the flow and heat transfer characteristics and strength characteristics of the turbine blades under actual operating conditions as much as possible, ensuring the safe and stable operation of the turbine blades.

[0043] Secondly, by conducting the test turbine blade in a high-temperature test shell and providing precisely flowed cooling gas to the leading edge, middle chord, and trailing edge regions of the test turbine blade, this invention achieves accurate reproduction of the "internal cooling and external heating" load characteristics of the actual operating conditions of the test turbine blade, solving the problem of low accuracy in constructing the temperature load environment of traditional test benches. At the same time, by using a variable frequency speed control motor to drive the transmission shaft to rotate, this invention solves the problem of mismatch in the force direction of the blade caused by the use of tensile load instead of centrifugal load in traditional turbine blade testing systems. Thus, it can achieve accurate simulation of the temperature load and centrifugal load of the test turbine blade.

[0044] Third, by coordinating the drive shaft, swirling elements, and test turbine blades, precise control of the swirling angle and direction of the three streams of cooling air entering the test turbine blades can be achieved by replacing different swirling elements. At the same time, through the detachable connection of multiple jet nozzles, high-temperature and high-speed airflow at the stator blade outlet can be simulated. By replacing different jet nozzles and precisely controlling the flow rate and temperature of the high-temperature air in the jet nozzles, precise control of the high-temperature airflow scouring position, airflow scouring speed, and angle can be achieved. The swirling elements and jet nozzles are easy to replace and can be used to study various combined working conditions, greatly reducing the cost of the experiment.

[0045] Fourth, this invention constructs a multi-device synchronous measurement-calibration method. By comparing and correcting multi-source data from strain gauge method, thermocouple method, non-contact stress field measurement system and high-speed thermal imager, it makes up for the shortcomings of unstable test signals and insufficient accuracy of various measurement methods under static or rotating conditions, and ensures the effectiveness and reliability of test data of the test system.

[0046] Fifth, this invention proposes a turbine blade modeling design method. Through geometric similarity design, the size of the internal cooling channel of the blade can be expanded, reducing the difficulty of blade processing. Through flow heat transfer similarity design and rotational similarity design, the test conditions can be made close to the actual operating conditions, thereby obtaining the most realistic test data and greatly improving the feasibility of the test. Attached Figure Description

[0047] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0048] Figure 2 This is a schematic diagram of the connection structure between the test shell and the splitter and collector in this invention;

[0049] Figure 3 This is a schematic diagram of the connection structure between the drive shaft and the vortex component in this invention;

[0050] Figure 4 This is a schematic diagram of the multi-airflow path of the present invention;

[0051] Figure 5This is a schematic diagram of the overall process structure of the present invention.

[0052] Figure label:

[0053] 1. First compressor; 2. Heater; 3. Pressure stabilizing tank; 4. Swirl component; 5. Regenerator; 6. Cooler; 7. Second compressor; 8. Gas dryer; 9. Thermostat; 10. High-speed thermal imager; 11. Strain gauge; 12. Non-contact stress field measurement system; 13. Flow divider; 14. Flow controller; 15. Miniature heater; 16. First bellows; 17. Nozzle; 18. Test shell; 19. Second bellows; 20. Collector; 21. Variable frequency speed control motor; 22. Rotary joint; 23. Cold air flow regulating device; 24. Drive shaft; 24a. Air intake section; 24b. Connecting section; 24c. Lead wire section; 25. Data transmission device; 26. First thermocouple. Detailed Implementation

[0054] The technical solutions of this application will now be described clearly and in detail with reference to the accompanying drawings. In the description of the embodiments of this application, unless otherwise stated, " / " indicates "or," for example, A / B can mean A or B. "And / or" in the text is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, and B alone. Furthermore, in the description of the embodiments of this application, "multiple" refers to two or more. The terms "first" and "second" are used for descriptive purposes only and should not be construed as implying or suggesting relative importance or implicitly indicating the number of indicated technical features. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature.

[0055] like Figure 1 , Figure 2As shown, this invention provides a high-temperature turbine blade gas-thermo-mechanical rotational testing system with multi-channel coordinated control, including a test housing 18, a drive shaft 24, a rotation assembly, a high-temperature gas supply assembly, a cooling gas supply assembly, and a detection assembly. The test housing 18 is made of a high-temperature resistant and transparent material. The drive shaft 24 is horizontally arranged inside the test housing 18, with both ends passing through the inner wall of the test housing 18 and rotatably sealed to it. A transmission channel is provided inside the drive shaft 24. The position on the drive shaft 24 inside the test housing 18 is used to install the test turbine blade, and the cooling channel of the test turbine blade is connected to the transmission channel. The rotation assembly is connected to the drive shaft 24 and is used to drive the drive shaft 24 to rotate, thus rotating the test turbine blade. The turbine blade is provided with a rotating environment to simulate the centrifugal load during actual operation. The high-temperature gas supply component is connected to the test housing 18 and is used to deliver high-temperature gas into the test housing 18 to provide a high-temperature environment for the test turbine blade and simulate the heat load during actual operation. The cooling gas supply component is connected to the drive shaft 24 and is used to deliver cooling gas into the test turbine blade through the transmission channel to simulate the cooling environment during actual operation. The detection component is used to detect the temperature and stress of the test turbine blade during operation, so as to obtain the flow and heat transfer characteristics and strength characteristics of the turbine blade under actual operating conditions as much as possible through the test, and ensure the safe and stable operation of the turbine blade.

[0056] like Figure 1 , Figure 2 As shown, the rotating assembly includes a variable frequency speed control motor 21. The variable frequency speed control motor 21 is located outside the test housing 18 and close to the transmission shaft 24. The output end of the variable frequency speed control motor 21 is connected to a first gear. A second gear is sleeved on the transmission shaft 24 near the first gear. The second gear meshes with the first gear. The variable frequency speed control motor 21 drives the transmission shaft 24 to rotate and can adjust the speed of the transmission shaft 24.

[0057] like Figure 1 , Figure 2As shown, the high-temperature gas supply assembly includes a first compressor 1, a heater 2, a pressure stabilizing tank 3, a distributor 13, and multiple nozzles 17. The inlet of the first compressor 1 is connected to the atmosphere and is used to compress air. The inlet of the heater 2 is connected to the outlet of the first compressor 1 and is used to heat air. The inlet of the pressure stabilizing tank 3 is connected to the outlet of the heater 2 and is used to eliminate air turbulence to stabilize pressure. The inlet of the distributor 13 is connected to the outlet of the pressure stabilizing tank 3. Multiple nozzles 17 are arranged on one side of the test housing 18, and each nozzle 17 corresponds to a different outlet of the distributor 13. The nozzles 17 are located close to the drive shaft 24 and are evenly arranged around the drive shaft 24. Each nozzle 17 communicates with the interior of the test housing 18 and is detachably connected to the test housing 18 for easy replacement. Each nozzle 17 is connected to the corresponding outlet of the distributor 13 through a first bellows 16, which is also detachably connected to the nozzle 17.

[0058] The nozzle 17 comes in different specifications, and its inner diameter and jet angle can be selected as needed.

[0059] like Figure 2 As shown, each outlet of the splitter 13 is sequentially equipped with a flow controller 14 and a micro heater 15. In order to ensure the circumferential uniformity of the high-temperature air entering the test housing 18, the flow rate in each nozzle 17 needs to be strictly controlled so that the flow velocity at the outlet of each nozzle 17 is the same. The flow controller 14 installed at each outlet of the splitter 13 is used to adjust the flow rate of each stream of high-temperature gas. The micro heater 15 is used to readjust the temperature of the high-temperature gas to eliminate the heat loss caused during the transmission of the high-temperature gas, so that the temperature of each stream of high-temperature gas is strictly controlled at the set temperature.

[0060] like Figure 1 , Figure 2 As shown, the cooling gas supply assembly includes a second compressor 7, a gas dryer 8, and a thermostat 9. The inlet of the second compressor 7 is connected to the atmosphere and is used to compress air. The inlet of the gas dryer 8 is connected to the outlet of the second compressor 7 and is used to remove moisture from the air. The inlet of the thermostat 9 is connected to the outlet of the gas dryer 8 and is used to lower the air temperature to a set temperature to obtain cooling air. The outlet of the thermostat 9 is connected to the drive shaft 24 through a rotary joint 22. The outlet of the thermostat 9 is connected to the transmission channel, which facilitates the entry of cooling air into the transmission channel and into the cooling channel of the test turbine blade.

[0061] like Figure 1 , Figure 5As shown, a collector 20 is provided on the side of the test housing 18 away from the multiple jet nozzles 17. Multiple inlets of the collector 20 are connected to the test housing 18 through second bellows 19. The multiple second bellows 19 are evenly arranged around the drive shaft 24. The high-temperature air inside the test housing 18 is mixed with the cooling air and then enters the collector 20. The outlet of the collector 20 is connected to the first inlet of the regenerator 5. The first outlet of the regenerator 5 is connected to the inlet of the cooler 6. The outlet of the cooler 6 is connected to the atmosphere. The second inlet of the regenerator 5 is connected to the outlet of the first compressor 1. The regenerator 5 allows the mixed air to preheat the compressed air from the outlet of the first compressor 1, avoiding heat loss in the mixed air and saving energy. The second outlet of the regenerator 5 is connected to the inlet of the heater 2.

[0062] Each of the first corrugated pipes 16 and each of the second corrugated pipes 19 is a high-temperature vibration-resistant corrugated flexible hose. The pipe shape can be adjusted at will, providing strong obstacle avoidance capabilities. It also eliminates the influence of gravity on long pipes, reduces stress at connections, and the corrugated characteristics of the pipe wall have vibration-absorbing and anti-vibration effects, suppressing the transmission of component vibrations and enhancing the stability of the internal air passages.

[0063] like Figure 1 , Figure 2 As shown, the detection assembly includes multiple first thermocouples 26, multiple second thermocouples, a high-speed thermal imager 10, multiple strain gauges, a strain meter 11, and a non-contact stress field measurement system 12. The multiple first thermocouples 26 are disposed on the side of the test housing 18 and located between multiple first bellows 16 and multiple second bellows 19. The multiple first thermocouples 26 are evenly arranged around the drive shaft 24. The multiple first thermocouples 26 are used to detect the temperature inside the test housing 18. The multiple second thermocouples are disposed on the test turbine blades and are used to detect the temperature during the test. During the test, the temperature on the turbine blade is measured by a high-speed thermal imager 10 located outside the test housing 18. The high-speed thermal imager 10 is used to detect the temperature inside the test housing 18. Multiple strain gauges are installed on the test turbine blade to detect the stress on the turbine blade during the test. A strain gauge 11 is connected to the multiple strain gauges and is used to collect the stress detected by the multiple strain gauges. A non-contact stress field measurement system 12 is installed outside the test housing 18 to detect the stress on the turbine blade during the test.

[0064] like Figure 3 As shown, a swirl element 4 is provided between the drive shaft 24 and the test turbine blade. The swirl element 4 is sleeved on the drive shaft 24. A swirl channel is opened inside the swirl element 4. The swirl channel is connected to the transmission channel and the cooling channel of the test turbine blade. The swirl element 4 is detachably connected to the drive shaft 24 and the test turbine blade.

[0065] like Figure 3 As shown, the drive shaft 24 consists of an air intake section 24a, a connecting section 24b, and a lead wire section 24c from right to left. The transmission channel is located between the air intake section 24a and the connecting section 24b. The swirl element 4 is sleeved on the connecting section 24b. A lead wire channel is opened inside the lead wire section 24c. The lead wire channel has a U-shaped structure, which facilitates the lead wires of multiple strain gauges and multiple second thermocouples to be led out from inside the test housing 18. A data transmission device 25 is provided at the end of the drive shaft 24 near the lead wire section 24c. The lead wires of each strain gauge and each second thermocouple are electrically connected to the data transmission device 25. The data transmission device 25 is electrically connected to the strain gauge 11. The data transmission device 25 is used to transmit the stress values ​​detected by multiple strain gauges to the strain gauge 11 and the temperature values ​​detected by multiple second thermocouples to external devices.

[0066] The transmission channel consists of three first connecting channels arranged side by side, each with a rectangular vertical cross-section. The swirling channel consists of three second connecting channels, each corresponding to one of the three first connecting channels. Each second connecting channel is connected to its corresponding first connecting channel, and each second connecting channel has a spiral structure inside. The three second connecting channels correspond to the cooling channel inlets at the leading edge, middle chord, and trailing edge of the bottom of the test turbine blade, facilitating the delivery of swirling cooling air into the test turbine blade. The swirling element 4 comes in different models, and different swirling angles and directions can be selected as needed.

[0067] like Figure 2 As shown, a cold air flow regulating device 23 is provided at the position of the air intake section 24a on the drive shaft 24, so that the cooling air flow in each first connecting channel can be adjusted by the cold air flow regulating device 23.

[0068] like Figure 5 As shown, the present invention also provides a method for high-temperature blade gas-thermo-structure rotation test with multi-channel coordinated control, comprising the following steps:

[0069] Step 1: First, conduct a static test. Turn on the cooling gas supply component to deliver cooling gas into the test turbine blade. Then, turn on the high-temperature gas supply component to deliver high-temperature gas into the test housing 18. After maintaining the static condition for a certain period of time, simultaneously collect test data from multiple devices, including data from multiple first thermocouples 26, multiple second thermocouples, strain gauge 11, non-contact stress field measurement system 12, and high-speed thermal imager 10.

[0070] Step 2: Based on the test data of multiple devices collected synchronously, compare, analyze and correct the test data of multiple devices under static conditions, and repeat Step 1 to Step 2 to conduct test measurements under different static conditions.

[0071] Step 3: Perform a rotational test. Turn on the cooling gas supply component and the high-temperature gas supply component in sequence. After maintaining the rotational condition for a certain period of time, collect test data from multiple devices simultaneously, including data from multiple first thermocouples 26, multiple second thermocouples, strain gauge 11, and high-speed thermal imager 10.

[0072] Step 4: Based on the test data of multiple devices collected simultaneously, compare, analyze and correct the test data of multiple devices under rotating conditions, and repeat steps 3 to 4 to conduct test measurements under different rotating conditions.

[0073] Step 5: Replace the test turbine blades, multiple jet nozzles 17 and swirl elements 4, and repeat steps 1 to 4 to achieve the test and measurement of different test turbine blades, different jet nozzles 17 and different swirl elements 4.

[0074] Step 6: Based on the test results obtained from the experiment, convert the test data into performance parameters that can be applied to actual engineering projects.

[0075] Before conducting static condition tests, the relevant parameters of the test turbine blades are obtained using a modeling design method based on the actual turbine blades. The test turbine blades are then fabricated according to these parameters. The modeling design method includes three aspects: geometric similarity design, flow and heat transfer similarity design, and rotational similarity design.

[0076] First, geometric similarity design is performed to ensure that the ratio of the characteristic dimension of the experimental turbine blade to that of the actual turbine blade is the modeling ratio MR. By setting the modeling ratio MR, the size of the internal cooling channel of the experimental turbine blade can be increased, reducing the manufacturing difficulty of the experimental turbine blade. The specific calculation formula is as follows:

[0077]

[0078] In the formula, the subscripts M and 0 represent the experimental turbine blade and the actual turbine blade, respectively, L is the characteristic dimension, and MR is the modeling ratio.

[0079] Secondly, flow heat transfer similarity design is performed to ensure that the Reynolds number Re, Prandtl number Pr, and temperature ratio TR are equal in the model test and actual operating conditions. The specific calculation formula is as follows:

[0080]

[0081] In the formula, u is the fluid velocity, μ is the fluid dynamic viscosity, ρ is the fluid density, λ is the thermal conductivity, and C is the fluid density. P T represents specific heat, and T represents temperature. The superscripts g and c represent high-temperature air and cooling air, respectively, and the subscripts w and f represent the heat transfer wall and the fluid, respectively.

[0082] Finally, rotational similarity design is performed to ensure that the rotation radius of the modeled test and the actual operating conditions is the same as the modeling ratio MR, and the rotation number Ro of the modeled test and the actual operating conditions is the same. The specific calculation formula is as follows:

[0083]

[0084] In the formula, R is the rotation radius of the channel, and ω is the rotational angular velocity.

[0085] In step 1, when the cooling gas supply assembly is first turned on, the switches of each device in the cooling air circuit are turned on in sequence, including the second compressor 7 switch, the gas dryer 8 switch, the thermostat 9 switch, the cold air flow regulating device 23 switch, and the cooler 6 switch, adjusting the thermostat 9 value and the flow rate at the cold air regulating device 23 to the required values ​​for the test. When the high-temperature gas supply assembly is turned on, the switches of each device in the high-temperature air circuit are turned on in sequence, including the first compressor 1 switch, the heater 2 switch, the pressure stabilizing tank 3 switch, the flow controller 14 switch, and each miniature heating device 15 switch, slowly increasing the high-temperature gas temperature and the flow rate of each stream of high-temperature gas in the distributor 13 to the required values ​​for the test. During this process, the values ​​of each device in the cooling air circuit must be kept stable to prevent high-temperature gas from flowing back into the cooling air circuit and causing equipment damage.

[0086] In step 1, the time spent in the static state is greater than 30 minutes, and in step 6, the time spent in the rotating state is greater than 30 minutes.

[0087] In step 2, when comparing and correcting the test data of multiple devices under static conditions based on the test data of multiple devices collected simultaneously, the data of the non-contact stress field measurement system 12 is further calibrated using the data of strain gauge 11, and the data of the high-speed thermal imager 10 under static conditions is calibrated using the data of multiple second thermocouples on the surface of the test turbine blade. The specific calibration formula is as follows:

[0088]

[0089] In the formula, X n For strain gauge 11 data, x n For data from the non-contact stress field measurement system 12, T m For the thermocouple data on the test blade surface, t mFor the high-speed thermal imaging system 10 data, a and c are the stress calibration coefficient and temperature calibration coefficient, respectively, and b and d are the stress bias term and temperature bias term, respectively. During the calibration process, the goal is to minimize the total deviation, and a, b, c and d are continuously updated.

[0090] Due to the bonding reliability issues of strain gauges and sensors such as thermocouples, signal loss and abnormal signals often occur in engineering practice. In contrast, the data measurement of non-contact stress field measurement system 12 and high-speed thermal imager 10 is relatively stable, but they also have problems such as low test accuracy. The multi-device synchronous measurement-calibration method can make up for the shortcomings of various measurement methods in terms of unstable test signals and insufficient accuracy under the set working conditions, and ensure the validity and reliability of the test data of the test system.

[0091] In step 4, the method of comparing, analyzing, and correcting the test data of multiple devices under rotating conditions based on the test data of multiple devices collected simultaneously is the same as the method of comparing, analyzing, and correcting the test data of multiple devices under stationary conditions in step 4.

[0092] It is understood that the present invention has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of the present invention.

Claims

1. 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The multi-gas-path synergistically regulated high-temperature vane gas-thermal solid-rotation test system according to claim 1, characterized in that, ​ 3. The multi-gas-path cooperatively regulated high-temperature vane gas-thermal solid-rotation test system according to claim 1, characterized in that, The test shell (18) is provided with a flow collector (20) on the side away from the plurality of air nozzles (17), a plurality of inlets of the flow collector (20) are communicated with the test shell (18) through a second corrugated pipe (19), the plurality of second corrugated pipes (19) are uniformly arranged around the transmission shaft (24), the outlet of the flow collector (20) is connected with the first inlet of the regenerator (5), the first outlet of the regenerator (5) is connected with the inlet of the cooler (6), the outlet of the cooler (6) is communicated with the atmosphere, the second inlet of the regenerator (5) is connected with the outlet of the first compressor (1), and the second outlet of the regenerator (5) is connected with the inlet of the heater (2).

4. The multi-gas-path synergistically regulated high-temperature vane gas-thermal solid-rotation test system according to claim 3, characterized in that, The detection assembly comprises: A plurality of first thermocouples (26) are arranged on the side of the test shell (18) and between the plurality of first corrugated pipes (16) and the plurality of second corrugated pipes (19), the plurality of first thermocouples (26) are uniformly arranged around the transmission shaft (24), and the plurality of first thermocouples (26) are used for detecting the temperature inside the test shell (18) respectively; A plurality of second thermocouples are arranged on the test turbine blade and used for detecting the temperature on the turbine blade during the test; A high-speed thermal imager (10) is arranged outside the test shell (18) and used for detecting the temperature of the test turbine blade inside the test shell (18); A plurality of strain gauges are arranged on the test turbine blade and used for detecting the stress on the turbine blade during the test; A strain gauge (11) is connected with the plurality of strain gauges and used for collecting the stress detected by the plurality of strain gauges; A non-contact stress field measurement system (12) is arranged outside the test shell (18) and used for detecting the stress on the turbine blade during the test.

5. The multi-gas-path synergistically regulated high-temperature vane gas-thermal solid-rotation test system according to claim 4, characterized in that, A rotational flow member (4) is arranged between the transmission shaft (24) and the test turbine blade, the rotational flow member (4) is sleeved on the transmission shaft (24), a rotational flow channel is formed in the rotational flow member (4), the rotational flow channel is communicated with the transmission channel and the cooling channel of the test turbine blade respectively, and the rotational flow member (4) is detachably connected with the transmission shaft (24) and the test turbine blade.

6. A high-temperature vane gas-heat solid-rotation test method with multi-gas-path collaborative regulation, characterized in that, Based on the system of claim 5, the following steps are included: Step 1, first, a static working condition test is carried out, the cooling gas supply assembly is opened, the cooling gas is delivered into the test turbine blade, then the high-temperature gas supply assembly is opened, the high-temperature gas is delivered into the test shell (18), after a certain time of maintaining the static working condition, the test data of the plurality of devices are synchronously collected, including the data of the plurality of first thermocouples (26), the data of the plurality of second thermocouples, the data of the strain gauge (11), the data of the non-contact stress field measurement system (12) and the data of the high-speed thermal imager (10); Step 2, according to the test data of the plurality of devices synchronously collected, the test data of the plurality of devices under the static working condition are compared and analyzed and corrected, steps 1 to 2 are repeated, and test measurements of different static working conditions are carried out. Step 3, the rotating condition test is further conducted, the cooling gas supply assembly and the high-temperature gas supply assembly are sequentially opened, the test data of multiple devices are synchronously collected after a certain time of maintaining the rotating condition, including the data of multiple first thermocouples (26), the data of multiple second thermocouples, the data of the strain gauge (11) and the data of the high-speed thermal imager (10); Step 4, the test data of multiple devices under the rotating condition are compared and corrected according to the synchronously collected test data of multiple devices, steps 3 to 4 are repeated to conduct test measurement under different rotating conditions; Step 5, the test turbine blade, multiple jet nozzles (17) and swirl members (4) are replaced, steps 1 to 4 are repeated to realize test and measurement of different test turbine blades, different jet nozzles (17) and different swirl members (4); Step 6, according to the test results obtained by the test, the test data is converted into performance parameters applicable to engineering practice.

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