High-temperature blade gas thermosetting rotation test system and method based on multi-gas-path coordinated regulation and control

Abstract

The invention belongs to the technical field of gas turbine blade test equipment, and relates to a multi-gas-path coordinated regulation high-temperature blade gas thermosetting rotation test system, which comprises a test shell, a transmission shaft, a rotation assembly, a high-temperature gas supply assembly, a cooling gas supply assembly and a detection assembly. The transmission shaft can be driven to rotate through the rotating assembly, centrifugal force load borne in the actual operation process is simulated, high-temperature gas is conveyed into the test shell through the high-temperature gas supply assembly, a high-temperature environment is provided for the tested turbine blade, and thermal load borne in the actual operation process is simulated; cooling gas is conveyed into the tested turbine blade through the transmission channel by the cooling gas supply assembly, the cooling environment in the actual operation process is simulated, and finally various data of the test are detected through the detection assembly. Therefore, the flow heat transfer characteristic and the strength characteristic of the turbine blade under the actual operation condition can be obtained as far as possible through tests.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbine blade test equipment, and relates to a high-temperature blade gas-thermal-solid rotation test system and method with multi-gas-path collaborative regulation. Background Art

[0002] A gas turbine is an internal combustion power machine that uses continuously flowing gas as the working medium to drive the turbine blades to rotate at high speed, converting the thermal energy of the fuel into useful work. Among them, the turbine blade is the most core hot-end component that converts thermal energy into mechanical energy. Its working environment is harsh, and in order to pursue greater power and higher efficiency, the turbine inlet temperature is increasing day by day. The problems of turbine blade failure caused by high thermal load and high temperature gradient are increasing day by day, seriously affecting the safe and stable operation of the gas turbine. Therefore, obtaining relevant operating data of gas turbine turbine blades through experiments, optimizing the blade structure, and ensuring the safe and stable operation of the turbine blades are of great significance for reducing major economic losses and avoiding catastrophic accidents.

[0003] The actual operating conditions of the turbine blade are relatively complex. First, it needs to directly bear the high-temperature gas from the combustion chamber, with a large thermal load. Second, during the rotation of the turbine blade, it is long-term subjected to centrifugal force load. Finally, in order to avoid the occurrence of blade ablation, a complex cooling channel structure is usually arranged inside the turbine blade. Therefore, due to the relatively complex actual operating conditions of the turbine blade, there is currently no test equipment that can better simulate the actual operating conditions of the turbine blade, resulting in difficulty in obtaining the flow and heat transfer characteristics and strength characteristics of the turbine blade under actual operating conditions through experiments, affecting the safe and stable operation of the turbine blade. Summary of the Invention

[0004] The purpose of the present invention is to provide a high-temperature blade gas-thermal-solid rotation test system and method with multi-gas-path collaborative regulation, which can better simulate the actual operating conditions of the turbine blade, so that the flow and heat transfer characteristics and strength characteristics of the turbine blade under actual operating conditions can be obtained as much as possible through experiments, ensuring the safe and stable operation of the turbine blade.

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

[0006] A high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation, comprising:

[0007] A test housing;

[0008] A transmission shaft, horizontally arranged inside the test housing, with both ends of the transmission shaft passing through the inner wall of the test housing and rotatably and sealingly connected to the test housing. A transmission channel is arranged inside the transmission shaft. The position of the transmission shaft inside the test housing is used to install a test turbine blade, and the cooling channel of the test turbine blade is communicated with the transmission channel;

[0009] A rotating component, connected to the drive shaft, is used to drive the drive shaft to rotate, providing a rotating environment for the test turbine blade and simulating the centrifugal force load received during actual operation;

[0010] A high-temperature gas supply component, connected to the test housing, is used to transport high-temperature gas into the test housing, providing a high-temperature environment for the test turbine blade and simulating the thermal load received during actual operation;

[0011] A cooling gas supply component, connected to the drive shaft, is used to transport cooling gas into the test turbine blade through a transmission channel, simulating the cooling environment during actual operation;

[0012] A detection component is used to detect the temperature and stress received by the test turbine blade during operation.

[0013] The features of the present invention also lie in:

[0014] Among them, the high-temperature gas supply component includes:

[0015] A first compressor, with its inlet connected to the atmosphere, is used to compress air;

[0016] A heater, with its inlet connected to the outlet of the first compressor, is used to heat the air;

[0017] A pressure stabilizing tank, with its inlet connected to the outlet of the heater;

[0018] A diverter, with its inlet connected to the outlet of the pressure stabilizing tank;

[0019] A plurality of jet nozzles are arranged on one side of the test housing. The plurality of jet nozzles correspond one-to-one to the plurality of outlets of the diverter. The positions of the plurality of jet nozzles are close to the drive shaft and are evenly arranged around the drive shaft. Each jet nozzle is connected to the inside of the test housing. Each jet nozzle is detachably connected to the test housing. Each jet nozzle is connected to the corresponding outlet of the diverter through a first bellows.

[0020] Among them, a flow controller and a micro-heater are sequentially arranged at each outlet of the diverter.

[0021] Among them, the cooling gas supply component includes:

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

[0023] A gas dryer, with its inlet connected to the outlet of the second compressor, is used to remove moisture in the air;

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

[0025] A collector is provided on one side of the test shell away from the multiple air nozzles, and multiple inlets of the collector are respectively connected to the test shell through second bellows, and the multiple second bellows are evenly arranged around the transmission 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, and the second outlet of the regenerator is connected to the inlet of the heater.

[0026] The detection components include:

[0027] A plurality of first thermocouples are arranged on the side of the test shell and between the plurality of first bellows and the plurality of second bellows. The plurality of first thermocouples are evenly arranged around the transmission shaft and are respectively used to detect the temperature inside the test shell.

[0028] a plurality of second thermocouples, disposed on the test turbine blades, for detecting the temperature on the turbine blades during the test;

[0029] A high-speed thermal imager, arranged outside the test housing, for detecting the temperature of the surface of the test turbine blade inside the test housing;

[0030] A plurality of strain gauges are provided on the test turbine blades to detect stresses on the turbine blades during the test;

[0031] A strain gauge, connected to a plurality of strain gauge signals, for collecting stress detected by the plurality of strain gauges;

[0032] The non-contact stress field measurement system is arranged outside the test housing and is used to detect the stress on the turbine blades during the test.

[0033] A swirl component is arranged between the transmission shaft and the test turbine blade. The swirl component is sleeved on the transmission shaft. A swirl channel is opened inside the swirl component. The swirl channel is respectively connected to the transmission channel and the cooling channel of the test turbine blade. The swirl component is detachably connected to the transmission shaft and the test turbine blade.

[0034] The high-temperature blade gas-thermal solid rotation test method with multi-gas path coordinated control includes the following steps:

[0035] Step 1, first conduct a static working condition test, open the cooling gas supply component, and deliver the cooling gas into the test turbine blade, then open the high-temperature gas supply component, and deliver the high-temperature gas into the test shell, and after maintaining the static working condition for a certain period of time, synchronously collect test data of multiple devices, including data of multiple first thermocouples, data of multiple second thermocouples, data of strain gauges, data of non-contact stress field measurement system, and data of high-speed thermal imager;

[0036] Step 2: Based on the test data of multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the static condition. Repeat Steps 1 to 2 to conduct test measurements under different static conditions;

[0037] Step 3: Then conduct a rotating condition test. Sequentially turn on the cooling gas supply component and the high-temperature gas supply component. After maintaining the rotating condition for a certain period of time, synchronously collect the test data of multiple devices, including the data of multiple first thermocouples, the data of multiple second thermocouples, the data of the strain gauge, and the data of the high-speed thermal imager;

[0038] Step 4: Based on the test data of multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the rotating condition. Repeat Steps 3 to 4 to conduct test measurements under different rotating conditions;

[0039] Step 5: Replace the test turbine blade, multiple jet nozzles, and swirl components, and repeat Steps 1 to 4 to achieve the tests and measurements of different test turbine blades, different jet nozzles, and different swirl components;

[0040] Step 6: According to the test results obtained from the tests, convert the test data into performance parameters applicable to engineering practice.

[0041] The high-temperature blade gas-thermal-solid rotation test system and method with multi-gas-path collaborative regulation of the present invention have the following advantages:

[0042] First, through the cooperation of the test housing, the transmission shaft, the rotating component, the high-temperature gas supply component, the cooling gas supply component, and the detection component, the rotating component can drive the transmission shaft to rotate, providing a rotating environment for the test turbine blade, simulating the centrifugal force load received during the actual operation process. The high-temperature gas supply component transports high-temperature gas into the test housing to provide a high-temperature environment for the test turbine blade, simulating the thermal load received during the actual operation process. The cooling gas supply component transports cooling gas into the test turbine blade through the transmission channel to simulate the cooling environment during the actual operation process. And finally, the detection component detects various data of the test, so that the flow and heat transfer characteristics and strength characteristics of the turbine blade under the actual operation conditions can be obtained as much as possible through the test, ensuring the safe and stable operation of the turbine blade.

[0043] Second, the present invention conducts tests on the test turbine blade in a test housing at high temperature and can provide cooling gas with precise flow rates for the leading edge, mid-chord, and trailing edge regions of the test turbine blade, achieving an accurate restoration 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 driving the transmission shaft to rotate with a variable frequency speed regulation motor, it solves the problem of mismatched force directions of the blade caused by using tensile load to replace centrifugal load in the traditional turbine blade testing system, thereby enabling accurate simulation of the temperature load and centrifugal load of the test turbine blade.

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

[0045] Fourth, the present invention constructs a multi-device synchronous measurement and calibration method. Through the comparative analysis and correction of 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 stationary or rotating working conditions, ensuring the effectiveness and reliability of the test data of the test system.

[0046] Fifth, the present invention proposes a modular design method for turbine blades. Through geometric similarity design, the size of the internal cooling channels of the blade can be enlarged, reducing the difficulty of blade processing. Through flow and heat transfer similarity design and rotational similarity design, the test working conditions can be made close to the actual operating conditions, so as to obtain the most real test data through testing, greatly improving the test feasibility. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0048] Figure 2 is a schematic diagram of the connection structure of the test housing with the diverter and the collector in the present invention;

[0049] Figure 3 is a schematic diagram of the connection structure of the transmission shaft with the swirl element in the present invention;

[0050] Figure 4 is a schematic diagram of the multi-air path flow path in the present invention;

[0051] Figure 5Schematic diagram of the overall process structure of the present invention.

[0052] Reference numerals:

[0053] 1. First compressor; 2. Heater; 3. Pressure stabilizing tank; 4. Swirl element; 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. Shunt; 14. Flow controller; 15. Micro heater; 16. First bellows; 17. Jet nozzle; 18. Test housing; 19. Second bellows; 20. Collector; 21. Variable frequency speed regulation motor; 22. Rotary joint; 23. Cold air flow regulating device; 24. Drive shaft; 24a. Air extraction section; 24b. Connection section; 24c. Air lead section; 25. Data transmission device; 26. First thermocouple. Detailed implementation manners

[0054] The technical solutions in the present application will be clearly and elaborately described below with reference to the accompanying drawings. Among them, in the description of the embodiments of the present application, unless otherwise specified, " / " means "or". For example, A / B may mean A or B. The "and / or" in the text is only a description of the relationship between associated objects, indicating that there can be three relationships. For example, A and / or B may mean: A exists alone, A and B exist simultaneously, and B exists alone. In addition, in the description of the embodiments of the present application, "a plurality" means two or more than two. The following terms "first" and "second" are only for descriptive purposes and cannot be construed as implying or indicating relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features.

[0055] As Figure 1 、 Figure 2As shown in the figure, the present invention provides a high-temperature blade gas-thermal-solid rotation test system with coordinated regulation of multiple gas paths, which includes a test housing 18, a transmission shaft 24, a rotating 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 transmission shaft 24 is horizontally arranged inside the test housing 18. The two ends of the transmission shaft 24 respectively pass through the inner wall of the test housing 18 and are rotationally and sealingly connected to the test housing 18. A transmission channel is arranged inside the transmission shaft 24. The position of the transmission shaft 24 inside the test housing 18 is used to install a test turbine blade, and the cooling channel of the test turbine blade is communicated with the transmission channel. The rotating assembly is connected to the transmission shaft 24 and is used to drive the transmission shaft 24 to rotate, providing a rotating environment for the test turbine blade and simulating the centrifugal force load received during actual operation. The high-temperature gas supply assembly is communicated with the test housing 18 and is used to transport high-temperature gas into the test housing 18 to provide a high-temperature environment for the test turbine blade and simulate the thermal load received during actual operation. The cooling gas supply assembly is communicated with the transmission shaft 24 and is used to transport cooling gas into the test turbine blade through the transmission channel to simulate the cooling environment during actual operation. The detection assembly is used to detect the temperature and stress received by the test turbine blade during operation, so that the flow heat transfer characteristics and strength characteristics of the turbine blade under actual operating conditions can be obtained as much as possible through the test, ensuring the safe and stable operation of the turbine blade.

[0056] As Figure 1 , Figure 2 shown in the figure, the rotating assembly includes a variable-frequency speed-regulating motor 21. The variable-frequency speed-regulating motor 21 is arranged outside the test housing 18 and is close to the transmission shaft 24. The output end of the variable-frequency speed-regulating motor 21 is connected with a first gear. A second gear is sleeved on the transmission shaft 24 close to the first gear. The second gear is meshed and connected with the first gear. The transmission shaft 24 is driven to rotate by the variable-frequency speed-regulating motor 21, and the rotation speed of the transmission shaft 24 can be adjusted.

[0057] As Figure 1 , Figure 2As shown in the figure, the high-temperature gas supply assembly includes a first compressor 1, a heater 2, a pressure stabilizing tank 3, a diverter 13 and a plurality of jet nozzles 17. The inlet of the first compressor 1 is connected to the atmosphere. The first compressor 1 is used to compress air. The inlet of the heater 2 is connected to the outlet of the first compressor 1. The heater 2 is used to heat the air. The inlet of the pressure stabilizing tank 3 is connected to the outlet of the heater 2. The pressure stabilizing tank 3 is used to eliminate air turbulence to stabilize the pressure. The inlet of the diverter 13 is connected to the outlet of the pressure stabilizing tank 3. A plurality of jet nozzles 17 are arranged on one side of the test housing 18. The plurality of jet nozzles 17 correspond to the plurality of outlets of the diverter 13 one by one. The positions of the plurality of jet nozzles 17 are close to the transmission shaft 24 and are evenly arranged around the transmission shaft 24. Each jet nozzle 17 communicates with the inside of the test housing 18. Each jet nozzle 17 is detachably connected to the test housing 18, which is convenient for replacing the jet nozzle 17. Each jet nozzle 17 is connected to the corresponding outlet of the diverter 13 through a first bellows 16. The first bellows 16 is also detachably connected to the jet nozzle 17.

[0058] Among them, the jet nozzles 17 have different specifications, and the inner diameter and jet angle of the jet nozzles 17 can be selected according to needs.

[0059] As Figure 2 shown in the figure, a flow controller 14 and a micro heater 15 are sequentially arranged at each outlet of the diverter 13. In order to ensure the circumferential uniformity of the high-temperature air entering the test housing 18, the flow rate in each jet nozzle 17 needs to be strictly controlled so that the flow velocity at the outlet of each jet nozzle 17 is the same. The flow rate of each high-temperature gas is adjusted through the flow controller 14 arranged at each outlet of the diverter 13. The micro heating device 15 is used to re-adjust 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 high-temperature gas is strictly controlled at the set temperature.

[0060] As Figure 1 、 Figure 2 shown in the figure, 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. The second compressor 7 is used to compress air. The inlet of the gas dryer 8 is connected to the outlet of the second compressor 7. The gas dryer 8 is used to remove moisture in the air. The inlet of the thermostat 9 is connected to the outlet of the gas dryer 8. The thermostat 9 is used to lower the air temperature to the set temperature to obtain cooling air. The outlet of the thermostat 9 is connected to the transmission shaft 24 through a rotary joint 22. The outlet of the thermostat 9 is communicated with the transmission channel, which is convenient for the cooling air to enter the transmission channel and enter the cooling channel of the test turbine blade through the transmission channel.

[0061] As Figure 1 、 Figure 5As shown in the figure, a collector 20 is provided on one side of the test housing 18 away from the plurality of jet nozzles 17. The plurality of inlets of the collector 20 are respectively communicated with the test housing 18 through the second bellows 19. The plurality of second bellows 19 are evenly arranged around the transmission shaft 24. The high-temperature air and the cooling air inside the test housing 18 are mixed and then enter 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 communicated with the atmosphere. The second inlet of the regenerator 5 is connected to the outlet of the first compressor 1. Through the regenerator 5, the mixed air pre-heats 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] Among them, each first bellows 16 and each second bellows 19 are high-temperature and vibration-resistant corrugated hoses. The pipeline shape can be adjusted arbitrarily, with strong obstacle avoidance. At the same time, it can eliminate the influence of the gravity of the long pipeline, reduce the stress at the connection, and the corrugation characteristics of the pipeline wall have the function of absorbing and resisting vibration, which can inhibit the conduction of component vibration and enhance the stability of the internal gas path.

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

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

[0065] As shown Figure 3 in the figure, the drive shaft 24 is composed of an air extraction section 24a, a connection section 24b and a lead section 24c from right to left. The transmission channel is arranged in the air extraction section 24a and the connection section 24b. The swirl element 4 is sleeved on the connection section 24b. A lead channel is arranged inside the lead section 24c. The lead channel is a U-shaped structure, which is convenient for leading out the leads of multiple strain gauges and the leads of multiple second thermocouples from the inside of the test housing 18. A data transmission device 25 is arranged at the end of the drive shaft 24 close to the lead section 24c. The lead of each strain gauge and the lead of each second thermocouple are respectively 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 transmit the temperature values detected by multiple second thermocouples to an external device.

[0066] Among them, the transmission channel is composed of three first connection channels. The three first connection channels are arranged side by side. The vertical cross-section of each first connection channel is rectangular. The swirl channel is composed of three second connection channels. The three second connection channels correspond to the positions of the three first connection channels one by one. Each second connection channel is communicated with the corresponding first connection channel. The inside of each second connection channel is a spiral structure. The three second connection channels correspond to the leading edge, mid-chord and trailing edge cooling channel inlets at the bottom of the test turbine blade, which is convenient for sending the cooling air with swirl into the test turbine blade. The swirl element 4 has different models, and the swirl element 4 with different swirl angles and directions can be selected according to needs.

[0067] As shown Figure 2 in the figure, a cold air flow regulating device 23 is arranged at the position of the drive shaft 24 where the air extraction section 24a is located, which is convenient for regulating the cooling air flow in each first connection channel respectively through the cold air flow regulating device 23.

[0068] As shown Figure 5 in the figure, the present invention also provides a high-temperature blade gas-thermal-solid rotation test method with multi-airway collaborative regulation, which includes the following steps:

[0069] Step 1, first conduct a static condition test. Open the cooling gas supply assembly, send the cooling gas into the test turbine blade, then open the high-temperature gas supply assembly, send the high-temperature gas into the test housing 18. After maintaining the static condition for a certain time, synchronously collect the test data of multiple devices, including the data of multiple first thermocouples 26, the data of multiple 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;

[0070] Step 2: Based on the test data of multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the static condition. Repeat Step 1 to Step 2 to conduct test measurements under different static conditions;

[0071] Step 3: Then conduct a rotating condition test. Sequentially turn on the cooling gas supply component and the high-temperature gas supply component. After maintaining the rotating condition for a certain period of time, synchronously collect the test data of multiple devices, 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;

[0072] Step 4: Based on the test data of multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the rotating condition. Repeat Step 3 to Step 4 to conduct test measurements under different rotating conditions;

[0073] Step 5: Replace the test turbine blade, multiple jet nozzles 17, and the swirl component 4. Repeat Step 1 to Step 4 to achieve the tests and measurements of different test turbine blades, different jet nozzles 17, and different swirl components 4;

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

[0075] Among them, before conducting the static condition test, first, according to the relevant parameters of the actual turbine blade, use the modular design method to obtain the relevant parameters of the test turbine blade, and process the test turbine blade according to the relevant parameters of the test turbine blade. The modular design method includes three aspects: geometric similarity design, flow and heat transfer similarity design, and rotational similarity design.

[0076] First, conduct geometric similarity design to ensure that the ratio of the characteristic dimensions of the test turbine blade to those of the actual turbine blade is the modular ratio MR. By setting the modular ratio MR, the size of the internal cooling channel of the test turbine blade can be enlarged, and the processing difficulty of the test turbine blade can be reduced. The specific calculation formula is:

[0077]

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

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

[0080]

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

[0082] Finally, rotational similarity design is carried out to ensure that the rotational radius of the scaled model test and the actual operating condition is the scaling ratio MR, and the rotational speed Ro of the scaled model test is the same as that of the actual operating condition. The specific calculation formula is:

[0083]

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

[0085] Among them, in step 1, when the cooling gas supply component is first opened, the switches of each device in the cooling air circuit are sequentially turned on, including the switch of the second compressor 7, the switch of the gas dryer 8, the switch of the thermostat 9, the switch of the cold air flow regulating device 23, and the switch of the cooler 6, and the value of the thermostat 9 and the flow rate at the cold air regulating device 23 are adjusted to the values required for the test; when the high-temperature gas supply component is then opened, the switches of each device in the high-temperature air circuit are sequentially turned on, including the switch of the first compressor 1, the switch of the heater 2, the switch of the pressure stabilizing tank 3, the flow controller 14, and the switch of each micro heating device 15, and the temperature of the high-temperature gas and the flow rates of each strand of high-temperature gas of the flow divider 13 are slowly increased to the values required for the test. During this period, the values of each device in the cooling air circuit need to be kept stable to avoid damage to the equipment caused by the backflow of high-temperature gas into the cooling air circuit.

[0086] Among them, in step 1, the time for maintaining the static condition is greater than 30 min, and in step 6, the time for maintaining the rotational condition is greater than 30 min.

[0087] Among them, in step 2, when comparing, analyzing, and correcting the test data of multiple devices under the static condition according to the test data of multiple devices collected synchronously, the data of the strain gauge 11 is used to further calibrate the data of the non-contact stress field measurement system 12, and the data of multiple second thermocouples on the surface of the test turbine blade is used to calibrate the data of the high-speed thermal imager 10 under the static state. The specific correction formula is:

[0088]

[0089] Wherein, X n is the data of the strain gauge 11, x n is the data of the non-contact stress field measurement system 12, T m is the data of the thermocouple on the surface of the test blade, t mFor the data of the high-speed thermal imaging system 10, a and c are the stress calibration coefficient and the temperature calibration coefficient respectively, and b and d are the stress offset term and the temperature offset term respectively. During the calibration process, with the minimum total deviation as the calibration target, a, b, c, and d are continuously updated.

[0090] Due to the bonding reliability problems of sensors such as strain gauges and thermocouples, problems such as signal loss and signal anomalies often exist in engineering practice. In contrast, the data measurements of the non-contact stress field measurement system 12 and the high-speed thermal imaging system 10 are relatively stable, but there are also problems such as low test accuracy. The method of multi-device synchronous measurement and correction can compensate for the shortcomings of unstable test signals and insufficient accuracy of various measurement methods under the set working conditions, ensuring the effectiveness and reliability of the test data of the test system.

[0091] Among them, in step 4, the method of comparing, analyzing, and correcting the test data of multiple devices under the rotating working condition based on the test data of multiple synchronously collected devices is the same as the method of comparing, analyzing, and correcting the test data of multiple devices under the static working condition in step 4.

[0092] It can be understood that the present invention is described through some embodiments. Those skilled in the art know that without departing from the spirit and scope of the present invention, various changes or equivalent replacements can be made to these features and embodiments. In addition, under the teaching 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 present invention. Therefore, the present invention is not limited by the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application belong to the scope protected by the present invention.

Claims

1. A high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation, characterized in that Comprising: A test housing (18); A drive shaft (24), horizontally arranged inside the test housing (18), both ends of the drive shaft (24) respectively pass through the inner wall of the test housing (18) and are rotationally and sealingly connected to the test housing (18). A transmission channel is arranged inside the drive shaft (24). The position of the drive shaft (24) inside the test housing (18) is used to install test turbine blades, and the cooling channels of the test turbine blades are communicated with the transmission channel; A rotating assembly, connected to the drive shaft (24), for driving the drive shaft (24) to rotate, providing a rotating environment for the test turbine blades, and simulating the centrifugal force load received during actual operation; A high-temperature gas supply assembly, communicated with the test housing (18), for transporting high-temperature gas into the test housing (18), providing a high-temperature environment for the test turbine blades, and simulating the heat load received during actual operation; A cooling gas supply assembly, communicated with the drive shaft (24), for transporting cooling gas into the test turbine blades through the transmission channel, simulating the cooling environment during actual operation; A detection assembly, for detecting the temperature and stress received by the test turbine blades during operation.

2. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 1, wherein, The high-temperature gas supply assembly includes: A first compressor (1), the inlet of which is connected to the atmosphere, for compressing air; A heater (2), the inlet of which is connected to the outlet of the first compressor (1), for heating air; A pressure stabilizing tank (3), the inlet of which is connected to the outlet of the heater (2); A diverter (13), the inlet of which is connected to the outlet of the pressure stabilizing tank (3); A plurality of jet nozzles (17), arranged on one side of the test housing (18). The plurality of jet nozzles (17) correspond to the plurality of outlets of the diverter (13) one by one. The positions of the plurality of jet nozzles (17) are close to the drive shaft (24) and are evenly arranged around the drive shaft (24). Each jet nozzle (17) is communicated with the inside of the test housing (18). Each jet nozzle (17) is detachably connected to the test housing (18). Each jet nozzle (17) is connected to the corresponding outlet of the diverter (13) through a first corrugated pipe (16).

3. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 2, wherein A flow controller (14) and a micro heater (15) are sequentially arranged at each outlet of the diverter (13).

4. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 2, wherein The cooling gas supply assembly includes: A second compressor (7), the inlet of which is connected to the atmosphere, for compressing air; A gas dryer (8), the inlet of which is connected to the outlet of the second compressor (7), for removing moisture in the air; A thermostat (9), the inlet of which is connected to the outlet of the gas dryer (8), for reducing the air temperature to a set temperature. 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 communicated with the transmission channel.

5. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 4, characterized in that, On one side of the test shell (18) away from the multiple jet nozzles (17), a collector (20) is provided. The multiple inlets of the collector (20) are respectively communicated with the test shell (18) through second bellows (19). The multiple second bellows (19) are uniformly arranged around the transmission shaft (24). 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 communicated with the atmosphere. The second inlet of the regenerator (5) is connected to the outlet of the first compressor (1). The second outlet of the regenerator (5) is connected to the inlet of the heater (2).

6. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 5, characterized in that The detection assembly includes: Multiple first thermocouples (26), arranged on the side surface of the test shell (18) and located between the multiple first bellows (16) and the multiple second bellows (19). The multiple first thermocouples (26) are uniformly arranged around the transmission shaft (24). The multiple first thermocouples (26) are respectively used to detect the temperature inside the test shell (18); Multiple second thermocouples, arranged on the test turbine blade, used to detect the temperature on the turbine blade during the test; A high-speed thermal imager (10), arranged outside the test shell (18), used to detect the temperature of the test turbine blade inside the test shell (18); Multiple strain gauges, arranged on the test turbine blade, used to detect the stress on the turbine blade during the test; A strain gauge (11), signal-connected to the multiple strain gauges, used to collect the stress detected by the multiple strain gauges; A non-contact stress field measurement system (12), arranged outside the test shell (18), used to detect the stress on the turbine blade during the test.

7. The high-temperature blade gas-thermal-solid rotation test system with multi-gas-path collaborative regulation according to claim 6, characterized in that A swirl element (4) is arranged between the transmission shaft (24) and the test turbine blade. The swirl element (4) is sleeved on the transmission shaft (24). A swirl channel is opened inside the swirl element (4). The swirl channel is respectively communicated with the transmission channel and the cooling channel of the test turbine blade. The swirl element (4) is detachably connected to the transmission shaft (24) and the test turbine blade respectively.

8. A high-temperature blade gas-thermal-solid rotation test method with multi-gas-path collaborative regulation, characterized in that Based on the system as claimed in claim 7, it includes the following steps: Step 1, first conduct a static condition test. Open the cooling gas supply assembly, transport the cooling gas into the test turbine blade, then open the high-temperature gas supply assembly, transport the high-temperature gas into the test shell (18). After maintaining the static condition for a certain period of time, synchronously collect the test data of multiple devices, including the data of multiple first thermocouples (26), the data of multiple 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 multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the static condition. Repeat Step 1 to Step 2 to conduct test measurements under different static conditions; Step 3: Conduct a rotation condition test. Sequentially turn on the cooling gas supply assembly and the high-temperature gas supply assembly. After maintaining the rotation condition for a certain period of time, synchronously collect the test data of multiple devices, 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: Based on the test data of multiple devices collected synchronously, conduct comparative analysis and correction on the test data of multiple devices under the rotation condition. Repeat Step 3 to Step 4 to conduct test measurements under different rotation conditions. Step 5: Replace the test turbine blade, multiple jet nozzles (17), and the swirl component (4). Repeat Step 1 to Step 4 to achieve the tests and measurements of different test turbine blades, different jet nozzles (17), and different swirl components (4). Step 6: According to the test results obtained from the tests, convert the test data into performance parameters that can be applied to engineering practice.

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