Rotating Turbine Blade Cooling Test System and Method

Abstract

The present invention relates to the technical field of gas turbines. The present invention discloses a rotating turbine blade cooling test system and method. The rotating turbine blade cooling effect test system includes an aeroengine, a rotating turbine blade cooling test device, a cooling air source device, a test cooling water device, a control system, and a data acquisition system. The aeroengine includes a gas generator for providing mainstream gas to the rotating turbine blade cooling test device and a compressor for providing cooling air to the rotating turbine blade cooling test device. The cooling air source device is connected to the rotating turbine blade cooling test device and is used to control the flow rate and pressure of the cooling air entering the rotating turbine blade cooling test device. The test cooling water device is connected to the rotating turbine blade cooling test device. The rotating turbine blade cooling test system provided by the present invention has the advantages of low test cost, no position limitation for the test device, and flexible activation.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular, to a rotating turbine blade cooling test system and method. Background Art

[0002] To enhance market competitiveness, gas turbines need to continuously increase the output and efficiency of the units, resulting in a continuous increase in the inlet temperature of the turbine blades. To ensure the safe, stable, and long-life operation of the turbine blades at higher temperatures, in addition to using more advanced materials, it is more important to introduce efficient turbine blade cooling design technologies.

[0003] In related technologies, some indicators of the efficient turbine blade cooling design can be verified through the cooling effect test of the turbine blade in a stationary state. However, the internal flow and heat transfer phenomena in the multi-stage turbine flow passage of a heavy-duty gas turbine are very complex and highly coupled. The secondary flow vortex system interacts with the main flow region of the turbine, and the inter-stage interference may cause blade vibration. Therefore, the cooling effect of the actual turbine blade in the rotating working state is very different from that measured in the stationary state. Measuring in the rotating state is more in line with the actual engineering situation. To verify the influence of cooling air mixing on the aerodynamic performance of the turbine stage and the influence of the rotating state on the cooling effect of the turbine moving blade, it is necessary to establish a rotating turbine blade cooling effect test device and conduct research on the flow and cooling of high-temperature rotating turbine blades. Summary of the Invention

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

[0005] To this end, an embodiment of the present invention provides a rotating turbine blade cooling test system, which has the advantages of low test cost, unrestricted position of the test device, and flexible activation.

[0006] According to the rotating turbine blade cooling test system of an embodiment of the present invention, the rotating turbine blade cooling test system includes a rotating turbine blade cooling test device, an aero-engine, a cooling air source device, a test cooling water device, a control system, and a data acquisition system. The aero-engine includes a gas generator for providing mainstream gas to the rotating turbine blade cooling test device and a compressor for providing cooling air to the rotating turbine blade cooling test device. The cooling air source device is connected to the rotating turbine blade cooling test device, and the cooling air source device is used to control the flow rate and pressure of the cooling air entering the rotating turbine blade cooling test device. The test cooling water device is connected to the rotating turbine blade cooling test device, and the test cooling water device is used to cool the inlet and outlet of the rotating turbine blade cooling test device. The control system is respectively connected to the rotating turbine blade cooling effect test device, the cooling air source device, and the test cooling water device. The control system is used to control the output of the mainstream gas, the cooling air, and the cooling water. The data acquisition system is electrically connected to the control system, and the data acquisition system is used to collect the operating parameters of the test system and send them to the control system.

[0007] The rotating turbine blade cooling test system according to the embodiment of the present invention has the advantages of low test cost, no position limitation for the test device, and flexible activation.

[0008] In some embodiments, the rotating turbine blade cooling test device sequentially includes a mainstream gas inlet valve, a turbine blade test section, a spray section, and a silencing tower. The mainstream gas inlet valve is used to control the flow rate of the mainstream gas entering the turbine blade test section. The turbine blade test section, the spray section, and the silencing tower are sequentially connected. The spray section is used to quickly cool down the mainstream gas, and the silencing tower is used to eliminate noise.

[0009] In some embodiments, the cooling air source device includes a cooling air inlet valve and a cooling air regulating valve. The cooling air inlet valve is connected to the compressor, and the cooling air regulating valve is connected to the turbine blade test section. The cooling air inlet valve and the cooling air regulating valve are used to control the flow rate and pressure of the cooling air entering the turbine blade test section.

[0010] In some embodiments, the test cooling water device includes a cooling tower, an inlet pipe, a makeup pipe, and an outlet pipe. The cooling tower is connected to the outlet of the gas generator and the spray section through the inlet pipe. The cooling tower is connected to the inlet and outlet of the test turbine section through the outlet pipe. The makeup pipe is connected to the cooling tower.

[0011] In some embodiments, the turbine blade test section includes a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section, and an exhaust volute. The exhaust volute is connected to the test turbine cylinder and the spray section, and is used to collect the outlet air flow of the turbine assembly.

[0012] In some embodiments, the scaling ratio of the turbine assembly is from 1 / 4 to 1 / 3.

[0013] In some embodiments, the turbine blade test section further includes a hydraulic clearance adjustment device, which is used to adjust the clearance between the turbine blade and the test turbine cylinder assembly.

[0014] In some embodiments, the data acquisition system includes a pressure acquisition device, a temperature acquisition device, a flow rate acquisition device, a drive system acquisition device, a dynamic stress acquisition device, and a vibration acquisition device. The pressure acquisition device acquires the pressure of the mainstream gas inlet pipeline, the outlet pressure of the turbine assembly, and the pressure of the cooling air. The temperature acquisition module acquires the temperatures of the mainstream gas and the cooling air. The flow rate acquisition device acquires the flow rates of the mainstream gas and the cooling air. The drive acquisition device acquires the rotational speed, torque, and power data of the turbine assembly. The dynamic stress acquisition device acquires the dynamic stress of the turbine blade. The vibration acquisition device acquires the vibration data of the casing.

[0015] In some embodiments, the drive acquisition device includes a hydraulic dynamometer. The output shaft of the turbine blade test section is connected to the hydraulic dynamometer, and the hydraulic dynamometer is used to measure the shaft power of the turbine assembly and control the output rotational speed of the turbine assembly.

[0016] In some embodiments, the control system includes a data storage module, a control switching module, a communication module, and a safety module. The data storage module is used to store the operation parameters of the test system sent by the data acquisition system. The control switching module is used to switch between the low-voltage electrical manual control mode and the computer remote control mode. The communication module is used to communicate with the data acquisition system and the upper computer. The safety module is used to monitor the corresponding parameter values according to the preset parameters to achieve emergency protection.

[0017] According to the rotating turbine blade cooling test method of the embodiments of the present invention, the rotating turbine blade cooling test method includes the following steps: extracting the gas at the outlet of the aeroengine gas generator as the mainstream gas, and extracting the air at the outlet of the aeroengine compressor as the cooling air; respectively introducing the mainstream gas and the cooling air into the mainstream channel and the internal cooling channel of the turbine blade of the turbine blade test section to conduct the rotating turbine blade cooling effect test; collecting the outlet air flow of the turbine blade test section, quickly cooling the outlet air flow and discharging it into the silencing tower. Description of the Drawings

[0018] Figure 1 is a schematic structural diagram of a rotating turbine blade cooling test system according to an embodiment of the present invention.

[0019] Reference numerals: 1, aeroengine; 2, compressor; 3, combustion chamber; 4, gas turbine; 5, power turbine; 6, gas generator; 7, rotating turbine blade cooling effect test device; 8, cooling air source device; 9, test cooling water device; 10, control system; 11, data acquisition system; 12, main stream gas inlet valve; 13, main stream gas regulating valve; 14, corrugated compensator; 15, turbine blade test section; 16, spray section; 17, exhaust butterfly valve; 18, silencing tower; 19, hydraulic clearance adjustment device; 20, hydraulic dynamometer; 21, cooling air inlet valve; 22, cooling air regulating valve; 23, water pump; 24, make-up water pipeline; 25, inlet pipeline; 26, cooling tower; 27, outlet pipeline; 28, flow measurement point; 29, pressure measurement point; 30, temperature measurement point. Detailed Embodiment

[0020] The embodiments of the present invention will be described in detail below, and the examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0021] The rotating turbine blade cooling test system according to an embodiment of the present invention, as Figure 1As shown in the figure, the rotating turbine blade cooling test system includes a rotating turbine blade cooling test device, an aero-engine 1, a cooling air source device 8, a test cooling water device 9, a control system 10, and a data acquisition system 11. The aero-engine 1 includes a gas generator 6 for supplying mainstream gas to the rotating turbine blade cooling test device, a compressor 2 for supplying cooling air to the rotating turbine blade cooling test device, and a power turbine 5. The power turbine 5 mainly converts the energy of the high-temperature and high-pressure gas at the inlet of the gas turbine 4 into the mechanical energy of the power turbine 5. The cooling air source device 8 is connected to the rotating turbine blade cooling test device. The cooling air source device 8 is used to control the flow rate and pressure of the cooling air entering the rotating turbine blade cooling test device. The test cooling water device 9 is connected to the rotating turbine blade cooling test device. The test cooling water device 9 is used to cool the inlet and outlet of the rotating turbine blade cooling test device. The control system 10 is respectively connected to the rotating turbine blade cooling effect test device 7, the cooling air source device 8, and the test cooling water device 9. The control system 10 is used to control the output of the mainstream gas, the cooling air, and the cooling water. The data acquisition system 11 is electrically connected to the control system 10. The data acquisition system 11 is used to collect the operating parameters of the test system and send them to the control system 10. In the present invention, the aero-engine 1 is used to supply gas to the rotating turbine blade cooling test device. The aero-engine 1 uses a retired aero-engine 1. Compared with a specially established rotating turbine blade cooling effect test device under working conditions, it can reduce the equipment purchase cost of the test device and the power consumption cost of the corresponding equipment, such as the air compressor for providing high-pressure mainstream air, the air electric heater, the combustion chamber 3 for providing high-temperature gas, and the blower, filter, and air heater for providing cooling air. The rotating turbine blade cooling test device supplied with gas by the aero-engine 1 is less restricted by the spatial position, and there is no need for work such as power grid dispatching and unit transformation, so that the test can be started flexibly and takes less time.

[0022] The rotating turbine blade cooling test system according to the embodiment of the present invention has the advantages of low test cost, less position restriction of the test device, and flexible startup.

[0023] In some embodiments, as Figure 1 shown, the rotating turbine blade cooling test device successively includes a mainstream gas inlet valve 12, a turbine blade test section 15, a spray section 16, and a silencing tower 18. The mainstream gas inlet valve 12 is used to control the flow rate of the mainstream gas entering the turbine blade test section 15. The turbine blade test section 15, the spray section 16, and the silencing tower 18 are successively connected. The spray section 16 is used to quickly cool down the mainstream gas. The silencing tower 18 is used to eliminate noise.

[0024] Specifically, the mainstream gas inlet valve 12 is connected to the outlet extraction pipeline of the gas generator 6 of the aero-engine 1. A mainstream gas regulating valve 13 is also provided to control the mainstream gas inlet flow rate and pressure by adjusting the opening degrees of the mainstream gas inlet valve 12 and the mainstream gas regulating valve 13. The exhaust gas of the spray section 16 enters the silencing tower 18 through the exhaust butterfly valve 17 for noise reduction and then is discharged into the atmosphere.

[0025] In some embodiments, as Figure 1 shown, the cooling air source device 8 includes a cooling air inlet valve 21 and a cooling air regulating valve 22. The cooling air inlet valve 21 is connected to the compressor 2, and the cooling air regulating valve 22 is connected to the turbine blade test section 15. The cooling air inlet valve 21 and the cooling air regulating valve 22 are used to control the flow rate and pressure of the cooling air entering the turbine blade test section 15.

[0026] Specifically, the cooling air inlet valve 21 is connected to the exhaust cylinder of the compressor 2 of the aero-engine 1, and the cooling air regulating valve 22 is connected to the turbine blade test section 15 through a pipeline. The cooling air enters the internal cooling channels of the turbine blades from the top of the stator blades or the roots of the rotor blades. Flow measurement points 28, pressure measurement points 29, and temperature measurement points 30 are provided on the pipeline connecting the cooling air regulating valve 22 and the turbine blade test section 15.

[0027] In some embodiments, as Figure 1 shown, the test cooling water device 9 includes a cooling tower 26, a water pump 23, an inlet pipeline 25, a makeup pipeline 24, and an outlet pipeline 27. The cooling tower 26 is connected to the outlet of the gas generator 6 and the spray section 16 through the inlet pipeline 25. The cooling tower 26 is connected to the inlet and outlet of the test turbine section through the outlet pipeline 27. The makeup pipeline 24 is connected to the cooling tower 26. The water pump 23 is arranged on the inlet pipeline 25.

[0028] Specifically, the test cooling water device is used to cool the inlet and outlet of the turbine blade test section 15. The cooling water of the cooling tower 26 is sprayed into the spray section 16 to reduce the exhaust gas temperature after the turbine test section to below 100 °C, ensuring that the downstream backpressure valve and the silencing tower 18 do not exceed the operating temperature. The pipe section before the spray section 16 adopts a high-temperature alloy double-layer water jacket structure, and the pipeline material after water spraying is 304 stainless steel.

[0029] In some embodiments, the turbine blade test section 15 includes a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section, and an exhaust volute. The exhaust volute is connected to the test turbine cylinder and the spray section 16, and the exhaust volute is used to collect the outlet air flow of the turbine assembly.

[0030] Specifically, the turbine assembly includes a first-stage turbine stator blade, a first-stage turbine rotor blade, a second-stage turbine stator blade, and a second-stage turbine rotor blade. The turbine blade test section 15 can operate under configurations of single-row blade row, single-stage turbine, one-and-a-half-stage turbine, and two-stage turbine. The inlet temperature of the turbine blade test section 15 can reach 900 °C, and the inlet pressure can reach 2.8 MPa. The housing of the turbine blade test section 15 is designed as a double-layer housing, with heat insulation material installed between the double layers. The bellows compensator 14 is installed on the main air intake pipe to absorb the expansion of the intake pipe.

[0031] In some embodiments, the scaling ratio of the turbine assembly is from 1 / 4 to 1 / 3. Thus, the simulation effect of the turbine assembly is more appropriate, which can ensure the test effect while reducing the test cost.

[0032] In some embodiments, as Figure 1 shown, the turbine blade test section 15 further includes a hydraulic clearance adjustment device 19, which is used to adjust the clearance between the turbine blade and the test turbine cylinder assembly.

[0033] Specifically, the hydraulic clearance adjustment device 19 drives a piston through hydraulic oil to push the thrust bearing and rotor of the test turbine, realizing axial displacement so as to adjust the clearance between the top of the test turbine rotor blade and the test turbine cylinder. At the same time, a stopper is set to limit the amount of axial displacement. The function of the hydraulic clearance adjustment device 19 is that when the gas turbine enters the fully warmed-up state, that is, when the static and dynamic clearances no longer change, the rotor is moved a certain distance along the reverse gas flow direction through the hydraulic device, reducing the static and dynamic clearances of the gas turbine 4, so that the aeroengine 1 can achieve higher efficiency and power, thus making the rotating turbine blade cooling effect test as close to the actual situation as possible.

[0034] In some embodiments, the data acquisition system 11 includes a pressure acquisition device, a temperature acquisition device, a flow rate acquisition device, a transmission system acquisition device, a dynamic stress acquisition device, and a vibration acquisition device. The pressure acquisition device acquires the pressure of the main gas inlet pipe, the outlet pressure of the turbine assembly, and the pressure of the cooling air. The temperature acquisition device acquires the temperatures of the main gas and the cooling air. The flow rate acquisition device acquires the flow rates of the main gas and the cooling air. The transmission acquisition device acquires the rotational speed, torque, and power data of the turbine assembly. The dynamic stress acquisition device acquires the dynamic stress of the turbine blade. The vibration acquisition device acquires the vibration data of the casing.

[0035] Specifically, the pressure acquisition device includes a pressure scanning valve and a pressure transmitter for acquisition, the temperature acquisition device includes a thermocouple and a temperature indicating paint for acquisition; the flow rate acquisition device uses a flow nozzle and a mass flowmeter for acquisition; the transmission system acquisition device acquires the turbine speed, turbine torque, and turbine power; the dynamic stress acquisition device measures the dynamic stress of the blade by combining a ceramic ion spray high-temperature strain gauge and a thin-film strain gauge, and is selected according to the blade shape and the test position; the acceleration sensor is used to measure the vibration of the casing in the vibration acquisition device. The pressure test of the test piece includes a steady-state pressure test and a dynamic pressure test. The data acquisition system 11 acquires data such as the mainstream gas inlet temperature, the mainstream gas inlet total pressure, the test section outlet static pressure, the mainstream air flow rate, the fuel temperature and pressure of the combustion chamber 3, the cooling air flow rate, temperature and pressure, and the torque and power of the test turbine.

[0036] In some embodiments, as Figure 1 shown, the transmission acquisition device includes a hydraulic dynamometer 20, and the output shaft of the turbine blade test section 15 is connected to the hydraulic dynamometer 20, and the hydraulic dynamometer 20 is used to measure the shaft power of the turbine assembly and control the output speed of the turbine assembly.

[0037] Specifically, the output shafts of the hydraulic dynamometer 20 and the turbine blade test section 15 are connected by a coupling, and another hydraulic dynamometer 20 is connected to the output shaft of the power turbine 5 of the aero-engine 1 by a coupling to consume the output power of the aero-engine 1.

[0038] In some embodiments, the control system 10 includes a data storage module, a control switching module, a communication module, and a safety module. The data storage module is used to store the operating parameters of the test system sent by the data acquisition system 11. The control switching module is used to switch between the low-voltage electrical manual control mode and the computer remote control mode. The communication module is used to communicate with the data acquisition system 11 and the upper computer. The safety module is used to monitor the corresponding parameter values according to the preset parameters to achieve emergency protection.

[0039] Specifically, the control system 10 has a data management function implemented through the data storage module. The data storage module has functions such as data recording, data playback, and parameter configuration; the control system 10 has two modes: local and remote. The control system 10 realizes the independent control function of parallel operation of low-voltage electrical manual control and computer remote control through the control switching module; the control system 10 has a function of mutual data communication to facilitate data transmission and receiving data from the data acquisition system 11; the control system 10 has a safety protection function, and emergency protection processing is achieved by configuring the alarm limit values of the corresponding parameters.

[0040] According to the method for testing the cooling of a rotating turbine blade according to an embodiment of the present invention, the method for testing the cooling of a rotating turbine blade includes the following steps: extracting the gas at the outlet of the gas generator 6 of the aeroengine 1 as the mainstream gas, and extracting the air at the outlet of the compressor 2 of the aeroengine 1 as the cooling air; respectively introducing the mainstream gas and the cooling air into the mainstream channel of the turbine blade test section 15 and the internal cooling channel of the turbine blade to conduct a test on the cooling effect of the rotating turbine blade; collecting the outlet air flow of the turbine blade test section 15, rapidly cooling the outlet air flow and discharging it into the silencing tower 18.

[0041] The technical advantages of the method for testing the cooling of a rotating turbine blade according to an embodiment of the present invention are the same as those of the above-mentioned rotating turbine blade cooling test system, and will not be elaborated here.

[0042] For a certain model of 300MW-class F-class unit, the air flow rate at the inlet of the compressor is 730 kg / s, and the air flow rate at the inlet of the compressor of a certain model of retired aeroengine is 138 kg / s; the 1 / 4 scaled test turbine composed of 1 stage of stator blades and 1 stage of rotor blades, the calculated results of the air flow rate and the mainstream gas flow rate for the cooling effect test are listed in the following table; the air flow rate extracted from the outlet of the compressor of the retired aeroengine for the rotating turbine blade cooling effect test accounts for about 5.47% of the air flow rate at the outlet of the compressor, and will not affect the safe operation of the power station gas turbine.

[0043]

[0044] The equipment purchase and project costs saved by the present invention are 80 million - 105 million yuan. The power of these equipment is 28,000 - 34,000 kW. For a cooling effect test of a test turbine, 8 working conditions are performed, and each working condition is calculated according to 1 hour. The test electricity consumption is 224,000 - 272,000 kWh; if the industrial electricity is calculated at the electricity consumption cost of 0.9 yuan / kWh, by using the method provided by the present invention, 201,600 - 244,800 yuan can be saved.

[0045] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0046] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0047] In the present invention, unless otherwise clearly specified and defined, terms such as "mounted", "connected", "coupled", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0048] In the present invention, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0049] In the present invention, terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0050] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions, and variations made by those of ordinary skill in the art to the above embodiments are within the protection scope of the present invention.

Claims

1. A rotating turbine blade cooling test system, characterized in that, it includes: A rotating turbine blade cooling test device; An aeroengine, which includes a gas generator for supplying mainstream gas to the rotating turbine blade cooling test device and a compressor for supplying cooling air to the rotating turbine blade cooling test device; A cooling air source device, which is connected to the rotating turbine blade cooling test device, and the cooling air source device is used to control the flow rate and pressure of the cooling air entering the rotating turbine blade cooling test device; A test cooling water device, which is connected to the rotating turbine blade cooling test device, and the test cooling water device is used to cool the inlet and outlet of the rotating turbine blade cooling test device; A control system, which is respectively connected to the rotating turbine blade cooling effect test device, the cooling air source device and the test cooling water device, and the control system is used to control the output of the mainstream gas, the cooling air and the cooling water; and A data acquisition system, which is electrically connected to the control system, and the data acquisition system is used to collect the operating parameters of the test system and send them to the control system; The rotating turbine blade cooling test device sequentially includes a mainstream gas inlet valve, a turbine blade test section, a spray section and a silencing tower. The mainstream gas inlet valve is used to control the flow rate of the mainstream gas entering the turbine blade test section. The turbine blade test section, the spray section and the silencing tower are connected in sequence. The spray section is used to quickly cool down the mainstream gas, and the silencing tower is used to eliminate noise; The turbine blade test section includes a test turbine cylinder assembly, a turbine assembly, an inlet measurement section, an outlet measurement section and an exhaust volute. The exhaust volute is connected to the test turbine cylinder and the spray section, and the exhaust volute is used to collect the outlet air flow of the turbine assembly; The modular ratio of the turbine assembly is from 1 / 4 to 1 / 3.

2. The rotating turbine blade cooling effect test system supplied with air by the aeroengine according to claim 1, characterized in that, The cooling air source device includes a cooling air inlet valve and a cooling air regulating valve. The cooling air inlet valve is connected to the compressor, and the cooling air regulating valve is connected to the turbine blade test section. The cooling air inlet valve and the cooling air regulating valve are used to control the flow rate and pressure of the cooling air entering the turbine blade test section.

3. The rotating turbine blade cooling effect test system supplied with air by the aeroengine according to claim 1, characterized in that, The test cooling water device includes a cooling tower, an inlet pipe, a makeup pipe and an outlet pipe. The cooling tower is connected to the outlet of the gas generator and the spray section through the inlet pipe, and the cooling tower is connected to the inlet and outlet of the turbine blade test section through the outlet pipe. The makeup pipe is connected to the cooling tower.

4. The rotating turbine blade cooling effect test system supplied with air by the aeroengine according to claim 1, characterized in that, The turbine blade test section further includes a hydraulic clearance adjustment device, which is used to adjust the clearance between the turbine blade and the test turbine cylinder assembly.

5. The rotating turbine blade cooling effect test system for an aeroengine air supply according to claim 1, wherein, the data acquisition system includes a pressure acquisition device, a temperature acquisition device, a flow rate acquisition device, a drive system acquisition device, a dynamic stress acquisition device and a vibration acquisition device. The pressure acquisition device acquires the pressure of the mainstream gas inlet pipeline, the outlet pressure of the turbine assembly, and the pressure of the cooling air. The temperature acquisition module acquires the temperatures of the mainstream gas and the cooling air. The flow rate acquisition device acquires the flow rates of the mainstream gas and the cooling air. The drive system acquisition device acquires the rotational speed, torque and power data of the turbine assembly. The dynamic stress acquisition device acquires the dynamic stress of the turbine blade. The vibration acquisition device acquires the vibration data of the casing.

6. The rotating turbine blade cooling effect test system for an aeroengine air supply according to claim 5, wherein, the drive system acquisition device includes a hydraulic dynamometer. The output shaft of the turbine blade test section is connected to the hydraulic dynamometer, and the hydraulic dynamometer is used to measure the shaft power of the turbine assembly and control the output rotational speed of the turbine assembly.

7. The rotating turbine blade cooling effect test system for an aeroengine air supply according to claim 1, wherein, the control system includes a data storage module, a control switching module, a communication module and a safety module. The data storage module is used to store the operating parameters of the test system sent by the data acquisition system. The control switching module is used to switch between the low-voltage electrical manual control mode and the computer remote control mode. The communication module is used to communicate with the data acquisition system and the upper computer. The safety module is used to monitor the corresponding parameter values according to the preset parameters to achieve emergency protection.

8. A rotating turbine blade cooling test method, using the rotating turbine blade cooling effect test system according to any one of claims 1-7, wherein, it includes the following steps: Extracting the gas at the outlet of the aeroengine gas generator as the mainstream gas, and extracting the air at the outlet of the aeroengine compressor as the cooling air; Respectively introducing the mainstream gas and the cooling air into the mainstream channel and the internal cooling channel of the turbine blade of the turbine blade test section to conduct a rotating turbine blade cooling effect test; Collecting the outlet air flow of the turbine blade test section, quickly cooling the outlet air flow and discharging it into the silencing tower.

Images