Comprehensive test system for overcooling and multiphase erosion of power end blades simulating polar environments

Abstract

The present invention aims to solve the problem of the lack of service status simulation test equipment for power end blades under polar environmental conditions by developing a comprehensive test system for simulating polar environment power end blade overcooling and multiphase flow erosion. The comprehensive test system of the present invention includes a blade operation simulation unit, a low-temperature environment simulation unit and a medium filling device. In the blade operation simulation unit, a plurality of rotors are arranged on the main shaft, and the power end blades are mounted on the rotors along the circumferential direction. The inner spiral pipe extends into the anti-leakage cover and faces the power end blades. The medium filling device includes a plurality of filling chambers, and the pressure compensation channel is connected to each filling chamber. The low-temperature environment simulation unit includes a medium pre-cooling device, a pressure stabilizing tank, a supercharger, a low-temperature cooling air pipe and an extreme cooling device. The present invention realizes polar environment simulation through the low-temperature environment simulation unit and the composite erosion unit. In combination with the blade operation simulation unit and the dust removal device, the multiphase flow erosion performance test of the power end blades in a simulated polar environment can be realized.

Description

Technical Field

[0001] The present invention belongs to the field of material performance testing devices, and in particular relates to a comprehensive testing device for overcooling and multiphase flow erosion of power end blades in a simulated polar environment. Background Art

[0002] When operating in polar environments, aircraft engines and gas turbines face over 20 different loads, including high temperatures, stresses, and corrosion. Furthermore, they must contend with the effects of ingested materials like fog, snow, and ice from the low-temperature environment. The ingestion of hard objects like ice into the air intake can damage or even break the high-speed rotating blades. Cold air currents can cause ice to form on the rotor blades, and overloaded and unevenly distributed blades can cause rotor vibration. When the blades rotate at high speeds, the combined effects of ice adsorption and heat generation can cause ice to slide off. The impact of these ice fragments on the outer walls and the resulting ice fragments can cause secondary damage to the engine, leading to unexpected shutdowns. For land-based and sea-based wind turbines operating under extreme conditions, their components are subjected to the combined erosion of cold, high-speed airflow mixed with fog, snow, and ice. This shortens the turbine's service life and makes the safe operation of the turbine blades difficult. Furthermore, propeller aircraft like helicopters face similar challenges when operating in extreme conditions, including ice formation and impact with hard objects.

[0003] Currently, some researchers are conducting research on the service behavior of power-end blades. Pei Yanling and others applied alternating stress to external force-applying components and workpieces and conducted coupled experiments to fully simulate the high-temperature service environment of aircraft engines and study the impact of alternating stress on engine service performance. Shang Yong and others heated rotor blades and sprayed corrosive media on their surfaces to study the failure mechanism of thermal barrier coatings on high-temperature rotors under high-temperature service conditions. Zhang Bo and others used an air pump and sand storage drum to mix sand and simulate the aerodynamic load characteristics of wind turbine blades being washed, in order to study the erosion effect of simulated wind and sand environments on wind turbine blades. Currently, researchers are mainly studying the service state of power-end blades under the influence of stress and media in normal and high-temperature environments.

[0004] However, research on the service behavior of power-end blades in special service environments, especially those in polar environments, has not yet been conducted. The failure mechanism of blades in the complex, low-temperature polar environment is still unclear, which will limit my country's future polar scientific research, natural resource exploration, and independent development needs. Therefore, there is an urgent need to provide a system that can simulate the supercooled atmosphere and multiphase flow erosion in polar environments to test the service performance of power-end blades. This system can fill the current gap in comprehensive service performance testing of power-end blades in polar environments. This has important scientific and practical significance for my country's polar resource development, polar equipment protection, and polar safety. Summary of the Invention

[0005] The present invention aims to address the lack of test equipment for simulating the service state of power-end blades in polar environments. By providing a comprehensive testing system for simulating the overcooling and multiphase erosion of power-end blades in polar environments, the system can simulate the operational service state of power-end blades at a low cost. By creating a polar environment, one or more substances, including water mist, ice chips, ice crystals, and mosses, are mixed and doped in a phase flow and then injected onto the operating power-end blades to investigate their service performance under the combined effects of overcooling, dynamic icing, and multiphase erosion in polar environments.

[0006] The present invention provides a comprehensive test system for simulating polar environment power end blade overcooling and multiphase flow erosion, comprising a blade operation simulation unit, a low temperature environment simulation unit, and a medium filling device, wherein the blade operation simulation unit comprises a cylindrical shell, a leak-proof cover, power end blades, a main shaft, a rotor, a high-temperature bearing, and a support frame, wherein the cylindrical shell is horizontally arranged, the main shaft is fixed to the central axis of the cylindrical shell through the support frame, a high-temperature bearing is arranged between the main shaft and the support frame, a rotor is arranged on the main shaft, the power end blades are mounted on the rotor along the circumferential direction, and an insulation layer and a heating device are arranged on the inner wall of the cylindrical shell; an anti-leakage cover is provided at the air inlet end of the blade operation simulation unit, an inner spiral pipe extends into the leak-proof cover and faces the power end blades, and the inner wall of the inner spiral pipe is provided with spiral rifling;

[0007] The medium filling device includes a pressure-compensating channel, a moss-filled cabin, an ice-chip-filled cabin, an ice-crystal-filled cabin, a water mist-filled cabin, a water-filled cabin, a spiral structure pipe and a mixing chamber. The moss-filled cabin, the ice-chip-filled cabin, the ice-crystal-filled cabin, the water mist-filled cabin and the water-filled cabin are arranged in a fan shape. The pressure-compensating channel is sequentially connected with the moss-filled cabin, the ice-chip-filled cabin, the ice-crystal-filled cabin, the water mist-filled cabin and the water-filled cabin through a branch pipe. A valve is provided on the branch pipe. The moss-filled cabin, the ice-chip-filled cabin, the ice-crystal-filled cabin, the water mist-filled cabin and the water-filled cabin are respectively connected with the mixing chamber through a conduit. The lower part of the mixing chamber is connected with the erosion medium pipeline through a connecting pipe. The outer sleeve of the mixing chamber is provided with a spiral structure pipe, and the spiral structure pipe is connected to the medium pre-cooling device.

[0008] The low-temperature environment simulation unit includes a medium pre-cooling device, a pressure-sustaining tank, a booster, a low-temperature cold air pipeline and an extreme cold device. The booster is connected to the pressure-sustaining tank through a pipeline. The first outlet of the pressure-sustaining tank is connected to the pressure-compensating channel. The second outlet of the pressure-sustaining tank is connected to the inlet of the extreme cold device through the boosting channel. One end of the erosion medium pipeline is connected to the boosting channel. The other end of the erosion medium pipeline is connected to the inlet of the inner spiral pipeline through a tee. The outlet of the extreme cold device is connected to the inlet of the inner spiral pipeline through a tee through the low-temperature cold air pipeline.

[0009] The present invention provides a comprehensive test system for supercooling and multiphase flow erosion of power end blades in a simulated polar environment. The multiphase flow erosion comprehensive test system mainly includes a blade operation simulation unit, a low temperature environment simulation unit, a composite erosion unit (i.e., a medium filling device) and a dust removal device.

[0010] The blade operation simulation unit mainly heats the blades and provides them with a high-speed rotating motion state, while also constructing the service temperature environment of the engine blades. The low-temperature environment simulation unit mainly simulates the low-temperature environment of the polar regions, providing a polar low-temperature service atmosphere for the blades in service. The composite erosion unit mainly provides a variety of media such as water mist, ice chips, ice crystals, and mosses in the phase flow simulated by the engine intake, while accelerating the media to a high-speed motion state through airflow impact. In conjunction with the low-temperature environment simulation unit, the low-temperature pre-cooled mixed medium is mixed with the extremely cold airflow and then rushed into the blade operation simulation unit through the outlet of the inner spiral pipe. The dust removal device mainly purifies the gas ejected from the tail of the blade operation simulation unit and the erosion medium at the outlet to achieve the purpose of protecting the environment. Finally, with the combined action of multiple units and devices, a comprehensive performance test of blade supercooling dynamic icing and multiphase flow erosion in a simulated polar environment is achieved.

[0011] The present invention utilizes a low-temperature environment simulation unit and a composite erosion unit to simulate polar environments. Through sensor test data feedback and intelligent computer control of the system, combined with a blade operation simulation unit and dust removal device, it can simulate polar environments and test the multiphase flow erosion (scour) performance of power-end blades. Furthermore, the system can conduct laboratory tests of power-end blade overcooling and multi-medium mixed complex phase flow erosion in polar environments. The environment, medium type, and external service environment can all be intelligently adjusted to meet the diverse needs of power-end blades in polar low-temperature service environments, solving the problem of laboratory simulation of dynamic icing and multiphase flow erosion comprehensive service testing of power-end blades in polar environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1This is a schematic diagram of the structure of the comprehensive test system for simulating overcooling and multiphase flow erosion of power end blades in polar environments of the present invention. In the figure, 1, heating control device, 2, wire, 3, anti-leakage cover, 4, dust removal device, 5, thermal insulation layer, 6, thermal insulation layer, 7, hinge shaft, 8, bolt, 9, heating device, 10, power end blade, 11, main shaft, 12, limit nut, 13, rotor, 14, high-temperature bearing, 15, support column, 16, computer, 17, inner spiral pipe, 1 8. Tee, 19. Sensor, 20. Low-temperature simulation unit air impact valve, 21. Medium erosion pressure release valve, 22. Pressure compensation channel, 23. Pressure compensation channel valve, 24. Medium pre-cooling device, 25. Medium filling device, 26. Medium flow valve, 27. Pressure gauge, 28. Pre-cooling pipeline, 29. Erosion medium pipeline, 30. Pressure regulating tank, 31. Booster, 32. Power supply, 33. Low-temperature cooling pipeline, 34. Extreme cooling device, 35. Booster channel;

[0013] Figure 2 is a structural schematic diagram of a medium filling device;

[0014] Figure 3 This is a left-view structural diagram of the blade operation simulation unit;

[0015] Figure 4 This is a structural diagram of the inner spiral pipe. DETAILED DESCRIPTION

[0016] Specific embodiment one: This embodiment simulates the polar environment power end blade overcooling and multiphase flow erosion comprehensive test system includes a blade operation simulation unit, a low temperature environment simulation unit and a medium filling device, wherein the blade operation simulation unit includes a cylindrical shell, a leakage prevention cover 3, a power end blade 10, a main shaft 11, a rotor 13, a high temperature bearing 14 and a support frame 15, wherein the cylindrical shell is horizontally placed, the main shaft 11 is fixed on the central axis of the cylindrical shell through the support frame 15, a high temperature bearing 14 is arranged between the main shaft 11 and the support frame 15, a rotor 13 is arranged on the main shaft 11, the power end blade 10 is mounted on the rotor 13 along the circumferential direction, and an insulation layer 6 and a heating device 9 are arranged on the inner wall of the cylindrical shell; an anti-leakage cover 3 is provided at the air inlet end of the blade operation simulation unit, an inner spiral pipe 17 extends into the leakage prevention cover 3 and faces the power end blade 10, and the inner wall of the inner spiral pipe 17 is provided with spiral rifling;

[0017] The medium filling device includes a pressure compensation channel 22, a moss filling chamber 25-1, an ice chip filling chamber 25-2, an ice crystal filling chamber 25-3, a water mist filling chamber 25-4, a water filling chamber 26-5, a spiral structure pipe 25-6 and a mixing chamber 25-7. The moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4 and the water filling chamber 26-5 are arranged in a fan shape. The pressure compensation channel 22 is connected to the moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4 and the water filling chamber 26-5 in sequence. 25-3, the water mist filling chamber 25-4, and the water filling chamber 26-5 are connected through a branch pipe, and a valve is provided on the branch pipe. The moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4, and the water filling chamber 26-5 are respectively connected to the mixing chamber 25-7 through a conduit. The lower part of the mixing chamber 25-7 is connected to the erosion medium pipeline 29 through a connecting pipe. The outside of the mixing chamber 25-7 is provided with a spiral structure pipeline 25-6, which is connected to the medium pre-cooling device 24.

[0018] The low-temperature environment simulation unit includes a medium pre-cooling device 24, a pressure-surge tank 30, a booster 31, a low-temperature cold air pipeline 33 and an extreme cold device 34. The booster 31 is connected to the pressure-surge tank 30 through a pipeline. The first outlet of the pressure-surge tank 30 is connected to the pressure-compensating channel 22. The second outlet of the pressure-surge tank 30 is connected to the inlet of the extreme cold device 34 through the boosting channel 35. One end of the erosion medium pipeline 29 is connected to the boosting channel 35. The other end of the erosion medium pipeline 29 is connected to the inlet of the inner spiral pipeline 17 through a tee 18. The outlet of the extreme cold device 34 is connected to the inlet of the inner spiral pipeline 17 through the low-temperature cold air pipeline 33 through the tee 18.

[0019] Specific embodiment 2: This embodiment differs from the specific embodiment 1 in that a dust removal device 4 is provided at the air outlet end of the blade operation simulation unit.

[0020] The dust removal device in this embodiment is a post-processing device for the gas blown out from the blade operation simulation unit, reducing the impact of impurities in the blown gas on the environment. The position and height of the dust removal device can be adjusted according to actual needs.

[0021] Specific embodiment three: This embodiment is different from specific embodiment one or two in that a heat insulation layer 5 is provided between the support frame 15 and the heating device 9 .

[0022] Specific embodiment 4: This embodiment differs from any one of specific embodiments 1 to 3 in that a medium flow valve 26 is provided on the pipeline connecting the mixing chamber 25 - 7 and the erosion medium pipeline 29 .

[0023] Specific embodiment 5: This embodiment differs from any one of specific embodiments 1 to 4 in that the heating device 9 is connected to the heating control device 1 via a wire 2 .

[0024] Specific embodiment 6: This embodiment is different from specific embodiments 1 to 5 in that limiting nuts 12 are provided at both ends of the main shaft 11 .

[0025] The limiting nut is provided in this embodiment to prevent the rotor from flying out from both sides.

[0026] Specific embodiment seven: This embodiment differs from any one of specific embodiments one to six in that a medium erosion pressure release valve 21 and a pressure gauge 27 are provided on the erosion medium pipeline 29 .

[0027] Specific embodiment eight: This embodiment differs from any one of specific embodiments one to seven in that a sensor 19 is provided in the inner spiral pipe 17 .

[0028] The sensor in this embodiment can detect the phase flow velocity, temperature, humidity, etc. at the outlet of the inner spiral pipe in real time, and can realize a real-time feedback function.

[0029] Specific embodiment 9: This embodiment is different from specific embodiments 1 to 8 in that the main shaft 11 is driven to rotate by a motor, and the speed of the main shaft 11 is controlled to be 0-5000 r / min.

[0030] In this embodiment, the radius of the rotor on the main shaft is between 10 cm and 50 cm.

[0031] Specific embodiment ten: This embodiment differs from specific embodiments one to nine in that the temperature of the medium in the inner spiral pipe 17 is controlled to be -70°C-0°C, and the maximum speed of the air impulse device is 70m / s.

[0032] Embodiment: The present embodiment simulates the comprehensive test system for overcooling and multiphase flow erosion of power-end blades in polar environments, including a blade operation simulation unit, a low-temperature environment simulation unit and a medium filling device, wherein the blade operation simulation unit includes a cylindrical shell, a leakage prevention cover 3, a power-end blade 10, a main shaft 11, a limit nut 12, a rotor 13, a high-temperature bearing 14 and a support frame 15, wherein the cylindrical shell is horizontally arranged, the main shaft 11 is fixed on the central axis of the cylindrical shell through the support frame 15, a high-temperature bearing 14 is arranged between the main shaft 11 and the support frame 15, a rotor 13 is arranged on the main shaft 11, the power-end blade 10 is mounted on the rotor 13 along the circumferential direction, and an insulation layer 6 and a heating device 9 are arranged on the inner wall of the cylindrical shell; an anti-leakage cover 3 is provided at the air inlet end of the blade operation simulation unit, an inner spiral pipe 17 extends into the leakage prevention cover 3 and faces the power-end blade 10, and a spiral rifling is provided on the inner wall of the inner spiral pipe 17;

[0033] The medium filling device includes a pressure compensation channel 22, a moss filling chamber 25-1, an ice chip filling chamber 25-2, an ice crystal filling chamber 25-3, a water mist filling chamber 25-4, a water filling chamber 26-5, a spiral structure pipe 25-6 and a mixing chamber 25-7. The moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4 and the water filling chamber 26-5 are arranged in a fan shape. The pressure compensation channel 22 is connected to the moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4 and the water filling chamber 26-5 in sequence. The filling chamber 25-4 and the water filling chamber 26-5 are connected by a branch pipe, each of which is provided with a valve. The moss filling chamber 25-1, the ice chip filling chamber 25-2, the ice crystal filling chamber 25-3, the water mist filling chamber 25-4, and the water filling chamber 26-5 are respectively connected to the mixing chamber 25-7 through a conduit. The lower portion of the mixing chamber 25-7 is connected to the erosion medium pipeline 29 through a connecting pipe. A medium flow valve 26 is provided on the connecting pipe. The outside of the mixing chamber 25-7 is provided with a spiral structure pipeline 25-6, which is connected to the medium pre-cooling device 24.

[0034] The low temperature environment simulation unit includes a medium pre-cooling device 24, a pressure stabilizing tank 30, a booster 31, a low temperature cold air pipeline 33 and an extreme cold device 34. The booster 31 is connected to the pressure stabilizing tank 30 through a pipeline. The first outlet of the pressure stabilizing tank 30 is connected to the pressure compensation channel 22. A pressure compensation channel valve 23 is provided on the pipeline between the pressure stabilizing tank 30 and the pressure compensation channel 22. The second outlet of the pressure stabilizing tank 30 is connected to the inlet of the extreme cold device 34 through a boosting channel 35. The boosting channel 35 is provided with a low temperature simulation unit air shock. The valve 20 is connected to the boosting channel 35 at one end of the erosion medium pipeline 29, and the other end of the erosion medium pipeline 29 is connected to the inlet of the inner spiral pipeline 17 through the tee 18. The erosion medium pipeline 29 is provided with a medium erosion pressure release valve 21 and a pressure gauge 27. The outlet of the extreme cold device 34 is connected to the inlet of the inner spiral pipeline 17 through the low-temperature cold air pipeline 33 through the tee 18. The tee 18 is set at the inlet of the inner spiral pipeline 17 by a snap. A sensor 19 is provided in the inner spiral pipeline 17.

[0035] In this embodiment, the cylindrical outer shell of the blade motion simulation unit is divided into two semicircular shells, which are hinged via a hinge shaft 7. The open and closed ends of the two semicircular shells are connected by bolts 8. The two ports of the blade motion simulation unit can be sealed to achieve excellent thermal insulation. The vehicle column connected to the wheel of this system can be raised and lowered to adjust the position and height of the blade motion simulation unit.

[0036] This embodiment provides an experimental system for comprehensive testing of power-end blade overcooling and multiphase flow erosion in simulated polar environments. It includes a heating control device 1 connected to a heating element 9. An insulation layer 6, located outside the resistance wire, primarily provides a constant temperature atmosphere for the blade operation simulation unit, with a heating range of room temperature to 1000°C. The device housing can be opened by loosening bolts 8 beneath the insulation layer 6. After loosening the retaining nuts 12 at each end of the main shaft, the rotor 13 can be removed or moved, and the blades can be installed onto the rotor 13. The rotor can then be adjusted to the desired number and position.

[0037] The main shaft 11 is mounted on a support frame and realizes its high-speed and high-temperature rotation function through a high-temperature bearing 14. The two ends are connected to the limit nuts 12 connected thereto to prevent the rotor from flying out on both sides.

[0038] During the experiment, after setting the blade's ambient atmosphere and motion state, the gas flow from the left inner spiral conduit 17 needed to be adjusted. In the device controlling this atmosphere, a booster 31 uses its own pressure gauge to measure pressure and compresses gas into a surge tank 30. Two pipelines branch from the surge tank 30. The upper pressure-compensating channel 22 branches off to compensate for the pressure of the medium filling device 25. A pressure-compensating valve 23 is installed at the outlet of the pressure-compensating channel 22 to adjust the pressure.

[0039] The structural diagram of the medium filling device is as follows Figure 2 As shown. This unit adopts a fan-shaped curved design structure, and compactly designs the pressure-compensating channel 22, moss-filled chamber 25-1, ice-filled chamber 25-2, ice crystal-filled chamber 25-3, water mist-filled chamber 25-4, water-filled chamber 26-5, and spiral structure pipe 25-6. Valves are installed in the pressure-compensating channels of each device, and switches and detection instruments are installed at the outlet position. The valves and switches in this unit are all controlled by the computer 16, and the outlets of each chamber of the medium filling device 25 are all collected in a specific channel to achieve the mixing function of various media. At the same time, the outflow material in the chamber flows to the main pipeline, and the outer periphery of the main pipeline is pre-cooled by the spiral structure pipe 25-6. The cold air flow in the pre-cooling device 24 runs within the spiral structure, providing a pre-cooled low-temperature environment for the material in the pipeline and achieving medium temperature regulation.

[0040] By observing the data displayed by the sensor 19 at the outlet of the inner spiral pipe 17, the humidity, flow rate, temperature and other parameters of the gas at the outlet can be intuitively observed. Furthermore, the parameters can be adjusted by adjusting the low-temperature simulation unit air impact valve 20, the medium erosion pressure release valve 21, the medium flow valve 26 and related devices, and finally the required test standard can be constructed.

[0041] In addition, a power supply 32 is connected to the supercharger 31 to provide power. A valve 20 is located at the front end of the pressure replenishment process for the extreme cold device to adjust the replenishment pressure. The pressure replenishment gas and the cold air generated by the extreme cold device are collected in the low-temperature cold air duct 33. Furthermore, the outflowing medium from the medium filling device 25, after pre-cooling, flows into the erosion medium duct 29. Adjusting the medium erosion pressure release valve 21 can adjust the flow rate of the gas and mixed solid medium within the erosion medium duct 29. Both the erosion medium duct 29 and the low-temperature cold air duct 33 are constructed of double-layered polar ship steel to minimize internal cold air loss and meet service requirements. Furthermore, at the outlets of the erosion medium duct 29 and the low-temperature cold air duct 33, both ducts are connected to the inner spiral duct 17 via a tee. A sensor 19 is located at the outlet of the inner spiral duct 17 to monitor the flow rate, temperature, and humidity at the outlet. There is a leak-proof cover 3 outside the inner spiral pipe 17, which can adjust the relative position with the outlet of the inner spiral pipe 17 and ensure that it maintains a horizontal relationship with the blade operation simulation unit. The leak-proof cover 3 can be used to reabsorb the blocks generated by the impact of the solids in the impacting fluid and the blades, and the solids can be re-absorbed under the suction of the blade operation simulation unit to reduce experimental errors.

[0042] In this embodiment, the blade operation simulation unit and the dust removal device 6 are designed with a structure that can be raised and lowered and moved horizontally, and the relative positions can be adjusted according to specific requirements. There is a hinged shaft 7 structure at the top of the blade operation simulation unit, and the opening and closing rotation of the outer shell of the blade operation simulation unit is completed by hinge. The heating parameters of the heating device 9 can be controlled by the computer 16, and the device divides the heating device 9 into 3 sections, and the heating temperature of each section can be set separately to realize the segmented heating function. Regarding the design of the inner spiral pipe 17, the pipe is also made of polar ship steel, and the spiral rifling design is used to simulate the movement state of the material inside the inhaled engine. In addition, the test valves in the comprehensive test system are all controlled by the computer 16, and the heating control device 1, the pre-cooling device 24, the supercharger 31 and the extreme cold device 34 are parameterized by their own equipment. In addition, Figure 4 It is a cross-sectional schematic diagram of the inner spiral pipe 17 and its left view, which can more intuitively understand the internal structure of the sleeve.

[0043] Application Example: This embodiment simulates the polar environment. The comprehensive performance test method for ice erosion of power end blades is implemented by the following steps:

[0044] S1. Conduct safety inspections on the blade operation simulation unit, low temperature environment simulation unit, composite erosion unit, etc. to ensure the reliability of all parts;

[0045] S2. Weigh each blade to be tested and record the weight. Remove bolts 8, open the housing, remove the retaining nuts 12, and remove the rotor 13 to facilitate installation. Adjust the number of blades 10 to be installed and their slot positions on the spindle 11 according to test requirements. Check the installation symmetry, install the retaining nuts 12, and close the housing. Turn on the power supply 32 and heating control device 1, and control the temperature of the device according to the required temperature using the computer 16.

[0046] S3. Turn on the booster 31 to prepare the pressure, open the low-temperature simulation unit air-blast valve 20 to adjust the air flow speed, and release the erosion gas at a lower speed; after the ventilation is completed, turn on the extreme cold device 34, which can cool the (gaseous) medium to -70°C-0°C. After stable operation, adjust the low-temperature simulation unit air-blast valve 20 to adjust the air flow. As the gas flows into the low-temperature cold air pipe 33, the temperature in the pipe gradually decreases, and under the connection of the tee 18, the air flow enters the inner spiral pipe 17;

[0047] S4. Turn on the pre-cooling device 24 to create a low-temperature environment (-10°C to 0°C), and fill the water mist, ice chips, ice crystals, and mosses in the medium filling device 25 into different compartments. At the same time, adjust the pressure compensation channel valve 23 to adjust the pressure compensation airflow. Parameters are set by the computer 16 according to the type, content, and size of the medium required for the actual test, and monitoring is performed by the detection instruments at the exit of each compartment.

[0048] S5. Simultaneously start the low-temperature environment simulation unit and the composite erosion unit, adjust the parameters such as the humidity, flow rate, and content of the erosion medium according to the reading feedback of the sensor 19, and then shut down the equipment;

[0049] S6. After the blade operation simulation unit is heated to the specified temperature, the closed ends are opened and the blade operation simulation unit is moved to a position corresponding to the inner spiral pipe 17. The dust removal device is then adjusted and moved to the rear of the blade operation simulation unit, and the experiment is ready to begin.

[0050] S7. Set the rotation speed of blade 10 according to actual needs. After the blade runs stably, adjust the equipment parameters to the same parameters as in step S5, and start the low-temperature environment simulation unit, composite erosion unit and other related equipment to start the comprehensive service performance test experiment of the blade under polar environment supercooling and multiphase flow erosion;

[0051] S8. After a certain period of time, the experiment ends. After the system cools down, the bolts 8 of the fixing device housing are opened, the limit nuts 12 are removed, and the blades 10 are taken out. The damage of each blade is observed and then weighed. The serviceability of the power end blades is evaluated based on the weight change and damage.

[0052] S9. Through the coordinated action of the computer 16 and various systems, by changing parameters such as the flushing rate, flushing time, blade service environment temperature and rotation speed, the above steps S1-S8 are repeated to perform service performance tests under different conditions.

Claims

1. Comprehensive test system for simulating polar environment power end blade overcooling and multiphase flow erosion, characterized by The comprehensive test system comprises a blade operation simulation unit, a low temperature environment simulation unit and a medium filling device, wherein the blade operation simulation unit comprises a cylindrical shell, a leakage prevention cover (3), a power end blade (10), a main shaft (11), a rotor (13), a high temperature bearing (14) and a support frame (15), wherein the cylindrical shell is horizontally arranged, the main shaft (11) is fixed on the central axis of the cylindrical shell through the support frame (15), a high temperature bearing (14) is arranged between the main shaft (11) and the support frame (15), a rotor (13) is arranged on the main shaft (11), the power end blade (10) is mounted on the rotor (13) along the circumferential direction, and a heat insulation layer (6) and a heating device (9) are arranged on the inner wall of the cylindrical shell; an air inlet end of the blade operation simulation unit is provided with a leakage prevention cover (3), an inner spiral pipe (17) extends into the leakage prevention cover (3) and faces the power end blade (10), and the inner wall of the inner spiral pipe (17) is provided with spiral rifling; The medium filling device comprises a pressure replenishing channel (22), a moss-filled chamber (25-1), an ice-chip filled chamber (25-2), an ice crystal filled chamber (25-3), a water mist filled chamber (25-4), a water filled chamber (26-5), a spiral structure pipe (25-6) and a mixing chamber (25-7). The moss-filled chamber (25-1), the ice-chip filled chamber (25-2), the ice crystal filled chamber (25-3), the water mist filled chamber (25-4) and the water filled chamber (26-5) are arranged in a fan shape. The pressure replenishing channel (22) is connected to the moss-filled chamber (25-1), the ice-chip filled chamber (25-2), the ice crystal filled chamber (25-3), the water mist filled chamber (25-4) and the water filled chamber (26-5) in sequence. The chamber (25-3), the water mist filling chamber (25-4) and the water filling chamber (26-5) are connected through a branch pipe, and a valve is provided on the branch pipe. The moss filling chamber (25-1), the ice chip filling chamber (25-2), the ice crystal filling chamber (25-3), the water mist filling chamber (25-4) and the water filling chamber (26-5) are respectively connected to the mixing chamber (25-7) through a conduit. The lower part of the mixing chamber (25-7) is connected to the erosion medium pipeline (29) through a connecting pipe. The outside of the mixing chamber (25-7) is provided with a spiral structure pipeline (25-6), and the spiral structure pipeline (25-6) is connected to the medium pre-cooling device (24). The low-temperature environment simulation unit includes a medium pre-cooling device (24), a pressure-stabilizing tank (30), a booster (31), a low-temperature cold air pipeline (33) and an extreme cold device (34). The booster (31) is connected to the pressure-stabilizing tank (30) through a pipeline. The first outlet of the pressure-stabilizing tank (30) is connected to the pressure-compensating channel (22). The second outlet of the pressure-stabilizing tank (30) is connected to the inlet of the extreme cold device (34) through a boosting channel (35). One end of the erosion medium pipeline (29) is connected to the boosting channel (35). The other end of the erosion medium pipeline (29) is connected to the inlet of the inner spiral pipeline (17) through a tee (18). The outlet of the extreme cold device (34) is connected to the inlet of the inner spiral pipeline (17) through the low-temperature cold air pipeline (33) through the tee (18).

2. The comprehensive test system for supercooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that A dust removal device (4) is provided at the air outlet end of the blade operation simulation unit.

3. The comprehensive test system for supercooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that A heat insulating layer (5) is provided between the support frame (15) and the heating device (9).

4. The comprehensive test system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that A medium flow valve (26) is provided on a pipeline communicating between the mixing chamber (25-7) and the erosion medium pipeline (29).

5. The comprehensive testing system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that The heating device (9) is connected to the heating control device (1) via a wire (2).

6. The comprehensive testing system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that Limiting nuts (12) are provided at both ends of the main shaft (11).

7. The comprehensive test system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that A medium erosion pressure release valve (21) and a pressure gauge (27) are provided on the erosion medium pipeline (29).

8. The comprehensive testing system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that A sensor (19) is arranged in the inner spiral pipe (17).

9. The comprehensive testing system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that The main shaft (11) is driven to rotate by a motor, and the speed of the main shaft (11) is controlled to be 0-5000r / min.

10. The comprehensive testing system for overcooling and multiphase flow erosion of power end blades in simulated polar environments according to claim 1 is characterized in that The temperature of the medium in the inner spiral pipe (17) is controlled to be -70°C to 0°C, and the maximum speed of the air impact device is 70m / s.

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