CN115876628A - Comprehensive testing system for simulating pole environment power end blade supercooling and multiphase flow erosion - Google Patents
Comprehensive testing system for simulating pole environment power end blade supercooling and multiphase flow erosion Download PDFInfo
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Abstract
The invention discloses a comprehensive test system for simulating supercooling and multi-phase flow erosion of a power end blade in polar environment, and aims to solve the problem that the power end blade lacks service state simulation test equipment under polar environment conditions. The comprehensive test system comprises a blade operation simulation unit, a low-temperature environment simulation unit and a medium filling device, wherein a plurality of rotors are arranged on a main shaft in the blade operation simulation unit, power end blades are arranged on the rotors along the circumferential direction, an inner spiral pipeline extends into an anti-leakage cover and faces the power end blades, the medium filling device comprises a plurality of filling cabins, a pressure supplementing channel is communicated with each filling cabin, and the low-temperature environment simulation unit comprises a medium precooling device, a pressure stabilizing tank, a supercharger, a low-temperature cold air pipeline and an extreme cooling device. The invention realizes polar environment simulation through the low-temperature environment simulation unit and the composite erosion unit, and can realize multiphase flow erosion performance test of the power end blade under the simulated polar environment by combining the blade operation simulation unit, the dust removal device and the like.
Description
Technical Field
The invention belongs to the field of material performance testing devices, and particularly relates to a comprehensive testing device for simulating supercooling and multi-phase flow erosion of a power end blade in a polar environment.
Background
When an aircraft engine, a gas turbine, or the like operates in a polar environment, the multistage blade is required to be subjected to not only more than 20 kinds of loads such as high temperature, stress, and corrosive environment, but also the influence of an inhalant such as fog, snow, ice, or the like in an external low-temperature environment. Hard objects such as polar block ice and the like are sucked into the air inlet channel, so that the high-speed rotating blade is easy to damage and even break; the existence of cold airflow can cause the icing of the surface of the rotor blade, and the running of the blade with overload and uneven load distribution can cause the vibration phenomenon of the rotor; when the blades are in a high-speed rotating state, the comprehensive effects of icing adsorption and heat generation can cause icing to fall off, and the falling ice blocks impact the outer wall and generate crushed ice to cause secondary damage to the engine, so that unexpected parking is caused. For a roadbed/sea-based wind power generation device which operates under extreme conditions, when a component of the roadbed/sea-based wind power generation device is in service in a polar low-temperature environment for a long time, a rotor blade is subjected to the comprehensive scouring action of low-temperature high-speed airflow mixed with media such as fog, snow, ice and the like for a long time, so that the service life of the power generation device is shortened, and the operation safety of a fan blade is difficult to guarantee. In addition, when a propeller-driven aircraft such as a helicopter flies under extreme conditions, the operation of the propeller blades also faces the problems of low-temperature icing, hard object impact and the like.
At present, partial personnel carry out corresponding work aiming at the service behavior of the power end blade. Fidelity et al fully simulated the high-temperature service environment of an aircraft engine by applying alternating stress to an external force application assembly and a workpiece and performing a coupling experiment, and studied the influence of the alternating stress on the service performance of the engine; the inventor of the brave et al researches the failure mechanism of the thermal barrier coating of the high-temperature rotor in the high-temperature service environment by heating the rotor blade and spraying the corrosive medium on the surface of the rotor blade; zhang Bo et al utilize air pump and sand storage cylinder to carry out the sand grain and mix and simulate the pneumatic load characteristic that fan blade was washed out to research and simulate the erosion effect of sand environment to fan blade. Currently, researchers mainly conduct research on service states of blades at power ends under the action of stress, media and the like in normal-temperature and high-temperature environments.
However, currently, research on service behaviors of power end blades serving in some special service environments, especially in polar environment conditions, is not yet developed, and failure mechanisms of the blades in polar low-temperature complex environments are not clear, so that the requirements of polar scientific investigation, natural resource exploration and autonomous development in the future of China are limited. Therefore, a system capable of simulating supercooling atmosphere and multiphase flow scouring to test the service performance of the power end blade in the polar environment is urgently needed to fill the blank of the comprehensive service performance test of the power end blade in the polar environment at present, and the system has important scientific and practical significance for polar resource development, polar equipment protection, polar safety and the like in China.
Disclosure of Invention
The invention aims to solve the problem that a power end blade lacks test equipment for simulating the service state under the polar environment condition, and provides a comprehensive test system for simulating the supercooling and multiphase flow erosion of the power end blade under the polar environment, so that the running service state of the power end blade can be simulated under the condition of lower cost. One or more substances such as water mist, ice slag, ice crystals, moss and the like are mixed and doped in a phase flow and then are ejected to the blades at the running power end through polar environment construction, so that the service performance of the blades at the power end under the comprehensive actions of super-cooling dynamic ice hanging and multiphase flow erosion in the polar environment is researched.
The invention relates to a comprehensive testing system for simulating supercooling of blades at a power end of a polar environment and erosion of multiphase flow, which 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, an anti-leakage cover, blades at the power end, a main shaft, a rotor, a high-temperature bearing and a support frame, the cylindrical shell is transversely arranged, the main shaft is fixed on a central axis of the cylindrical shell through the support frame, the high-temperature bearing is arranged between the main shaft and the support frame, the rotor is arranged on the main shaft, the blades at the power end are arranged on the rotor along the circumferential direction, and a heat insulation layer and a heating device are arranged on the inner wall of the cylindrical shell; an air inlet end of the blade operation simulation unit is provided with an anti-leakage cover, an inner spiral pipeline extends into the anti-leakage cover and faces the blades at the power end, and the inner wall of the inner spiral pipeline is provided with a spiral rifling;
the medium filling device comprises a pressure supplementing channel, a moss filling cabin, an ice slag filling cabin, an ice crystal filling cabin, a water mist filling cabin, a water filling cabin, a spiral structure pipeline and a mixing chamber, wherein the moss filling cabin, the ice slag filling cabin, the ice crystal filling cabin, the water mist filling cabin and the water filling cabin are arranged in a fan shape;
the low-temperature environment simulation unit comprises a medium precooling device, a pressure stabilizing tank, a supercharger, a low-temperature air cooling pipeline and an extreme cooling device, wherein the supercharger is connected with the pressure stabilizing tank through a pipeline, a first outlet of the pressure stabilizing tank is communicated with a pressure supplementing channel, a second outlet of the pressure stabilizing tank is connected with an inlet of the extreme cooling device through a pressurizing channel, one end of the erosion medium pipeline is communicated with the pressurizing channel, the other end of the erosion medium pipeline is connected with an inlet of the inner spiral pipeline through a tee joint, and an outlet of the extreme cooling device is connected with an inlet of the inner spiral pipeline through a tee joint through the low-temperature air cooling pipeline.
The invention provides a comprehensive test system for simulating supercooling of a power end blade and multi-phase flow erosion in a polar environment.
The blade operation simulation unit is mainly used for heating the blades and providing a high-speed rotating motion state, and meanwhile, constructing the service temperature environment of the engine blades; the low-temperature environment simulation unit is mainly used for simulating the low-temperature environment of the polar region and providing a polar region low-temperature service atmosphere for the service blades; the composite erosion unit is mainly used for providing various media such as water mist, ice slag, ice crystals, moss plants and the like in a phase flow sucked by a simulation engine, accelerating the media to a high-speed motion state through air flow impact, mixing a mixed medium subjected to low-temperature precooling with extremely cold air flow by matching with a low-temperature environment simulation unit, and then flushing the mixed medium into the blade operation simulation unit through an outlet of an inner spiral pipeline; the dust removal device mainly achieves the purification effect on the gas emitted from the tail part of the blade operation simulation unit and the erosion medium at the outlet so as to achieve the effect of protecting the environment. Finally, under the combined action of multiple units and devices, comprehensive performance tests of blade supercooling dynamic ice hanging and multiphase flow erosion under the simulated polar region environment are realized.
The invention realizes polar environment simulation by using the low-temperature environment simulation unit and the composite erosion unit, can realize multiphase flow erosion (scouring) performance test of the power-end blade under the simulated polar environment by using sensor test data feedback and intelligent control of a computer on a system, and combining the blade operation simulation unit, the dust removal device and the like. Moreover, the system can realize the supercooling and multi-medium-doped complex-phase flow scouring test experiment of the power end blade in the polar region environment under the laboratory condition, the environment, the medium type and the external service environment can be intelligently adjusted, the multi-change requirement of the low-temperature service environment of the polar region of the power end blade can be met, and the laboratory simulation problem of simulating dynamic ice coating and multi-phase flow scouring comprehensive service test of the power end blade in the polar region environment is solved.
Drawings
Fig. 1 is a schematic structural diagram of a power end blade supercooling and multiphase flow erosion comprehensive test system under a simulated polar region environment of the invention, wherein 1, a heating control device, 2, a lead, 3, a leakage prevention cover, 4, a dust removal device, 5, a heat insulation layer, 6, a heat insulation layer, 7, a hinge shaft, 8, a bolt, 9, a heating device, 10, a power end blade, 11, a main shaft, 12, a limit nut, 13, a rotor, 14, a high-temperature bearing, 15, a support column, 16, a computer, 17, an internal spiral pipeline, 18, a tee joint, 19, a sensor, 20, a low-temperature simulation unit air erosion valve, 21, a medium erosion pressure release valve, 22, a pressure compensation channel, 23, a pressure compensation channel valve, 24, a medium precooling device, 25, a medium filling device, 26, a medium flow valve, 27, a pressure gauge, 28, a precooling pipeline, 29, an erosion medium pipeline, 30, a pressure stabilization tank, 31, a supercharger, 32, a power supply, 33, a low-temperature pipeline, 34, an extreme cooling device, 35, and a pressurization channel;
FIG. 2 is a schematic structural view of a medium filling apparatus;
FIG. 3 is a left side view of the blade operation simulation unit;
fig. 4 is a schematic structural diagram of an internal spiral pipeline.
Detailed Description
The first specific implementation way is as follows: the comprehensive testing system for simulating the supercooling of the blades at the power end of the polar environment and the erosion of multiphase flow 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, an anti-leakage cover 3, a power end blade 10, a main shaft 11, a rotor 13, a high-temperature bearing 14 and a support frame 15, the cylindrical shell is transversely arranged, the main shaft 11 is fixed on the central axis of the cylindrical shell through the support frame 15, the high-temperature bearing 14 is arranged between the main shaft 11 and the support frame 15, the rotor 13 is arranged on the main shaft 11, the power end blade 10 is installed 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; the air inlet end of the blade operation simulation unit is provided with an anti-leakage cover 3, an inner spiral pipeline 17 extends into the anti-leakage cover 3 and faces the power end blade 10, and the inner wall of the inner spiral pipeline 17 is provided with a spiral rifling;
the medium filling device comprises a pressure supplementing channel 22, a moss filling cabin 25-1, an ice ballast filling cabin 25-2, an ice crystal filling cabin 25-3, a water mist filling cabin 25-4, a water filling cabin 26-5, a spiral structure pipeline 25-6 and a mixing chamber 25-7, wherein the moss filling cabin 25-1, the ice ballast filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 are arranged in a fan shape, the pressure supplementing channel 22 is sequentially communicated with the moss filling cabin 25-1, the ice ballast filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 through branch pipes, valves are arranged on the branch pipes, the moss filling cabin 25-1, the ice ballast filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 are respectively communicated with the mixing chamber 25-7 through guide pipes, the lower part of the mixing chamber 25-7 is communicated with the mixing chamber 25-7 through a spiral structure pipeline 25-6, and a spiral structure pipeline 29-6 is sleeved on the mixing chamber;
the low-temperature environment simulation unit comprises a medium precooling device 24, a surge tank 30, a booster 31, a low-temperature cold air pipeline 33 and an extreme cold device 34, wherein the booster 31 is connected with the surge tank 30 through a pipeline, a first outlet of the surge tank 30 is communicated with a pressure supplementing channel 22, a second outlet of the surge tank 30 is connected with an inlet of the extreme cold device 34 through a pressure boosting channel 35, one end of an erosion medium pipeline 29 is communicated with the pressure boosting channel 35, the other end of the erosion medium pipeline 29 is connected with an inlet of the internal spiral pipeline 17 through a tee joint 18, and an outlet of the extreme cold device 34 is connected with an inlet of the internal spiral pipeline 17 through the low-temperature cold air pipeline 33 through the tee joint 18.
The second embodiment is as follows: the difference between the first embodiment and the second embodiment is that a dust removing device 4 is arranged at the air outlet end of the blade operation simulation unit.
The dust removing device of the embodiment is used for post-processing of gas in the device after being blown out from the blade operation simulation unit, and reduces the influence of impurities mixed in the blown-out gas on the environment. And the position and the height of the dust removing device can be adjusted according to actual requirements.
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that a thermally insulating layer 5 is provided between the support frame 15 and the heating device 9.
The fourth concrete implementation mode: the present embodiment differs from one of the first to third embodiments in that a medium flow valve 26 is provided in a conduit in which the mixing chamber 25-7 communicates with the erosion medium conduit 29.
The fifth concrete implementation mode is as follows: the present embodiment differs from one of the first to fourth embodiments in that the heating device 9 is connected to the heating control apparatus 1 through the lead wire 2.
The sixth specific implementation mode is as follows: the difference between this embodiment and one of the first to fifth embodiments is that the two ends of the main shaft 11 are provided with the limit nuts 12.
The present embodiment is provided with the limit nut to prevent the rotor from flying out from both sides.
The seventh concrete implementation mode: the present embodiment is different from one of the first to sixth embodiments in that a medium erosion pressure relief valve 21 and a pressure gauge 27 are provided in the erosion medium pipe 29.
The specific implementation mode eight: the present embodiment differs from one of the first to seventh embodiments in that a sensor 19 is provided in the inner spiral duct 17.
The sensor of the embodiment can detect the phase flow speed, the temperature, the humidity and the like of the outlet of the inner spiral pipeline in real time, and can realize the real-time feedback function.
The specific implementation method nine: the difference between the first embodiment and the eighth embodiment is that the main shaft 11 is driven by a motor to rotate, and the rotation speed of the main shaft 11 is controlled to be 0-5000r/min.
The radius of the rotor on the main shaft of the embodiment is between 10cm and 50 cm.
The detailed implementation mode is ten: the difference between this embodiment and one of the first to ninth embodiments is that the temperature of the medium in the inner spiral pipe 17 is controlled to be-70 ℃ -0 ℃, and the maximum speed of the air-blast device is 70m/s.
Example (b): the comprehensive testing system for simulating the supercooling of the power end blade and the erosion of multiphase flow in the polar environment 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, an anti-leakage cover 3, a power end blade 10, a main shaft 11, a limiting nut 12, a rotor 13, a high-temperature bearing 14 and a support frame 15, the cylindrical shell is transversely arranged, the main shaft 11 is fixed on the central axis of the cylindrical shell through the support frame 15, the high-temperature bearing 14 is arranged between the main shaft 11 and the support frame 15, the rotor 13 is arranged on the main shaft 11, the power end blade 10 is installed on the rotor 13 in the circumferential direction, and a heat insulation layer 6 and a heating device 9 are arranged on the inner wall of the cylindrical shell; the air inlet end of the blade operation simulation unit is provided with an anti-leakage cover 3, an inner spiral pipeline 17 extends into the anti-leakage cover 3 and faces the power end blade 10, and the inner wall of the inner spiral pipeline 17 is provided with a spiral rifling;
the medium filling device comprises a pressure supplementing channel 22, a moss filling cabin 25-1, a moss filling cabin 25-2, an ice crystal filling cabin 25-3, a water mist filling cabin 25-4, a water filling cabin 26-5, a spiral structure pipeline 25-6 and a mixing chamber 25-7, wherein the moss filling cabin 25-1, the moss filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 are arranged in a fan shape, the pressure supplementing channel 22 is sequentially communicated with the moss filling cabin 25-1, the moss filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 through branch pipes, each branch pipe is provided with a valve, the moss filling cabin 25-1, the moss filling cabin 25-2, the moss filling cabin 25-3, the water mist filling cabin 25-4 and the water filling cabin 26-5 are respectively communicated with the mixing chamber 25-7 through guide pipes, the lower part of the mixing chamber 25-7 is communicated with the medium filling cabin 25-7 through a connecting pipe 29, the spiral structure pipeline 25-6 is arranged on the mixing chamber 25-7, and the spiral structure is sleeved with the medium filling pipeline 25-6;
the low-temperature environment simulation unit comprises a medium precooling device 24, a surge tank 30, a booster 31, a low-temperature cold air pipeline 33 and an ultra-cold device 34, wherein the booster 31 is connected with the surge tank 30 through a pipeline, a first outlet of the surge tank 30 is communicated with a pressure supplementing channel 22, a pressure supplementing channel valve 23 is arranged on the pipeline between the surge tank 30 and the pressure supplementing channel 22, a second outlet of the surge tank 30 is connected with an inlet of the ultra-cold device 34 through a pressure boosting channel 35, a low-temperature simulation unit air flushing valve 20 is arranged on the pressure boosting channel 35, one end of an erosion medium pipeline 29 is communicated with the pressure boosting channel 35, the other end of the erosion medium pipeline 29 is connected with an inlet of the internal spiral pipeline 17 through a tee joint 18, a medium erosion pressure release valve 21 and a pressure gauge 27 are arranged on the erosion medium pipeline 29, an outlet of the ultra-cold device 34 is connected with an inlet of the internal spiral pipeline 17 through the low-temperature cold air pipeline 33 through the tee joint 18, the tee joint 18 is arranged at the inlet of the internal spiral pipeline 17 through a buckle, and a sensor 19 is arranged in the internal spiral pipeline 17.
In this embodiment, the cylindrical casing of the blade operation simulation unit is divided into two semicircular shells, the two semicircular shells are hinged through a hinge shaft 7, and the opening ends of the two semicircular shells are connected through a bolt 8. Two ports of the blade operation simulation unit can be closed, so that a good heat preservation effect is realized. The system is connected with the vehicle columns of the wheels, and can realize the lifting function so as to adjust the position and the height of the blade operation simulation unit.
The experiment system for simulating the comprehensive test of the supercooling and multiphase flow scouring of the power end blade in the polar region environment comprises a heating control device 1, a heating device 9 connected with the heating control device, and a heat preservation layer 6 arranged outside a resistance wire, wherein the heat preservation layer is mainly used for providing a certain temperature atmosphere for a blade operation simulation unit, and the heating range is room temperature-1000 ℃. The bolt 8 under the insulation layer 6 is opened, and the device shell can be opened. After the limit nuts 12 at both ends of the main shaft are opened, the rotor 13 can be removed or moved, the blades are mounted on the rotor 13, and the mounting number and position of the rotor are set according to the required conditions.
The main shaft 11 is installed on the supporting frame, and realizes the high-speed and high-temperature rotation function through a high-temperature bearing 14, and two ends of the main shaft are connected with a limit nut 12 connected with the main shaft, so as to prevent the rotor from flying out at two sides.
In the experimental process, after the environmental atmosphere and the motion state of the blade are set, the blown gas of the left inner spiral pipeline 17 needs to be set. In the apparatus for controlling the atmosphere, on the one hand, the booster 31 performs pressure detection by its own pressure gauge and compresses the gas into the surge tank 30. Two pipelines are divided from the surge tank 30, the upper pressure compensating channel 22 compensates the medium filling device 25 through a branch, and a pressure compensating channel valve 23 capable of regulating the magnitude of the pressure compensating pressure is arranged at the outlet of the pressure compensating channel 22.
The schematic structure of the medium filling device is shown in fig. 2. The unit adopts a fan-shaped bent design structure, the pressure supplementing channel 22, the moss filling cabin 25-1, the ice slag filling cabin 25-2, the ice crystal filling cabin 25-3, the water mist filling cabin 25-4, the water filling cabin 26-5, the spiral pipeline 25-6 and other devices are compactly designed, valves are arranged on the pressure supplementing channels of the devices, and a switch and a detection instrument are arranged at an outlet. The valves and switches in the unit are controlled by the computer 16, and the outlets of the compartments of the medium filling device 25 are converged to a specific channel, so as to realize the mixing function of various media. Meanwhile, effluent substances in the cabin flow to the main pipeline, the periphery of the main pipeline is precooled outside by adopting a pipeline 25-6 with a spiral structure, and cold air flow in the precooling device 24 runs in the spiral structure, so that a precooling low-temperature environment is provided for the substances in the pipeline, and the temperature adjustment of the medium is realized.
By observing the data display of the sensor 19 at the outlet of the internal spiral pipeline 17, parameters such as humidity, flow rate and temperature of gas at the outlet can be visually observed, further, parameter adjustment can be realized by adjusting the gas flushing valve 20, the medium flushing pressure release valve 21, the medium flow valve 26 and related devices of the low-temperature simulation unit, and finally, a required test standard is established.
In addition, a power source 32 is connected to the supercharger 31 for providing power. At the front end of the pressure compensation for the cryogenic device, a valve 20 is present, which allows the magnitude of the compensation pressure to be adjusted. The pressure compensating gas and the cold air produced by the ultra-cold device are collected in the low-temperature cold air pipeline 33. In addition, the outflow medium in the pre-cooled medium filling device 25 flows out to the erosion medium pipe 29, and the flow rate of the gas and the mixed solid medium in the erosion medium pipe 29 can be adjusted by adjusting the medium erosion pressure release valve 21. For the erosion medium pipeline 29 and the low-temperature cold air pipeline 33, steel for double-layer polar ships is adopted to reduce the dissipation of internal cold air and reach the service requirement standard. At the outlets of the air flow ducts of the erosion medium duct 29 and the low-temperature cold air duct 33, the two ducts are connected to the inner spiral duct 17 by a tee. The outlet of the internal spiral pipeline 17 is provided with a sensor 19 for detecting the flow rate, temperature, humidity and the like at the outlet. The anti-leakage cover 3 is arranged outside the inner spiral pipeline 17, so that the relative position of the anti-leakage cover 3 and the outlet of the inner spiral pipeline 17 can be adjusted, the horizontal relation between the anti-leakage cover 3 and the blade operation simulation unit can be guaranteed, the block body generated by impact between the solid in the impact fluid and the blade can be reabsorbed, and the solid can be reabsorbed under the suction action of the blade operation simulation unit, so that the experimental error can be reduced.
In this embodiment, the blade operation simulation unit and the dust removing device 6 are designed to have a structure capable of lifting and horizontally moving, and the relative positions can be adjusted according to specific requirements. The top end of the blade operation simulation unit is provided with a hinge shaft 7 structure, and the opening and closing rotation of the shell of the blade operation simulation unit is completed through the 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 each section can be independently set with heating temperature to realize the segmented heating function. Regarding the design of the inner spiral duct 17, the duct is also prepared using steel for polar ships, and the simulation of the motion state of the material sucked into the engine is achieved by the spiral rifling design. The test valves in the integrated test system are controlled by the computer 16, and the heating control device 1, the precooling device 24, the supercharger 31, and the ultra-cooling device 34 are provided with their parameters by their own devices. In addition, fig. 4 is a schematic cross-sectional view of the inner spiral duct 17 and a left side view thereof, so that the internal structure of the sleeve can be more intuitively understood.
The application example is as follows: the method for testing the comprehensive performance of simulating ice-coating scouring of the blades at the power end in the polar region environment is realized according to the following steps:
s1, safety inspection is carried out on a blade operation simulation unit, a low-temperature environment simulation unit, a composite erosion unit and the like, and the use reliability of parts of all parts is guaranteed;
s2, weighing each blade to be measured and recording. The bolt 8 is removed, the shell is opened, the limit nut 12 is removed, and the rotor 13 is removed to facilitate installation. Then adjusting the number of the installation blades 10 and the positions of the clamping grooves arranged on the main shaft 11 according to the test requirements, then checking the installation symmetry, installing the limit nut 12, closing the shell of the device, then turning on the power supply 32 and the heating control device 1, and controlling the temperature of the device through the computer 16 according to the temperature requirements;
s3, opening a supercharger 31 to prepare pressure, opening a low-temperature simulation unit gas flushing valve 20 to adjust the gas flow speed, and releasing the erosion gas at a lower speed; after ventilation is finished, the ultra-cold device 34 is opened, the ultra-cold device 34 can cool the (gaseous) medium to-70-0 ℃, the air blast valve 20 of the low-temperature simulation unit is adjusted to adjust the air flow after the operation is stable, the temperature in the pipeline is gradually reduced along with the flow of the air into the low-temperature cold air pipeline 33, and the air flow enters the inner spiral pipeline 17 under the connection of the tee joint 18;
s4, opening a precooling device 24 to build a low-temperature environment (minus 10-0 ℃), filling water mist, ice slag, ice crystals, moss plants and the like in a medium filling device 25 in different cabins, adjusting a pressure supplementing channel valve 23 to adjust pressure supplementing air flow, setting parameters through a computer 16 according to the type, content, size and the like of a medium required by actual test, and monitoring through a detection instrument at an outlet of each cabin;
s5, simultaneously starting the low-temperature environment simulation unit and the composite erosion unit, adjusting parameters such as humidity, flow rate and content of the scouring medium according to the indication feedback of the sensor 19, and then closing the equipment;
s6, after the temperature of the blade operation simulation unit is raised to a specified temperature, opening the two closed ends, moving the blade operation simulation unit to a position corresponding to the inner spiral pipeline 17, adjusting the dust removal device, moving the dust removal device to the tail of the blade operation simulation unit, and preparing to start an experiment;
s7, setting the rotating speed of the blade 10 according to actual requirements, adjusting equipment parameters to the same parameters in the step S5 after the blade runs stably, starting related equipment such as a low-temperature environment simulation unit, a composite erosion unit and the like, and starting a test experiment of supercooling and multiphase flow scouring on comprehensive service performance of the blade in polar environment;
and S8, after a certain time, ending the experiment. After the system is cooled, opening the bolt 8 of the shell of the fixing device, disassembling the limit nut 12, taking out the blade 10, observing the damage condition of each blade, then weighing the mass of the blade, and evaluating the service capacity of the power end blade according to the weight change and the damage condition;
and S9, repeating the steps from S1 to S8 to test the service performance under different conditions by changing parameters such as the scouring rate, the scouring time, the temperature of the service environment of the blade, the rotating speed and the like through the synergistic action of the computer 16 and each system.
Claims (10)
1. The comprehensive test system for simulating the supercooling of the power end blade and the erosion of multiphase flow in the polar environment is characterized by 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, an anti-leakage cover (3), the power end blade (10), a main shaft (11), a rotor (13), a high-temperature bearing (14) and a support frame (15), the cylindrical shell is transversely arranged, the main shaft (11) is fixed on the central axis of the cylindrical shell through the support frame (15), the high-temperature bearing (14) is arranged between the main shaft (11) and the support frame (15), the rotor (13) is arranged on the main shaft (11), the power end blade (10) is installed on the rotor (13) in 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 an anti-leakage cover (3), an inner spiral pipeline (17) extends into the anti-leakage cover (3) and faces the power end blade (10), and the inner wall of the inner spiral pipeline (17) is provided with a spiral rifling;
the medium filling device comprises a pressure supplementing channel (22), a moss filling cabin (25-1), a moss filling cabin (25-2), an ice crystal filling cabin (25-3), a water mist filling cabin (25-4), a water filling cabin (26-5), a spiral structure pipeline (25-6) and a mixing chamber (25-7), wherein the moss filling cabin (25-1), the moss filling cabin (25-2), the ice crystal filling cabin (25-3), the water mist filling cabin (25-4) and the water filling cabin (26-5) are arranged in a sector shape, the pressure supplementing channel (22) is sequentially communicated with a moss filling cabin (25-1), an ice slag filling cabin (25-2), an ice crystal filling cabin (25-3), a water mist filling cabin (25-4) and a water filling cabin (26-5) through branch pipes, valves are arranged on the branch pipes, the moss filling cabin (25-1), the ice slag filling cabin (25-2), the ice crystal filling cabin (25-3), the water mist filling cabin (25-4) and the water filling cabin (26-5) are respectively communicated with a mixing chamber (25-7) through guide pipes, the lower part of the mixing chamber (25-7) is communicated with an erosion medium pipeline (29) through a connecting pipe, and a spiral structure pipeline (25-6) is sleeved outside the mixing chamber (25-7) ) The spiral structure pipeline (25-6) is connected with the medium precooling device (24);
the low-temperature environment simulation unit comprises a medium precooling device (24), a pressure stabilizing tank (30), a supercharger (31), a low-temperature cold air pipeline (33) and an ultra-cold device (34), wherein the supercharger (31) is connected with the pressure stabilizing tank (30) through a pipeline, a first outlet of the pressure stabilizing tank (30) is communicated with a pressure supplementing channel (22), a second outlet of the pressure stabilizing tank (30) is connected with an inlet of the ultra-cold device (34) through a pressure boosting channel (35), one end of an erosion medium pipeline (29) is communicated with the pressure boosting channel (35), the other end of the erosion medium pipeline (29) is connected with an inlet of the internal spiral pipeline (17) through a tee joint (18), and an outlet of the ultra-cold device (34) is communicated with the inlet of the internal spiral pipeline (17) through the low-temperature cold air pipeline (33) through the tee joint (18).
2. The comprehensive testing system for simulating blade supercooling and multiphase flow erosion at the power end of the polar environment as claimed in claim 1, wherein a dust removing device (4) is arranged at the air outlet end of the blade operation simulating unit.
3. The comprehensive test system for simulating pole environment power end blade supercooling and multiphase flow erosion as claimed in claim 1, wherein a heat insulation layer (5) is arranged between the support frame (15) and the heating device (9).
4. The comprehensive test system for simulating pole environment power end blade supercooling and multiphase flow erosion as claimed in claim 1, wherein a medium flow valve (26) is arranged on a pipeline of the mixing chamber (25-7) communicated with an erosion medium pipeline (29).
5. The comprehensive test system for simulating blade supercooling and multiphase flow erosion at the power end of the polar environment as claimed in claim 1, wherein the heating device (9) is connected with the heating control device (1) through a lead (2).
6. The comprehensive testing system for simulating blade supercooling and multiphase flow erosion at a power end of a polar environment as claimed in claim 1, wherein two ends of a main shaft (11) are provided with limit nuts (12).
7. The comprehensive test system for simulating blade supercooling and multiphase flow erosion at a power end of a polar environment as claimed in claim 1, wherein a medium erosion pressure relief valve (21) and a pressure gauge (27) are arranged on an erosion medium pipeline (29).
8. The comprehensive test system for simulating polar environment power end blade supercooling and multiphase flow erosion as claimed in claim 1, wherein a sensor (19) is arranged in the inner spiral pipeline (17).
9. The comprehensive test system for simulating blade supercooling and multiphase flow erosion at the power end of the polar environment as claimed in claim 1, wherein the main shaft (11) is driven to rotate by a motor, and the rotating speed of the main shaft (11) is controlled to be 0-5000r/min.
10. The comprehensive test system for simulating the supercooling of blades at the power end of the polar environment and the erosion of the multiphase flow as claimed in claim 1, wherein the temperature of a medium in the inner spiral pipeline (17) is controlled to be-70-0 ℃, and the maximum speed of the air-blast device is 70m/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211542829.5A CN115876628A (en) | 2022-12-02 | 2022-12-02 | Comprehensive testing system for simulating pole environment power end blade supercooling and multiphase flow erosion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211542829.5A CN115876628A (en) | 2022-12-02 | 2022-12-02 | Comprehensive testing system for simulating pole environment power end blade supercooling and multiphase flow erosion |
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| Publication Number | Publication Date |
|---|---|
| CN115876628A true CN115876628A (en) | 2023-03-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211542829.5A Pending CN115876628A (en) | 2022-12-02 | 2022-12-02 | Comprehensive testing system for simulating pole environment power end blade supercooling and multiphase flow erosion |
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| Country | Link |
|---|---|
| CN (1) | CN115876628A (en) |
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2022
- 2022-12-02 CN CN202211542829.5A patent/CN115876628A/en active Pending
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