CN113944518B - Turbine blade dynamic test system based on circulation micro-pipeline - Google Patents
Turbine blade dynamic test system based on circulation micro-pipeline Download PDFInfo
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- CN113944518B CN113944518B CN202111052954.3A CN202111052954A CN113944518B CN 113944518 B CN113944518 B CN 113944518B CN 202111052954 A CN202111052954 A CN 202111052954A CN 113944518 B CN113944518 B CN 113944518B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/166—Sliding contact bearing
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention provides a turbine blade dynamic test system based on a circulating micro-pipeline, which comprises a closed heat preservation body, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat preservation body comprises an outer heat preservation wall and an inner heat preservation wall, a vacuum cavity is formed between the outer heat preservation wall and the inner heat preservation wall, and the inner heat preservation wall encloses a test cavity; the refrigerating and heating subsystem comprises a first micro pipeline, a refrigerating module and a heating module, wherein the first micro pipeline is connected with the refrigerating module and the heating module, and the first micro pipeline is arranged in the inner heat-insulating wall; the test subsystem comprises a temperature sensor and a performance test component, and the temperature sensor and the performance test component are arranged in the test cavity; the refrigerating module, the heating module, the temperature sensor and the performance testing assembly are all connected with the control subsystem. The test system can provide a temperature control environment of-50 ℃ to 2000 ℃, can simulate rapid and severe changes of the working environment temperature of the aeroengine, and realizes dynamic test of various performance indexes of the turbine blade under extreme conditions.
Description
Technical Field
The invention belongs to the technical field of turbine detection, and particularly relates to a turbine blade dynamic test system based on a circulation micro-pipeline.
Background
Aeroengines are the highest-end equipment in the field of equipment manufacturing, as the "heart" of an aircraft, reliability and safety of aeroengines are extremely important. The turbine blade is a core component of power output of the aero-engine, and is used for accurately, reliably and continuously monitoring the blade tip clearance on line, so that the turbine blade is a key for guaranteeing safe, efficient and long-service-life operation of the engine, and is one of important preconditions for improving the power output of the engine and enhancing the fighter capability and battlefield viability of the fighter. The flying height of advanced warplanes has now reached 20,000m to 30,000m, at which time the atmospheric temperature is as low as around-50 ℃. The turbine blades are therefore often subjected to high loads and thermal shocks, the operating environment temperature of which can be increased from-50 ℃ at the low pressure compressor to 2,000 ℃ at the combustor, with an exceptionally harsh operating environment.
How to better simulate the working environment of a turbine engine and detect relevant data is the key of turbine detection technology, most of the existing high-temperature detection systems are based on muffle furnace structures, and can detect various parameter changes of the turbine under high-temperature conditions, but the existing detection technologies are single in simulation environment, complicated in switching test environment, incapable of simulating deep cooling to the high-temperature environment and measuring turbine blade dynamic performance, and incapable of simulating rapid and severe changes of the working environment temperature of the aeroengine. Resulting in difficult measurement on data and waste of resources and time.
Disclosure of Invention
The invention aims to solve the technical problems that: the turbine blade dynamic test system based on the circulating micro-pipeline can provide a temperature control environment of-50 ℃ to 2,000 ℃, can simulate rapid and severe changes of the working environment temperature of an aeroengine, and realizes dynamic test of various performance indexes of the turbine blade under extreme conditions.
In order to solve the technical problems, the embodiment of the invention provides a turbine blade dynamic test system based on a circulating micro pipeline, which comprises a closed heat preservation body, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat preservation body comprises an outer heat preservation wall and an inner heat preservation wall, a vacuum cavity is formed between the outer heat preservation wall and the inner heat preservation wall, and the inner heat preservation wall encloses a test cavity; the refrigerating and heating subsystem comprises a first micro pipeline, a refrigerating module and a heating module, wherein the first micro pipeline is connected with the refrigerating module and the heating module, and the first micro pipeline is arranged in the inner heat-preserving wall; the test subsystem comprises a temperature sensor and a performance test component, and the temperature sensor and the performance test component are arranged in the test cavity; the refrigerating module, the heating module, the temperature sensor and the performance testing assembly are all connected with the control subsystem.
As a further improvement of the embodiment of the invention, the invention also comprises a driving subsystem, wherein the driving subsystem comprises a transmission shaft, a sliding bearing and a motor, and the sliding bearing is arranged on the inner heat-insulating wall; the motor is connected with a transmission shaft, the transmission shaft penetrates through the outer heat insulation wall and the sliding bearing, the turbine blade is assembled on the transmission shaft, and the turbine blade is positioned in the test cavity; the motor is connected with the control subsystem.
As a further improvement of the embodiment of the invention, the system further comprises an auxiliary pipe subsystem, wherein the auxiliary pipe subsystem comprises a second micro-pipe and an auxiliary module, the second micro-pipe is connected with the auxiliary module, and the auxiliary module is connected with the control subsystem; the second micro-pipeline is respectively arranged in the inner heat-preserving wall, the transmission shaft and the sliding bearing.
As a further improvement of the embodiment of the present invention, the auxiliary module includes a second refrigerant storage device storing a second refrigerant, a second refrigerant circulation pump and an air pump, where the second refrigerant storage device is connected with the second refrigerant circulation pump, the second refrigerant circulation pump is connected with the second micro-pipe, and the air pump is connected with the second micro-pipe.
As a further improvement of the embodiment of the invention, the heating module comprises a heating working medium storage, a heating working medium circulating pump, a relay and a power supply, wherein the heating working medium storage is used for storing liquid metal, the heating working medium circulating pump is connected with the heating working medium circulating pump, the heating working medium circulating pump is connected with the first micro pipeline, the anode and the cathode of the power supply are respectively connected with the two ends of the first micro pipeline through wires, the relay is arranged on the wires, and the relay is connected with the control subsystem.
As a further improvement of the embodiment of the invention, the refrigeration module comprises a first refrigeration working medium storage device storing a first refrigeration working medium, a first refrigeration working medium circulating pump, a condenser and a compressor, wherein the first refrigeration working medium storage device is connected with the first refrigeration working medium circulating pump, and the first refrigeration working medium circulating pump is connected with the first micro-pipeline; one end of the condenser is connected with one end of the first micro pipeline, the other end of the condenser is connected with the compressor, and the compressor is connected with the other end of the first micro pipeline.
As a further improvement of the embodiment of the present invention, the test subsystem further includes a triaxial mobile platform, and the triaxial mobile platform is connected to the performance testing assembly.
As a further improvement of the embodiment of the present invention, the first micro-pipeline is serpentine.
As a further improvement of the embodiment of the present invention, the first micro-pipe is a graphite fiber pipe.
As a further improvement of the embodiment of the invention, the inner wall surface of the outer heat preservation wall and the outer wall surface of the inner heat preservation wall are both provided with radiation heat dissipation coatings.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects: the turbine blade dynamic test system based on the circulating micro-pipeline provided by the embodiment of the invention can provide a temperature control environment of-50 ℃ to 2,000 ℃, simulate rapid and severe change of the working environment temperature of an aeroengine, and output and control power of 0-10,000RPM, so that dynamic test of various performance indexes of the turbine blade under extreme conditions is realized, and the problem that the conventional test system cannot provide dynamic detection of the turbine under various extreme conditions is solved.
The embodiment of the invention solves the contradiction problem that the heat capacity of the system needs to be increased when the heat insulation is carried out and the low heat capacity needs to be quickly responded by the system. In order to realize heat insulation of the system, the conventional measure is to increase a heat insulation system and improve the heat capacity of the system; in order to realize quick response of the system temperature, the conventional measure is to reduce the number of system components and reduce the heat capacity of the system. Obviously, the two are contradictory, but the invention realizes the heat preservation function by adopting the double-layer heat preservation wall, and simultaneously the first micro pipeline in the refrigerating and heating subsystem can be connected with the heating module for heating and the refrigerating module for cooling, thereby reducing the number of system components and reducing the heat capacity of the system. The embodiment of the invention reconciles contradictions of the heat capacity of the system, ensures the heat insulation and the heat preservation of the system, ensures the stability of simulating extreme conditions, accelerates the response speed of the system and ensures the rapid and severe change of the working environment temperature of the aero-engine.
Drawings
FIG. 1 is a top view of a turbine blade dynamic test system based on a circulation micro-pipeline according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a first micro-pipeline according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a first micro-pipeline connected to a heating module according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a first micro-circuit connected to a refrigeration module according to an embodiment of the present invention;
fig. 5 (a) is a schematic structural diagram of a second micro-pipe disposed in the inner heat insulation wall according to an embodiment of the present invention, fig. 5 (b) is a schematic structural diagram of a second micro-pipe disposed in the sliding bearing according to an embodiment of the present invention, and fig. 5 (c) is a schematic structural diagram of a second micro-pipe disposed in the transmission shaft according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of an auxiliary pipe subsystem according to an embodiment of the present invention;
FIG. 7 is a schematic diagram of a test subsystem according to an embodiment of the present invention;
FIG. 8 is a control logic block diagram of a turbine blade dynamic test system based on a circulation micro-pipeline according to an embodiment of the present invention.
In the figure: 1. the device comprises an outer heat-insulating wall, 2, an inner heat-insulating wall, 3, a support column, 4, turbine blades, 5, a transmission shaft, 6, a sliding bearing, 7, a first micro-pipeline, 8, a vacuum cavity, 9, an extraction opening, 10, a motor, 11, a test cavity, 12, a heating working medium circulating pump, 13, a heating working medium storage, 14, a control subsystem, 15, a relay, 16, a power supply, 17, a wire, 18, a first cooling working medium circulating pump, 19, a first cooling working medium storage, 20, a compressor, 21, a condenser, 22, a radiating fin, 24, a second micro-pipeline, 26, a first cooling working medium, 27, a second cooling working medium circulating pump, 28, a second cooling working medium storage, 29, an extraction pump, 32, a triaxial moving platform, 33, a data acquisition module, 34, a data transmission module, 35, a temperature sensor and 36 and a performance testing assembly.
Detailed Description
The following description of the embodiments of the present invention will be made more clearly and fully with reference to the accompanying drawings, in which it is to be understood that the embodiments described are merely some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The embodiment of the invention provides a turbine blade dynamic test system based on a circulating micro-pipeline, which is shown in figure 1 and comprises a closed heat insulation body, a refrigerating and heating subsystem, a test subsystem and a control subsystem. The heat preservation body includes outer heat preservation wall 1 and interior heat preservation wall 2, and outer heat preservation wall 1 and interior heat preservation wall 2 all enclose into confined inner chamber, and interior heat preservation wall 2 is arranged in the inner chamber of outer heat preservation wall 1. The inner heat preservation wall 2 is connected with the outer heat preservation cavity 1 through the support column 3. A vacuum cavity 8 is formed between the outer heat-insulating wall 1 and the inner heat-insulating wall 2, and the inner heat-insulating wall 2 encloses a test cavity 11. The outer heat preservation wall 1 is provided with an extraction opening 9 communicated with the vacuum cavity 8. Preferably, the outer heat-insulating wall 1 and the inner heat-insulating wall 2 are built by adopting alumina high-temperature-resistant heat-insulating bricks. The heat conduction, convection and radiation heat flow density is reduced, the heat exchange is reduced, and the heat insulation is realized.
The refrigerating and heating subsystem comprises a first micro pipeline 7, a refrigerating module and a heating module, wherein the first micro pipeline 7 is connected with the refrigerating module and the heating module, and the first micro pipeline 7 is arranged in the wall body of the inner heat preservation wall 2.
The testing subsystem comprises a temperature sensor 35 and a performance testing assembly 36, the temperature sensor 35 and the performance testing assembly 36 being arranged in the testing chamber 11. The performance test assembly 36 is used to test various performance of the turbine blade, including inductive reactance sensors, eddy current sensors, and the like.
The refrigeration module, the heating module, the temperature sensor 35, and the performance test assembly 36 are all coupled to the control subsystem 14. The temperature sensor 35 is used for monitoring the temperature in the test chamber 11 in real time, and transmitting the measurement data to the control subsystem 14 sequentially through the data acquisition module 33 and the data transmission module 34. The cooling and heating subsystem realizes a temperature environment of-50 ℃ to 2,000 ℃ in the test chamber 11 under the control of the control subsystem 14. The performance test assembly 36 detects the dynamic performance of the turbine blade and communicates the detected data to the control subsystem 14 via the data acquisition module 33 and the data transmission module 34 in sequence.
The embodiment solves the contradiction between the need of increasing the heat capacity of the system for heat insulation and the need of low heat capacity for quick response of the system. In order to realize heat insulation of the system, the conventional measure is to increase a heat insulation system and improve the heat capacity of the system; in order to realize quick response of the system temperature, the conventional measure is to reduce the number of system components and reduce the heat capacity of the system. Obviously, the two are mutually contradictory, but the invention realizes the heat preservation function by adopting the double-layer heat preservation wall, and the vacuum structure is adopted between the inner layer and the outer layer, thereby reducing heat conduction heat flow. Meanwhile, the first micro pipeline in the refrigerating and heating subsystem can be connected with the heating module for heating and the refrigerating module for cooling, so that the number of system components is reduced, and the heat capacity of the system is reduced. The embodiment of the invention reconciles contradictions of the heat capacity of the system, ensures the heat insulation and the heat preservation of the system, ensures the stability of simulating extreme conditions, accelerates the response speed of the system and ensures the rapid and severe change of the working environment temperature of the aero-engine.
The turbine blade dynamic test system based on the circulating micro-pipeline can provide a temperature control environment of-50 ℃ to 2,000 ℃, simulate rapid and severe change of the working environment temperature of an aeroengine, and output and control power of 0-10,000RPM, so that dynamic test of various performance indexes of the turbine blade under extreme conditions is realized, and the problem that the conventional test system cannot provide dynamic detection of the turbine under various extreme conditions is solved.
As a preferred example, the test system of the embodiment of the present invention further comprises a driving subsystem, which comprises a transmission shaft 5, a sliding bearing 6 and a motor 10, wherein the sliding bearing 6 is arranged on the inner heat insulation wall 2. The motor 10 is connected with the transmission shaft 5, and the transmission shaft 5 passes through the outer heat preservation wall 1 and the sliding bearing 6, and the turbine blade 4 is assembled on the transmission shaft 5, and the turbine blade 4 is arranged in the test cavity 11. The motor 10 is connected to a control subsystem. In the embodiment, the motor 10 is used for driving the transmission shaft 5, and the sliding bearing 6 is used for assisting, so that the transmission shaft 5 drives the turbine blade 4 to rotate, and the movement of the turbine blade 4 is simulated.
As a preferred example, the test system of the embodiment of the present invention further includes an auxiliary pipeline subsystem, the auxiliary pipeline subsystem includes a second micro pipeline 24 and an auxiliary module, the second micro pipeline 24 is connected with the auxiliary module, and the auxiliary module is connected with the control subsystem. As shown in fig. 5 (a), 5 (b) and 5 (c), the second micro-pipe 24 is provided in the inner heat-insulating wall 2, the transmission shaft 5 and the slide bearing 6, respectively.
After ensuring the stability of the system, in order to realize the quick response of the temperature control of the system, the test system of the embodiment of the invention adopts an auxiliary microtube subsystem, and a second micro pipeline 24 is arranged inside the inner heat insulation wall 2, the transmission shaft 5 and the sliding bearing 6, so that the heat capacity of the system can be reduced in a heating mode, and the whole temperature of the system can be reduced in a cooling mode.
Preferably, as shown in fig. 6, the auxiliary module includes a second refrigerant storage 28 storing a second refrigerant, a second refrigerant circulation pump 27 and an air pump 29, the second refrigerant storage 28 is connected to the second refrigerant circulation pump 27, the second refrigerant circulation pump 27 is connected to the second micro-pipe 24, and the air pump 29 is connected to the second micro-pipe 24. In the heating mode, the second micro-pipeline 24 is vacuumized by adopting the air pump 29, so that the heat flow density of heat conduction and convection heat exchange is reduced, the heat capacity of the system is reduced, and the temperature rising speed is increased. In the refrigeration mode, the second refrigerant is rapidly filled into the second micro-pipeline 24 through the second refrigerant storage 28 and the second refrigerant circulating pump 27, so that the overall temperature of the system is reduced.
As a preferred example, as shown in fig. 3, the heating module includes a heating working medium storage 13 storing liquid metal, a heating working medium circulation pump 12, a relay 15 and a power supply 16, the heating working medium storage 13 is connected with the heating working medium circulation pump 12, the heating working medium circulation pump 12 is connected with the first micro-pipeline 7, the anode and the cathode of the power supply 16 are respectively connected with two ends of the first micro-pipeline 7 through wires, the relay 15 is arranged on the wires 17, and the relay 15 is connected with the control subsystem.
In the embodiment of the invention, in a heating mode, the control subsystem 14 controls the heating working medium storage 13 and the heating working medium circulating pump 12 to introduce conductive liquid metal into the first micro-pipeline 7, apply voltage to the two ends of the first micro-pipeline 7, input heat through a joule effect, and improve the temperature of the system. Liquid metal gallium, indium, tin and alloys thereof are adopted as heating working media, the first micro-pipeline 7 is filled with conductive liquid metal, the Joule effect is enhanced, and the heating power is increased.
As a preferred example, as shown in fig. 4, the refrigeration module includes a first refrigerant storage 19 storing a first refrigerant, a first refrigerant circulation pump 18, a condenser 21, and a compressor 20, the first refrigerant storage 19 is connected to the first refrigerant circulation pump 18, and the first refrigerant circulation pump 18 is connected to the first micro-pipe 7. One end of the condenser 21 is connected to one end of the first micro-pipe 7, the other end of the condenser 21 is connected to the compressor 20, and the compressor 20 is connected to the other end of the first micro-pipe 7. The condenser 21 is also provided with cooling fins 22.
In the embodiment of the invention, in the refrigeration mode, the control subsystem 14 controls the first refrigeration working medium storage 19 and the first refrigeration working medium circulating pump 18 to introduce the first refrigeration working medium into the first micro-pipeline 7, and the first refrigeration working medium passes through the compressor 20 and the condenser 21 to extract heat through evaporation phase change heat exchange, so that the temperature of the system is reduced. Wherein, the first refrigerant adopts R123a and other refrigerant.
As a preferred example, as shown in FIG. 7, the testing subsystem further includes a three-axis motion stage 32, and both the temperature sensor 35 and the performance testing assembly 36 are coupled to the three-axis motion stage 32. In order to realize dynamic monitoring, the test system of the embodiment of the invention controls the triaxial moving platform 32 to adjust the position of the performance test assembly 36 through real-time temperature feedback of the temperature sensor 35, thereby reducing the influence of extreme temperature environment and thermal expansion and contraction of the system and turbine blades on performance test accuracy.
As a preferred example, as shown in fig. 2, the first micro-pipeline 7 is in a serpentine shape, and the serpentine-shaped micro-pipeline can lengthen the length of the micro-pipeline as much as possible in a limited space, and increase the specific surface area of the heat exchange surface, so as to enhance the refrigerating and heating effects.
As a preferred example, the first micro-pipe 7 is a graphite fiber pipe. The graphite fiber tube has high electric conductivity, high heat conduction and high temperature resistance.
As a preferable example, the inner wall surface of the outer heat preservation wall 1 and the outer wall surface of the inner heat preservation wall 2 are both provided with radiation heat dissipation coatings with low heat radiation and heat absorption, so that radiation heat flow is reduced, and heat insulation of the system is realized.
The flow of the method for dynamically testing the turbine blade by adopting the test system provided by the embodiment of the invention is as follows:
and (3) assembling a testing system: firstly, an inner heat preservation wall 2 and an outer heat preservation wall 1 are assembled, wherein a second micro pipeline 24 is arranged in heat preservation bricks of the inner heat preservation wall 2 and the outer heat preservation wall 1, a support column 3 is installed, and a low heat radiation and heat absorption coating is installed on the inner wall of a vacuum cavity 8 (the inner wall of the outer heat preservation wall 1 and the outer wall of the inner heat preservation wall 1). The turbine blade 4 is fitted on the drive shaft 5, then the sliding bearing 6 is assembled on the drive shaft 5, and then the part of the drive shaft 5 provided with the turbine blade 4 is extended into the test cavity 11, so that the sliding bearing 6 is arranged on the i-inner heat-preserving wall 2. The motor 10 is then fitted with the drive shaft 5 and the auxiliary module is connected with the insulating brick, the drive shaft 5 and the second micro-pipe 24 in the slide bearing 6. A plurality of hollow snakelike first micro-pipes 7 are sequentially overlapped and put into the insulating bricks of the inner insulating wall 2, and the first micro-pipes are partially connected in parallel and partially connected in series for convenient installation. The first micro-pipe 7 is connected to the heating module and the cooling module. The temperature sensor 35, the eddy current sensor and other sensors are inserted into the test cavity 11, the sensors are connected with the data acquisition module 33, and the data transmission module and the data acquisition module are connected and then fixed on the three-dimensional moving platform. As shown in fig. 8, the motor, the heating module, the cooling module, the auxiliary module, the data transmission module and the three-dimensional moving platform are connected with the control subsystem.
Before detection: and a test subsystem is adopted to test the system, and a comparison table of the sensor position and the inner cavity temperature is established.
The vacuum chamber is evacuated from the extraction opening 9 using a multistage extraction pump, and the triaxial moving platform is coarsely tuned, and the corresponding sensors are set at a reasonable position relative to the turbine blade 4.
And (3) deep cooling environment simulation:
the second refrigerant is injected into the second micro-pipeline 24 through the second refrigerant storage 28 and the second refrigerant circulating pump 27, the temperature is reduced in an acceleration way, meanwhile, the first refrigerant is injected into the first micro-pipeline 7 through the first refrigerant storage 19 and the first refrigerant circulating pump 18, and the refrigeration is started after the injection is finished. And starting the motor 10 to enable the turbine blade 4 to slowly rotate, and controlling the triaxial moving platform to finely adjust the sensor to a proper position by comparing the position of the sensor with a temperature comparison table of an inner cavity after the turbine blade 4 reaches a first preset temperature. The acceleration rotation is then started until the first predetermined rotational speed is reached. And after the data uploaded by the data transmission system is stable, starting to measure the data.
High-temperature environment simulation:
the second micro-pipeline 24 is vacuumized through the air pump 29, the heat capacity of the system is reduced, meanwhile, liquid metal is injected into the first micro-pipeline 7 through the heating working medium storage 13 and the heating working medium circulating pump 12, and the energization heating is started after the liquid metal is injected. And starting the motor 10 to enable the turbine blade 4 to slowly rotate, and controlling the triaxial moving platform to finely adjust the sensor to a proper position by comparing the position of the sensor with a temperature comparison table of the inner cavity after reaching a second preset temperature. The acceleration rotation is then started until a predetermined rotational speed is reached. And after the data uploaded by the data transmission system is stable, starting to measure the data.
According to the invention, a temperature control environment of-50 ℃ to 2,000 ℃ can be provided through the refrigerating and heating subsystem and the closed heat insulator, rapid and severe change of the working environment temperature of the aeroengine is simulated, 0-10,000RPM power output is provided through the driving subsystem, the test is performed through the testing subsystem through coordinated control of the control subsystem, so that dynamic test of various performance indexes of the turbine blade under extreme conditions is realized, and the problem that the conventional testing system cannot provide dynamic detection of the turbine under various extreme conditions is solved.
The refrigerating and heating subsystem provided by the embodiment of the invention adopts the first hollow snakelike micro-pipeline 7, can be connected with the heating module for heating and can be connected with the refrigerating module for refrigerating, and the first micro-pipeline 7 adopts double working mediums, so that the number of system components is reduced, and the heat capacity of the system is reduced. In the heating mode, the first micro-pipeline 7 is filled with conductive liquid metal, and the temperature of the system can be increased by applying voltage to the two ends of the first micro-pipeline 7 and inputting heat through the Joule effect. In the refrigeration mode, a first refrigeration working medium is introduced into the first micro-pipeline 7, heat is extracted through evaporation phase change heat exchange, and the temperature of the system is reduced.
The embodiment of the invention adopts a double-layer high-temperature-resistant insulating brick structure, ensures that heat conduction, convection and radiation heat flow density are reduced, and adopts a vacuum structure between the inner insulating wall and the outer insulating wall, thereby reducing heat conduction heat flow. In addition, the outer wall surface of the inner heat-insulating wall adopts a low heat radiation and heat absorption coating, so that radiation heat flow is reduced; the inner wall surface of the outer heat preservation wall also adopts a low heat radiation and heat absorption coating, so that radiation heat flow is reduced, heat exchange is reduced, and heat insulation is realized.
According to the embodiment of the invention, the real-time temperature in the test cavity is fed back through the temperature sensor, and the temperature-turbine blade position comparison table is established, so that the three-dimensional moving platform is controlled to adjust the position of the sensor, and the influence of the extreme temperature environment, the system, the expansion and contraction of the turbine blade and the measurement accuracy of the sensor is reduced.
In order to simulate the motion state of the turbine blade, the embodiment of the invention uses the motor to drive the transmission shaft and is assisted by the sliding bearing, so that the transmission shaft drives the turbine blade to rotate, thereby simulating the motion of the turbine blade.
The embodiment of the invention provides a scheme for solving the contradiction between the need of increasing the heat capacity of a system for heat insulation and the need of low heat capacity for quick response of the system. In order to realize heat insulation of the system, the conventional measure is to increase a heat insulation system and improve the heat capacity of the system; in order to realize quick response of the system temperature, the conventional measure is to reduce the number of system components and reduce the heat capacity of the system. Obviously, the two are contradictory, and the heat-insulating brick structure is adopted to assist the outer wall surface of the inner heat-insulating wall and the inner wall surface of the outer heat-insulating wall by adopting the double-layer high-temperature-resistant heat-insulating brick structure to use the low heat radiation and heat absorption coating, so that the radiation heat flow is reduced, and the heat-insulating function is further realized. Meanwhile, the first hollow snakelike micro-pipeline is adopted, so that the heating module can be connected with the heating module for heating, and the cooling module can be connected with the cooling module for cooling, thereby reducing the number of system components and reducing the heat capacity of the system. In addition, the insulating brick, the transmission shaft and the sliding bearing are internally provided with a second micro pipeline. The heat capacity of the system can be reduced in the heating mode, and the overall temperature of the system can be reduced in the cooling mode. The embodiment of the invention reconciles contradictions of the heat capacity of the system, ensures the heat insulation and the heat preservation of the system, ensures the stability of simulating extreme conditions, accelerates the response speed of the system and ensures the rapid and severe change of the working environment temperature of the aero-engine.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the specific embodiments described above, and that the above specific embodiments and descriptions are provided for further illustration of the principles of the present invention, and that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined in the appended claims. The scope of the invention is defined by the claims and their equivalents.
Claims (10)
1. The turbine blade dynamic test system based on the circulating micro-pipeline is characterized by comprising a closed heat preservation body, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat preservation body comprises an outer heat preservation wall (1) and an inner heat preservation wall (2), a vacuum cavity is formed between the outer heat preservation wall (1) and the inner heat preservation wall (2), and the inner heat preservation wall (2) encloses a test cavity; the refrigerating and heating subsystem comprises a first micro pipeline (7), a refrigerating module and a heating module, wherein the first micro pipeline (7) is connected with the refrigerating module and the heating module, and the first micro pipeline (7) is arranged in an inner heat-insulating wall; the test subsystem comprises a temperature sensor (35) and a performance test component (36), wherein the temperature sensor (35) and the performance test component (36) are arranged in a test cavity; the refrigerating module, the heating module, the temperature sensor (35) and the performance testing assembly (36) are all connected with the control subsystem.
2. The turbine blade dynamic test system of a circulating micro-pipeline according to claim 1, wherein the refrigeration module comprises a first refrigeration working medium storage (19) storing a first refrigeration working medium, a first refrigeration working medium circulating pump (18), a condenser (21) and a compressor (20), the first refrigeration working medium storage (19) is connected with the first refrigeration working medium circulating pump (18), and the first refrigeration working medium circulating pump (18) is connected with the first micro-pipeline (7); one end of a condenser (21) is connected with one end of the first micro pipeline (7), the other end of the condenser (21) is connected with a compressor (20), and the compressor (20) is connected with the other end of the first micro pipeline (7).
3. The turbine blade dynamic test system of the circulation micro-pipeline according to claim 1, further comprising a driving subsystem, wherein the driving subsystem comprises a transmission shaft (5), a sliding bearing (6) and a motor (10), and the sliding bearing (6) is arranged on the inner heat preservation wall (2); the motor (10) is connected with the transmission shaft (5), the transmission shaft (5) penetrates through the outer heat insulation wall and the sliding bearing (6), the turbine blade (4) is assembled on the transmission shaft (5), and the turbine blade (4) is positioned in the test cavity; the motor (10) is connected with the control subsystem.
4. The turbine blade dynamic test system of a circulation micro-line of claim 3, further comprising an auxiliary line subsystem comprising a second micro-line (24) and an auxiliary module, the second micro-line (24) being connected to the auxiliary module, the auxiliary module being connected to the control subsystem; the second micro pipeline (24) is respectively arranged in the inner heat insulation wall (2), the transmission shaft (5) and the sliding bearing (6).
5. The turbine blade dynamic test system of a circulating micro-pipe according to claim 4, wherein the auxiliary module comprises a second refrigerant storage (28) storing a second refrigerant, a second refrigerant circulating pump (27) and an air pump (29), the second refrigerant storage (28) is connected with the second refrigerant circulating pump (27), the second refrigerant circulating pump (27) is connected with the second micro-pipe (24), and the air pump (29) is connected with the second micro-pipe (24).
6. The turbine blade dynamic test system of the circulating micro-pipeline according to claim 1, wherein the heating module comprises a heating working medium storage (13) for storing liquid metal, a heating working medium circulating pump (12), a relay (15) and a power supply (16), the heating working medium storage (13) is connected with the heating working medium circulating pump (12), the heating working medium circulating pump (12) is connected with the first micro-pipeline (7), the anode and the cathode of the power supply (16) are respectively connected with the two ends of the first micro-pipeline (7) through wires, the relay (15) is arranged on the wires, and the relay (15) is connected with the control subsystem.
7. The turbine blade dynamic test system of a circulating micro-pipeline of claim 1, wherein the test subsystem further comprises a three-axis moving platform (32), the three-axis moving platform (32) being coupled to a performance test assembly (36).
8. The turbine blade dynamic test system of a circulating micro-pipeline according to claim 1, wherein the first micro-pipeline (7) is serpentine.
9. The turbine blade dynamic test system of a circulating micro-pipe according to claim 1, wherein the first micro-pipe (7) is a graphite fiber pipe.
10. The dynamic test system for turbine blades of a circulating micro-pipeline according to claim 1, wherein the inner wall surface of the outer heat-insulating wall (1) and the outer wall surface of the inner heat-insulating wall (2) are both provided with radiation heat-dissipating coatings.
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