CN113944518A - 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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- CN113944518A CN113944518A CN202111052954.3A CN202111052954A CN113944518A CN 113944518 A CN113944518 A CN 113944518A CN 202111052954 A CN202111052954 A CN 202111052954A CN 113944518 A CN113944518 A CN 113944518A
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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
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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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/166—Sliding contact bearing
Abstract
The invention provides a turbine blade dynamic test system based on a circulating micro pipeline, which comprises a closed heat insulator, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat insulator comprises an outer heat insulation wall and an inner heat insulation wall, a vacuum cavity is formed between the outer heat insulation wall and the inner heat insulation wall, and the inner heat insulation wall encloses a test cavity; the refrigeration and heating subsystem comprises a first micro pipeline, a refrigeration module and a heating module, the first micro pipeline is connected with the refrigeration module and the heating module, and the first micro pipeline is arranged in the inner heat-insulation 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 refrigeration 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 violent change of the working environment temperature of the aircraft engine, 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 testing system based on a circulating micro-pipeline.
Background
Aircraft engines are the highest end equipment in the field of equipment manufacture, as the "heart" of an aircraft, and the reliability and safety of aircraft engines is of paramount importance. The turbine blade is a core component of power output of the aero-engine, accurate, reliable and continuous online monitoring of blade top clearance of the aero-engine is a key for guaranteeing safe, efficient and long-life work of the engine, and is one of important prerequisites for improving power output of the engine and enhancing war plane operation capability and battlefield viability. The flying height of the advanced warplanes nowadays reaches 20,000m to 30,000m, and the atmospheric temperature is as low as-50 ℃. The turbine blades are therefore often subjected to high loads and thermal shocks, the operating environment temperature of which can increase from-50 ℃ at the low-pressure compressor to 2,000 ℃ at the combustion chamber, and the operating environment is extremely harsh.
How better simulation turbine engine's operational environment and detect relevant data just turbine detection technology key, current high temperature detecting system is most based on the muffle structure, can detect each item parameter change of turbine under the high temperature condition, but current detection technology simulation environment is single, and it is loaded down with trivial details to switch test environment, can not simulate cryrogenic to high temperature environment and measure turbine blade nature dynamics, more can not simulate the quick violent change of aeroengine operational environment temperature. Causing difficulties in measuring data and waste of resources and time.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the turbine blade dynamic testing system based on the circulating micro-pipeline can provide a temperature control environment of-50 ℃ to 2,000 ℃, can simulate rapid and violent change of the working environment temperature of an aircraft engine, and can realize dynamic testing 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 insulator, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat insulator comprises an outer heat insulation wall and an inner heat insulation wall, a vacuum cavity is formed between the outer heat insulation wall and the inner heat insulation wall, and the inner heat insulation wall encloses a test cavity; the refrigeration and heating subsystem comprises a first micro pipeline, a refrigeration module and a heating module, the first micro pipeline is connected with the refrigeration module and the heating module, and the first micro pipeline is arranged in the inner heat-insulation 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 refrigeration 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 heat insulation device further 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 insulation 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 pipeline subsystem, wherein the auxiliary pipeline subsystem comprises a second micro pipeline and an auxiliary module, the second micro pipeline 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 preservation 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 storing a second refrigerant, a second refrigerant circulating pump, and an air pump, the second refrigerant storage is connected to the second refrigerant circulating pump, the second refrigerant circulating pump is connected to the second micro-pipe, and the air pump is connected to the second micro-pipe.
As a further improvement of the embodiment of the present invention, the heating module includes a heating working medium storage storing liquid metal, a heating working medium circulating pump, a relay and a power supply, the heating working medium storage is connected to the heating working medium circulating pump, the heating working medium circulating pump is connected to the first micro-pipeline, the positive and negative electrodes of the power supply are respectively connected to two ends of the first micro-pipeline through wires, the relay is disposed on the wires, and the relay is connected to the control subsystem.
As a further improvement of the embodiment of the invention, the refrigeration module comprises a first refrigeration working medium storage device for 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 three-axis mobile platform, and the three-axis mobile platform is connected to the performance test component.
As a further improvement of the embodiments of the present invention, the first micro pipe has a serpentine shape.
As a further improvement of the embodiment of the present invention, the first micro pipeline is a graphite fiber pipe.
As a further improvement of the embodiment of the invention, the inner wall surface of the outer heat-insulating wall and the outer wall surface of the inner heat-insulating 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 can provide a temperature control environment of-50 ℃ to 2,000 ℃, simulate rapid and violent change of the working environment temperature of an aircraft engine, and output and control power at 0-10,000RPM, further realize dynamic test of various performance indexes of the turbine blade under extreme conditions, and solve the problem that the traditional test system cannot provide dynamic detection of the turbine under various extreme conditions.
The embodiment of the invention 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 the heat insulation and heat preservation of the system, the conventional measures are to increase a heat preservation system and improve the heat capacity of the system; in order to achieve quick response of the system temperature, the conventional measures are to reduce the number of system components and reduce the heat capacity of the system. Obviously, the two are mutually contradictory, and the invention realizes the heat preservation function by adopting the double-layer heat preservation wall, and meanwhile, the first micro-pipeline in the refrigeration and heating subsystem can be connected with the heating module to carry out temperature rise and can also be connected with the refrigeration module to carry out temperature reduction, thereby reducing the number of system components and reducing the heat capacity of the system. The embodiment of the invention reconciles the contradiction of the heat capacity of the system, thereby not only ensuring the heat insulation and the heat preservation of the system and the stability of simulating extreme conditions, but also accelerating the response speed of the system and ensuring that the rapid and violent change of the working environment temperature of the aero-engine can be simulated.
Drawings
FIG. 1 is a top view of a turbine blade dynamic testing system based on a circulating micro-pipe in accordance with an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a first micro-pipe in an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a first micro-pipe connected to a heating module according to an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a first micro-pipe connected to a refrigeration module according to an embodiment of the present invention;
fig. 5(a) is a schematic structural view illustrating a second micro pipe disposed in an inner thermal insulation wall according to an embodiment of the present invention, fig. 5(b) is a schematic structural view illustrating a second micro pipe disposed in a sliding bearing according to an embodiment of the present invention, and fig. 5(c) is a schematic structural view illustrating a second micro pipe disposed in a transmission shaft according to an embodiment of the present invention;
FIG. 6 is a schematic structural diagram of an auxiliary piping subsystem according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a test subsystem in an embodiment of the present invention;
FIG. 8 is a control logic block diagram of a turbine blade dynamic testing system based on a circulation micro-pipe according to an embodiment of the present invention.
In the figure: 1. an outer heat preservation wall 2, an inner heat preservation wall 3, a support column 4, a turbine blade 5, a transmission shaft 6, a sliding bearing 7, a first micro pipeline 8, a vacuum cavity 9, an air 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, the device comprises a lead, 18, a first refrigeration working medium circulating pump, 19, a first refrigeration working medium storage, 20, a compressor, 21, a condenser, 22, a radiating fin, 23, a radiation radiating coating, 24, a second micro pipeline, 26, a first refrigeration working medium, 27, a second refrigeration working medium circulating pump, 28, a second refrigeration working medium storage, 29, an air extracting pump, 32, a three-axis mobile platform, 33, a data acquisition module, 34, a data transmission module, 35, a temperature sensor, 36 and a performance testing assembly.
Detailed Description
The technical solutions in the embodiments of the present invention will be described more clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a turbine blade dynamic testing system based on a circulating micro pipeline, which comprises a closed heat insulator, a refrigerating and heating subsystem, a testing subsystem and a control subsystem as shown in figure 1. 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 a support pillar 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 testing 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 both built by 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, 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-insulating wall 2.
The testing subsystem includes a temperature sensor 35 and a performance testing component 36, the temperature sensor 35 and the performance testing component 36 being disposed in the testing chamber 11. The performance testing assembly 36 is used to test various properties 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 testing component 36 are all connected with 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 through the data acquisition module 33 and the data transmission module 34 in sequence. 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 testing assembly 36 detects the dynamic performance of the turbine blade and transmits 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 problem that the heat capacity of the system needs to be increased when the heat insulation and heat preservation are carried out, and the heat capacity of the system needs to be low when the system responds quickly. In order to realize the heat insulation and heat preservation of the system, the conventional measures are to increase a heat preservation system and improve the heat capacity of the system; in order to achieve quick response of the system temperature, the conventional measures are 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 reduces the heat conduction heat flow by adopting the vacuum structure between the inner layer and the outer layer. Meanwhile, the first micro-pipeline in the refrigerating and heating subsystem can be connected with the heating module to heat and can also be connected with the refrigerating module to cool, so that the number of system components is reduced, and the heat capacity of the system is reduced. The embodiment of the invention reconciles the contradiction of the heat capacity of the system, thereby not only ensuring the heat insulation and the heat preservation of the system and the stability of simulating extreme conditions, but also accelerating the response speed of the system and ensuring that the rapid and violent change of the working environment temperature of the aero-engine can be simulated.
The turbine blade dynamic testing system based on the circulating micro-pipeline can provide a temperature control environment of-50 ℃ to 2,000 ℃, simulate rapid and violent change of the temperature of the working environment of an aircraft engine, and output and control power at 0-10,000RPM, further realize dynamic testing of various performance indexes of the turbine blade under extreme conditions, and solve the problem that the traditional testing system cannot provide dynamic turbine detection under various extreme conditions.
As a preferable example, the testing system of the embodiment of the present invention further includes a driving subsystem, the driving subsystem includes a transmission shaft 5, a sliding bearing 6 and a motor 10, and the sliding bearing 6 is disposed on the inner thermal insulation wall 2. The motor 10 is connected with the transmission shaft 5, the transmission shaft 5 penetrates through the outer heat preservation wall 1 and the sliding bearing 6, the turbine blade 4 is assembled on the transmission shaft 5, and the turbine blade 4 is located in the testing 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, thereby simulating the motion of the turbine blade 4.
As a preferable example, the test system of the embodiment of the present invention further includes an auxiliary pipeline subsystem, where the auxiliary pipeline subsystem includes a second micro pipeline 24 and an auxiliary module, the second micro pipeline 24 is connected to the auxiliary module, and the auxiliary module is connected to the control subsystem. As shown in fig. 5(a), 5(b) and 5(c), the second micro-pipe 24 is provided in the inner thermal insulation wall 2, the transmission shaft 5 and the sliding bearing 6, respectively.
After the stability of the system is ensured, 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 micro-pipeline subsystem, and the second micro-pipeline 24 is arranged in the inner heat-insulating 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 integral 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 circulating pump 27 and a suction pump 29, the second refrigerant storage 28 is connected to the second refrigerant circulating pump 27, the second refrigerant circulating pump 27 is connected to the second micro-pipeline 30, and the suction pump 29 is connected to the second micro-pipeline 24. In the heating mode, the air pump 29 is adopted to vacuumize the second micro-pipeline 24, 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 refrigeration working medium is rapidly filled into the second micro-pipeline 24 through the second refrigeration working medium storage 28 and the second refrigeration working medium 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 medium storage 13 storing liquid metal, a heating medium circulation pump 12, a relay 15 and a power supply 16, the heating medium storage 13 is connected to the heating medium circulation pump 12, the heating medium circulation pump 12 is connected to the first micro-pipeline 7, the positive and negative electrodes of the power supply 16 are connected to two ends of the first micro-pipeline 7 through wires, the relay 15 is disposed on the wire 17, and the relay 15 is connected to the control subsystem.
In the embodiment of the invention, in the heating mode, the control subsystem 14 controls the heating working medium storage 13 and the heating working medium circulating pump 12 to introduce the conductive liquid metal into the first micro-pipeline 7, applies voltage to two ends of the first micro-pipeline 7, inputs heat through the joule effect, and improves the temperature of the system. Liquid metal gallium, indium, tin and alloy thereof are used as heating working media, and the first micro pipeline 7 is filled with conductive liquid metal, so that the Joule effect is strengthened, and the heating power is increased.
As a preferred example, as shown in fig. 4, the refrigeration module includes a first refrigeration working medium storage 19 storing a first refrigeration working medium, a first refrigeration working medium circulation pump 18, a condenser 21, and a compressor 22, the first refrigeration working medium storage 19 is connected to the first refrigeration working medium circulation pump 18, and the first refrigeration working medium circulation pump 18 is connected to the first micro-pipeline 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 fins 22.
In the embodiment of the invention, in a 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 heat is extracted through evaporation phase-change heat exchange by the compressor 20 and the condenser 21, so that the temperature of the system is reduced. Wherein, the first refrigeration working medium adopts refrigeration working media such as R123 a.
As a preferred example, as shown in fig. 7, the testing subsystem further includes a three-axis moving platform 32, and the temperature sensor 35 and the performance testing component 36 are connected to the three-axis moving platform 32. In order to realize dynamic monitoring, the testing system in the embodiment of the invention controls the three-axis mobile platform 32 to adjust the position of the performance testing component 36 through real-time temperature feedback of the temperature sensor 35, so that the influence of extreme temperature environment and thermal expansion and cold contraction of the system and the turbine blade on the performance testing accuracy is reduced.
As a preferred example, as shown in fig. 2, the first micro-pipe 7 is serpentine, and the length of the micro-pipe can be lengthened as much as possible in a limited space by using the serpentine micro-pipe, so as to increase the specific surface area of the heat exchange surface, thereby enhancing the cooling and heating effects.
As a preferred example, a graphite fiber tube is used as the first micro pipe 7. The graphite fiber pipe has high electric conductivity, high heat conductivity and high temperature resistance.
As a preferable example, 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 a radiation heat-dissipation coating 23 with low heat radiation and heat absorption, thereby reducing the radiation heat flow and realizing the heat insulation of the system.
The process of the method for dynamically testing the turbine blade by adopting the testing system of the embodiment of the invention is as follows:
assembling a test system: firstly, an inner heat insulation wall 2 and an outer heat insulation wall 1 are assembled, wherein a second micro pipeline 24 is arranged in the heat insulation bricks of the inner heat insulation wall 2 and the outer heat insulation 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 insulation wall 1 and the outer wall of the inner heat insulation wall 1). The turbine blade 4 is matched on the transmission shaft 5, then the sliding bearing 6 is assembled on the transmission shaft 5, and the part of the transmission shaft 5, which is provided with the turbine blade 4, extends into the testing cavity 11, so that the sliding bearing 6 is arranged on the i inner heat preservation wall 2. Then the motor 10 is matched with the transmission shaft 5, and the auxiliary module is connected with the second micro-pipeline 24 in the insulating brick, the transmission shaft 5 and the sliding bearing 6. A large number of hollow snake-shaped first micro pipelines 7 are orderly stacked and placed in the insulating bricks of the inner insulating wall 2, and for convenient installation, the first micro pipelines are partially connected in parallel and partially connected in series. And connecting the first micro pipeline 7 with a heating module and a refrigerating module. And then inserting the temperature sensor 35, the eddy current sensor and other sensors into the test cavity 11, connecting the sensors with the data acquisition module 33, and fixing the data transmission module and the data acquisition module on the three-dimensional mobile platform after connecting. As shown in fig. 8, the motor, the heating module, the cooling module, the auxiliary module, the data transmission module, and the three-dimensional mobile platform are connected to the control subsystem.
Before detection: and (4) establishing a comparison table of the sensor position and the inner cavity temperature by adopting a test subsystem test system.
And (3) pumping the vacuum cavity into vacuum from the air pumping port 9 by using a multi-stage air pump, roughly adjusting the three-axis moving platform, and setting the corresponding sensor at a reasonable position relative to the turbine blade 4.
Deep cooling environment simulation:
the second refrigeration working medium is injected into the second micro-pipeline 24 through the second refrigeration working medium storage 28 and the second refrigeration working medium circulating pump 27, the temperature is reduced at an accelerated speed, meanwhile, the first refrigeration working medium is injected into the first micro-pipeline 7 through the first refrigeration working medium storage 19 and the first refrigeration working medium circulating pump 18, and refrigeration is started after the injection is finished. And starting the motor 10 to slowly rotate the turbine blade 4, and after the first preset temperature is reached, comparing the position of the sensor with the inner cavity temperature comparison table, and controlling the three-axis mobile platform to finely adjust the sensor to a proper position. Thereafter, the spin-up is started until a first predetermined rotational speed is reached. And measuring the data after the data uploaded by the data transmission system is stable.
High-temperature environment simulation:
the second micro-pipeline 24 is vacuumized by the air pump 29 to reduce the heat capacity of the system, and simultaneously 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 liquid metal is electrified and heated after being injected. And starting the motor 10 to slowly rotate the turbine blade 4, and after the second preset temperature is reached, comparing the position of the sensor with the inner cavity temperature comparison table, and controlling the three-axis mobile platform to finely adjust the sensor to a proper position. Thereafter, the acceleration rotation is started until a predetermined rotation speed is reached. And measuring the data after the data uploaded by the data transmission system is stable.
The system can provide a temperature control environment of-50 ℃ to 2,000 ℃ through the refrigeration and heating subsystem and the closed heat insulator, simulate the rapid and violent change of the temperature of the working environment of an aircraft engine, provide 0-10,000RPM power output through the driving subsystem, test through the testing subsystem through the coordination control of the control subsystem, further realize the dynamic test of various performance indexes of the turbine blade under extreme conditions, and solve the problem that the traditional test system cannot provide the dynamic detection of the turbine under various extreme conditions.
The refrigeration and heating subsystem in the embodiment of the invention adopts the hollow snake-shaped first micro-pipeline 7, can be connected with the heating module for heating and can also be connected with the refrigeration module for refrigeration, and the first micro-pipeline 7 adopts double working media, so that the number of system components is reduced, and the heat capacity of the system is reduced. In the heating mode, conductive liquid metal is introduced into the first micro-pipeline 7, voltage can be applied to two ends of the first micro-pipeline 7, heat is input through a joule effect, and the temperature of the system is increased. Under the hot cold mode, let in first refrigerant in the first micro pipeline 7, extract the heat through evaporation phase transition heat transfer, reduce system temperature.
The embodiment of the invention adopts a double-layer high-temperature-resistant insulating brick structure, ensures that the density of heat conduction, convection and radiation heat flow is reduced, and reduces the heat conduction heat flow by adopting a vacuum structure between the inner insulating wall and the outer insulating wall. In addition, the outer wall surface of the inner heat-insulating wall adopts a low-heat radiation and heat absorption coating, so that the radiation heat flow is reduced; the inner wall surface of the outer heat insulation wall also adopts a low-heat radiation and heat absorption coating to reduce radiation heat flow so as to reduce heat exchange and realize heat insulation.
According to the embodiment of the invention, the real-time temperature in the test cavity is fed back by the temperature sensor, and the position of the sensor is adjusted by controlling the three-dimensional moving platform by establishing the temperature-turbine blade position comparison table, so that the influence of the extreme temperature environment, the expansion and contraction of the system and 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 the sliding bearing is used for assisting, 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 requirement of increasing the heat capacity of a system for heat insulation and the requirement of low heat capacity for quick response of the system. In order to realize the heat insulation and heat preservation of the system, the conventional measures are to increase a heat preservation system and improve the heat capacity of the system; in order to achieve quick response of the system temperature, the conventional measures are to reduce the number of system components and reduce the heat capacity of the system. Obviously, the two are mutually contradictory, and the invention reduces radiation heat flow by adopting a double-layer high-temperature-resistant insulating brick structure and using low-heat radiation and heat absorption coatings on the outer wall surface of the inner insulating wall and the inner wall surface of the outer insulating wall, thereby realizing the insulating function. Meanwhile, the hollow snake-shaped first micro pipeline is adopted, so that the heating module can be connected for heating, and the cooling module can be connected for cooling, the number of system components is reduced, and the heat capacity of the system is reduced. In addition, a second micro pipeline is used in the insulating brick, the transmission shaft and the sliding bearing. The heat capacity of the system can be reduced in the heating mode, and the overall temperature of the system can be reduced quickly in the cooling mode. The embodiment of the invention reconciles the contradiction of the heat capacity of the system, thereby not only ensuring the heat insulation and the heat preservation of the system and the stability of simulating extreme conditions, but also accelerating the response speed of the system and ensuring that the rapid and violent change of the working environment temperature of the aero-engine can be simulated.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are intended to further illustrate the principles of the invention, and that various changes and modifications may be made without departing from the spirit and scope of the invention, which is also intended to be covered by the appended claims. The scope of the invention is defined by the claims and their equivalents.
Claims (10)
1. A turbine blade dynamic test system based on a circulating micro pipeline is characterized by comprising a closed heat insulation body, a refrigerating and heating subsystem, a test subsystem and a control subsystem, wherein the heat insulation body comprises an outer heat insulation wall (1) and an inner heat insulation wall (2), a vacuum cavity is formed between the outer heat insulation wall (1) and the inner heat insulation wall (2), and the inner heat insulation wall (2) is enclosed into a test cavity; the refrigeration and heating subsystem comprises a first micro pipeline (7), a refrigeration module and a heating module, wherein the first micro pipeline (7) is connected with the refrigeration module and the heating module, and the first micro pipeline (7) is arranged in the inner heat-insulation wall; the testing subsystem comprises a temperature sensor (35) and a performance testing component (36), wherein the temperature sensor (35) and the performance testing component (36) are arranged in the testing cavity; and the refrigeration module, the heating module, the temperature sensor (35) and the performance testing component (36) are all connected with the control subsystem.
2. The system for dynamically testing the turbine blades of the circulating 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 located in the test cavity; the motor (10) is connected with the control subsystem.
3. The system of claim 2, further comprising an auxiliary piping subsystem, the auxiliary piping subsystem comprising a second micro-pipe (24) and an auxiliary module, the second micro-pipe (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 preservation wall (2), the transmission shaft (5) and the sliding bearing (6).
4. The turbine blade dynamic test system of a circulating micro-pipeline according to claim 3, wherein the auxiliary module comprises a second refrigerant storage (28) storing a second refrigerant, a second refrigerant circulating pump (27) and a suction 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-pipeline (24), and the suction pump (29) is connected with the second micro-pipeline (24).
5. The turbine blade dynamic test system of the circulation micro-pipeline according to claim 1, wherein the heating module comprises a heating medium storage (13) storing liquid metal, a heating medium circulating pump (12), a relay (15) and a power supply (16), the heating medium storage (13) is connected with the heating medium circulating pump (12), the heating medium circulating pump (12) is connected with the first micro-pipeline (7), the positive and negative poles of the power supply (16) are respectively connected with two ends of the first micro-pipeline (7) through leads, the relay (15) is arranged on the leads, and the relay (15) is connected with the control subsystem.
6. The turbine blade dynamic test system of the 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 (22), 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 the condenser (21) is connected with one end of the first micro pipeline (7), the other end of the condenser (21) is connected with the compressor (20), and the compressor (20) is connected with the other end of the first micro pipeline (7).
7. The system of claim 1, wherein the testing subsystem further comprises a tri-axial motion stage (32), the tri-axial motion stage (32) coupled to a performance testing assembly (36).
8. The system according to claim 1, characterized in that said first microcircuit (7) is serpentine.
9. The system for the dynamic testing of turbine blades of a circulating micro-circuit according to claim 1, characterized in that said first micro-circuit (7) uses a graphite fiber tube.
10. The system for dynamically testing the turbine blades of the 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 a radiation heat-dissipation coating (23).
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| US20170089771A1 (en) * | 2015-09-24 | 2017-03-30 | King Fahd University Of Petroleum And Minerals | System for determining thermal transmittance and thermal resistance of building walls assemblies under dynamic weather conditions |
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|---|---|---|---|---|
| US6855916B1 (en) * | 2003-12-10 | 2005-02-15 | Axcelis Technologies, Inc. | Wafer temperature trajectory control method for high temperature ramp rate applications using dynamic predictive thermal modeling |
| US20060256835A1 (en) * | 2005-05-12 | 2006-11-16 | Guardian Building Products, Inc. | Dynamic heat flow meter for measuring thermal properties of insulation or the like, and corresponding method |
| US20140103947A1 (en) * | 2012-04-05 | 2014-04-17 | Huy N. PHAN | Thermal reliability testing systems with thermal cycling and multidimensional heat transfer |
| US20170089771A1 (en) * | 2015-09-24 | 2017-03-30 | King Fahd University Of Petroleum And Minerals | System for determining thermal transmittance and thermal resistance of building walls assemblies under dynamic weather conditions |
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