Semi-physical test device for variable geometry low-pressure turbine adjusting mechanism

Abstract

The invention provides a variable geometry low-pressure turbine adjusting mechanism semi-physical test device, which relates to the technical field of aero-engine test equipment and comprises an engine model, a variable geometry low-pressure turbine adjusting mechanism prototype, a heating system, a measurement and control system, a real-time simulation machine system and an upper computer. The heating system is used for respectively heating the inner duct, the outer duct and the guide vane blades; the measurement and control system monitors the temperature of the inner duct, the temperature of the outer duct, the temperature of the guide vane blade and the angle change of the guide vane blade; the real-time simulation machine system is used for realizing real-time operation of the engine model; the upper computer is in communication connection with the measurement and control system and the real-time simulation machine system; according to the method, semi-physical simulation is adopted for research, high-precision simulation of the dynamic characteristics of the engine can be guaranteed while the test cost and test potential safety hazards are reduced, some processes which are difficult to achieve in the simulation process are simulated, and some data which are difficult to obtain in the digital simulation process are obtained.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengine test equipment, and particularly to a semi-physical test device for a variable geometry low-pressure turbine regulating mechanism. Background Art

[0002] For multi-purpose aircraft, the most attractive one is the variable cycle engine adopting variable geometry turbine technology. The variable geometry turbine is one of the core components for the engine to achieve variable cycle function. By adjusting the installation angle of the guide vane, the performance of each state point can reach the best at any given flight profile. The variable geometry turbine changes the magnitude of the output work by adjusting its own flow capacity, thereby changing the rotational speed difference between the high-pressure and low-pressure turbines, matching the working states of the fan and the compressor, improving the economy of the engine at some thrust states, and improving the transient response characteristics such as acceleration and deceleration. The design of the variable geometry turbine is more complex than that of other variable geometry components. It is not only in the high-pressure and high-temperature gas similar to the traditional turbine, but also different from the traditional turbine which only needs to have a high efficiency at the design point. The variable geometry turbine requires to maintain a relatively high efficiency at the design point and at different rotation angles of the guide vane. Therefore, the exploration work on the aerodynamic design of the variable geometry turbine is of great significance.

[0003] Aero turbines mainly have two forms: variable geometry high-pressure turbines and variable geometry low-pressure turbines. Considering the high-pressure turbine stage of aeroengines, the gas temperature is usually above 1800K, which makes the structures such as the rotating shaft installed on the variable geometry high-pressure turbine need to be cooled. Considering factors such as the stability of the variable geometry high-pressure turbine, the current domestic research focus has shifted to the aero geometric low-pressure turbine. Compared with the variable geometry high-pressure turbine, the gas temperature of the aero variable geometry low-pressure turbine is usually around 1500K, which greatly reduces the design difficulty of the cooling structure of the variable geometry low-pressure turbine.

[0004] For a complex transmission system such as the variable geometry low-pressure turbine actuator, if physical objects are used for testing, firstly, the test cost is expensive, and secondly, it is very easy to cause dangerous situations such as engine overheating and surge due to the imperfect control system during the test process.

[0005] Therefore, it is necessary to study a new test idea to solve the above technical problems. Summary of the Invention

[0006] The purpose of the present invention is to provide a semi-physical test device for a variable geometry low-pressure turbine regulating mechanism to solve the problems existing in the above prior art. By adopting semi-physical simulation for research, while reducing the test cost and test safety hazards, it can also ensure the high-precision simulation of the dynamic characteristics of the engine, simulate some processes that are difficult to achieve in the simulation process and obtain some data that are difficult to obtain in the digital simulation process, laying a foundation for the design of the engine control system and the research of dynamic characteristics.

[0007] To achieve the above object, the present invention provides the following solutions:

[0008] A semi-physical test device for a variable geometry low-pressure turbine regulating mechanism, comprising an engine model, a prototype of the variable geometry low-pressure turbine regulating mechanism, a heating system, a measurement and control system, a real-time simulator system, and a host computer;

[0009] The prototype of the variable geometry low-pressure turbine regulating mechanism includes a housing, an inner casing, an outer casing, guide vane blades, and a driving assembly. The housing, the outer casing, and the inner casing are coaxially sleeved from the outside to the inside. An outer annular duct is formed between the housing and the outer casing. The guide vane blades are located in the inner annular duct between the inner casing and the outer casing. The blade shafts of the guide vane blades are rotatably arranged on the outer casing. One end of the blade shaft is fixedly connected to one end of a rocker arm, and the other end of the rocker arm is hinged to a linkage ring. The driving assembly is used to drive the linkage ring to rotate;

[0010] The heating system is used to heat the inner annular duct, the outer annular duct, and the guide vane blades respectively;

[0011] The measurement and control system monitors the temperature of the inner annular duct, the temperature of the outer annular duct, the temperature of the guide vane blades, and the angular change of the guide vane blades;

[0012] The real-time simulator system is used to realize the real-time operation of the engine model;

[0013] The host computer is communicatively connected to the measurement and control system and the real-time simulator system.

[0014] As an embodiment, the driving assembly includes a linear power unit and a transmission mechanism. The transmission mechanism includes a rotating shaft and a slider. The output end of the linear power unit is hinged to one end of an outer connecting rod, and the other end of the outer connecting rod is hinged to one end of the rotating shaft. The slider is fixedly connected to the linkage ring. The slider is hinged to one end of an inner connecting rod, and the other end of the inner connecting rod is hinged to the other end of the rotating shaft. The rotating shaft is rotatably installed on the housing. The outer connecting rod and the inner connecting rod are respectively located inside and outside the housing.

[0015] As an embodiment, the linear power unit is a linear servo motor.

[0016] As an embodiment, the prototype of the variable geometry low-pressure turbine regulating mechanism further includes a fixing plate. The fixing plate is fixedly connected to the inner casing, the outer casing, and the housing. The fixing plate fixes the linear power unit through a bracket.

[0017] As an embodiment, a magnetorheological damper is further fixed on the fixed disk. The magnetorheological damper is in transmission connection with the linkage ring through the transmission mechanism, and the end of the magnetorheological damper is hinged to the end of the outer connecting rod; the magnetorheological damper is used to apply a load to the linkage ring.

[0018] As an embodiment, the magnetorheological damper and the linear power unit are evenly distributed on the fixed disk in the circumferential direction.

[0019] As an embodiment, the measurement and control system includes an angular displacement sensor. A support ring is further connected to the outer wall of the housing through a fixing bracket. The angular displacement sensor is fixed on the support ring and is connected to the blade shaft for measuring the rotation angle of the blade shaft.

[0020] As an embodiment, the heating system includes a hot air blower, a heating coil and a temperature control module. The air outlet of the hot air blower is communicated with the outer bypass duct; the heating coil is arranged in the inner bypass duct for heating the inner bypass duct; heating sheets are arranged inside the guide vane blades, and the temperature control module is in communication connection with the heating sheets for heating the guide vane blades.

[0021] As an embodiment, the measurement and control system further includes a first temperature sensor for measuring the temperature of the guide vane blades and a second temperature sensor for measuring the temperature of the inner bypass duct.

[0022] As an embodiment, the principle prototype of the variable geometry low-pressure turbine regulating mechanism further includes an end cover. The end cover is fixedly connected to the ends of the inner casing, the outer casing and the housing. Through holes communicated with the outer bypass duct are arranged on the end cover; the air outlet of the hot air blower is communicated with the through holes.

[0023] The present invention has the following technical effects compared with the prior art:

[0024] The present invention can simulate the time-delay characteristics of the variable geometry low-pressure turbine regulating mechanism during the variable operating condition switching process of the engine, as well as the regulation accuracy of the switching mechanism under different operating modes, so as to better analyze the influence of the variable geometry low-pressure turbine on the overall performance of the aeroengine; moreover, by heating the components in the prototype and operating the drive assembly to change the angle of the guide vane blades in the prototype, the present invention can avoid dangerous situations such as overheating and surge that may occur when directly using the engine for experiments, and reduce the experimental cost. Description of the Drawings

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0026] Figure 1 It is a schematic structural diagram of a principle prototype of a variable geometry low-pressure turbine regulating mechanism in an embodiment of the present invention;

[0027] Figure 2 It is Figure 1 A schematic diagram from the rear view perspective;

[0028] Figure 3 It is Figure 1 A schematic structural diagram after removing the end cover;

[0029] Figure 4 It is Figure 3 A schematic structural diagram after removing the outer shell;

[0030] Figure 5 It is Figure 4 A partial enlarged view of area A;

[0031] Figure 6 It is a schematic structural diagram of a transmission mechanism in an embodiment of the present invention;

[0032] Figure 7 It is a schematic structural diagram of a hot air blower in an embodiment of the present invention;

[0033] Figure 8 It is a schematic structural diagram of the combined use of a principle prototype of a variable geometry low-pressure turbine regulating mechanism and a hot air blower in an embodiment of the present invention;

[0034] Figure 9 It is a test principle diagram of a semi-physical test device for a variable geometry low-pressure turbine regulating mechanism in an embodiment of the present invention.

[0035] Explanation of reference numerals:

[0036] 1. Outer shell; 2. Inner casing; 3. Outer casing; 4. Guide vane blade; 5. Rocker arm; 6. Rotating shaft; 7. Slide block; 8. Linear servo motor; 9. Outer connecting rod; 10. Inner connecting rod; 11. Fixed disk; 12. Magnetorheological damper; 13. Angular displacement sensor; 14. Support ring; 15. Hot air blower; 16. End cover; 17. Linking ring. Detailed implementation manners

[0037] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] To make the above objects, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0039] The present invention provides a semi-physical test device for a variable geometry low-pressure turbine regulating mechanism. By using semi-physical simulation for research, while reducing the test cost and potential safety hazards of the test, it can also ensure a high-precision simulation of the dynamic characteristics of the engine, simulate some processes that are difficult to achieve in the simulation process, and obtain some data that are difficult to obtain in the digital simulation process, laying a foundation for the design of the engine control system and the research of dynamic characteristics.

[0040] As Figures 1 to 9 shown, the present invention provides a semi-physical test device for a variable geometry low-pressure turbine regulating mechanism, including an engine model, a prototype of the variable geometry low-pressure turbine regulating mechanism, a heating system, a measurement and control system, a real-time simulator system, and a host computer.

[0041] The prototype of the variable geometry low-pressure turbine regulating mechanism (hereinafter referred to as the prototype) includes a housing 1, an inner casing 2, an outer casing 3, guide vane blades 4, and a driving assembly. The housing 1, the outer casing 3, and the inner casing 2 are coaxially sleeved from outside to inside; an outer bypass duct is formed between the housing 1 and the outer casing 3, the guide vane blades 4 are located in the inner bypass duct between the inner casing 2 and the outer casing 3, and the blade shafts of the guide vane blades 4 are rotatably arranged on the outer casing 3; the blade shafts are fixedly connected to one end of a rocker arm 5, and the other end of the rocker arm 5 is hinged to a linkage ring 17; the driving assembly is used to drive the linkage ring 17 to rotate. A plurality of guide vane blades 4 are evenly arranged in the circumferential direction. Specifically, in this embodiment, 24 guide vane blades 4 are provided, and the flow area of the inner bypass duct can be changed by rotating the guide vane blades 4 by different angles.

[0042] The heating system is used to heat the inner bypass duct, the outer bypass duct, and the guide vane blades 4 respectively.

[0043] The measurement and control system monitors the temperature of the inner bypass duct, the temperature of the outer bypass duct, the temperature of the guide vane blades 4, and the angle change of the guide vane blades 4.

[0044] The real-time simulator system is used to realize the real-time operation of the engine model.

[0045] The host computer is communicatively connected to the measurement and control system and the real-time simulator system, and is used to monitor the test process and record test data.

[0046] When conducting the test, the heating system heats the inner duct, the outer duct, and the guide vane blade 4 respectively to simulate the vacuum working environment of the variable geometry low-pressure turbine; the driving component drives the guide vane blade 4 to rotate by a set angle. The measurement and control system monitors the temperature of the inner duct, the temperature of the outer duct, the temperature of the guide vane blade 4, and the angle change of the guide vane blade 4, and feeds the data back to the host computer. After analyzing the data, the host computer transmits it to the real-time simulation machine system to realize the operation of the engine model. At the same time, other engine operation data, such as engine speed, flight altitude, Mach number, etc., can also be set through the real-time simulation machine system. The host computer can collect and analyze the data from sensors and actuators, and realize the function of displaying the operation state and parameter changes of the engine model, which is convenient for operators to monitor, diagnose faults, and provide decision support. Of course, if the operation state of the engine model needs to be adjusted and the guide vane blade 4 needs to be changed, the driving component can also be used to drive the guide vane blade 4 to rotate, thereby realizing the closed-loop control of the prototype. Thus, the present invention can simulate the time-delay characteristics of the variable geometry low-pressure turbine regulating mechanism during the variable working condition switching process of the engine, as well as the regulating accuracy of the switching mechanism under different operation modes, so as to better analyze the influence of the variable geometry low-pressure turbine on the overall performance of the aeroengine; moreover, the present invention heats the components in the prototype and operates the guide vane blade 4 in the prototype to change the angle, which can avoid dangerous situations such as overheating and surge that may occur when directly using the engine for testing, and also reduces the test cost.

[0047] As an embodiment, the driving component includes a linear power part and a transmission mechanism. The transmission mechanism includes a rotating shaft 6 and a slider 7. The output end of the linear power part is hinged to one end of the outer connecting rod 9, and the other end of the outer connecting rod 9 is hinged to one end of the rotating shaft 6; the slider 7 is fixedly connected to the linkage ring 17, the slider 7 is hinged to one end of the inner connecting rod 10, and the other end of the inner connecting rod 10 is hinged to the other end of the rotating shaft 6. The output end of the linear power part can perform linear motion. While performing linear motion, it drives one end of the outer connecting rod 9 to move, thereby driving the rotating shaft 6 to rotate. While the rotating shaft 6 rotates, it drives the inner connecting rod 10 to move, thereby driving the slider 7 to move. While the slider 7 moves, it drives the linkage ring 17 to rotate. When the linkage ring 17 rotates, it drives the blade shaft to rotate through the rocker arm 5, realizing the adjustment of the angle of the guide vane blade 4, achieving the change of the blade windward area, and thus changing the flow area of the inner duct.

[0048] As an embodiment, the linear power part is a linear servo motor 8.

[0049] As an embodiment, the prototype further includes a fixed disk 11. The fixed disk 11 is fixedly connected to the inner casing 2, the outer casing 3, and the housing 1. The fixed disk 11 fixes the linear power part through a bracket.

[0050] As an embodiment, a magneto-rheological damper 12 is also fixed on the fixed disk 11. The magneto-rheological damper 12 is drivingly connected to the linkage ring 17 through a transmission mechanism. The end of the magneto-rheological damper 12 is hinged to the end of the outer connecting rod 9. The magneto-rheological damper 12 is used to apply a load to the linkage ring 17. The magneto-rheological damper 12 and the linear power unit are evenly distributed on the fixed disk 11 in the circumferential direction. The measurement and control system further includes a programmable power supply, which is used to control the magnitude of the resistance provided by the magneto-rheological damper 12 to simulate aerodynamic force.

[0051] As an embodiment, the measurement and control system includes an angular displacement sensor 13. A support ring 14 is also connected to the outer wall of the housing 1 through a fixing bracket. The angular displacement sensor 13 is fixed on the support ring 14. The angular displacement sensor 13 is connected to the blade shaft and is used to measure the rotation angle of the blade shaft, that is, the rotation angle of the guide vane blade 4.

[0052] As an embodiment, the heating system includes a hot air blower 15, a heating coil (not shown in the figure), and a temperature control module. The air outlet of the hot air blower 15 is communicated with the outer bypass duct. The heating coil is arranged in the inner bypass duct and is used to heat the inner bypass duct. The heating coil can be used in combination with a box-type resistance furnace to also achieve the purpose of heating the inner bypass duct. Heating sheets are arranged inside the guide vane blade 4. The temperature control module is communicatively connected to the heating sheets and is used to heat the guide vane blade 4. Specifically, grooves for arranging the heating sheets are provided inside the guide vane blade 4.

[0053] As an embodiment, the measurement and control system further includes a first temperature sensor for measuring the temperature of the guide vane blade 4 and a second temperature sensor for measuring the temperature of the inner bypass duct.

[0054] As an embodiment, the prototype further includes an end cover 16. The end cover 16 is fixedly connected to the ends of the inner casing 2, the outer casing 3, and the housing 1. A through hole communicated with the outer bypass duct is provided on the end cover 16. The air outlet of the hot air blower 15 is communicated with the through hole.

[0055] As an example, in the present invention, the host computer is communicatively connected to the real-time simulation machine system through UDP, and the host computer is connected to the PLC measurement and control system through remote I / O and serial communication.

[0056] The PLC measurement and control system is composed of a temperature control module, a servo controller, a programmable power supply, an Advantech industrial computer, an Advantech 1723U signal output card, an Advantech 1747U signal acquisition card, and supporting low-voltage components, and is used to complete the acquisition of on-site sensor signals and servo control. The first temperature sensor and the second temperature sensor can adopt K-type thermocouples.

[0057] The temperature control module is used to control and collect the temperature of the blades of the variable geometry low-pressure turbine regulating mechanism prototype and communicate with the host computer through the RS485 serial port protocol.

[0058] The servo controller is used to control the start / stop, displacement and rotational speed of the servo motor, and communicates with the host computer through the RS485 serial port protocol.

[0059] The programmable power supply is used to control the resistance provided by the magnetorheological damper 12 and communicates with the host computer through the RS232 serial port protocol.

[0060] The first temperature sensor is used to collect the blade temperature and transmit it to the temperature control module.

[0061] The second temperature sensor is used to collect the temperature of the inner duct and communicates with the host computer through the 1747U analog acquisition board.

[0062] The real-time simulation machine system uses the real-time simulation settings of Matlab software to realize the real-time operation of the engine model. Through this system, experimenters can observe the performance of the engine under different working conditions in real time, analyze its operating characteristics, and adjust relevant parameters in a timely manner to optimize the effect of the engine.

[0063] The host computer is developed using LABview software and is responsible for centralized monitoring, data processing and human-computer interaction. It realizes the control and management of the entire semi-physical test device through communication with the PLC measurement and control system and the real-time simulation machine system.

[0064] A semi-physical test method for a variable geometry low-pressure turbine regulating mechanism provided by the present invention includes the following steps:

[0065] Step 1: Check the test device

[0066] (1) Check whether there is any looseness or locking of each connecting part.

[0067] (2) Check whether the circuit is normal and whether there is any disconnection of the circuit.

[0068] (3) Check whether the zero return switch is normal.

[0069] (4) Check whether there are any sundries around the hot air blower 15. When the hot air blower 15 rotates, there should be no foreign objects at the air inlet.

[0070] Step 2: Turn on the power supply switch.

[0071] Step 3: Turn on the heating resistance box.

[0072] (1) After the intelligent temperature controller is powered on and self - tested, the actual furnace temperature is displayed on the upper window PV, and the heat preservation time to reach the set temperature is displayed on the lower window SV (when TE = 0, the timing function is cancelled, and the set temperature is displayed on the lower window SV). If you need to change the set value, you can press the SET setting key on the temperature controller once. The upper window displays SP (set temperature), and the lower window displays the set value. At this time, you can change the set value by pressing the △ and ▽ keys, and then press the SET setting key again to confirm the set value. At this time, the upper window of the instrument displays ST (set time), and the lower window displays the timing time in minutes. At this time, you can change the timing time by pressing the △ and ▽ keys, and then press the SET setting key again to confirm the timing time. The instrument returns to the normal state (when TE = 0, the timing function is cancelled, and the equipment is always at a constant temperature).

[0073] (2) Turn the "Heating" switch of the electric control box to the on position. The electric furnace starts to heat up and automatically maintains a constant temperature near the set value after reaching the set value. During the heating process, adjust the "Current Adjustment" knob (i.e., adjust the size of the heating current) to an appropriate position according to the requirements of the heating rate and the temperature. Generally, 15A is appropriate.

[0074] Step 4: Turn on the power supply switch of the hot air blower 15, start the cold - blowing mode of the hot air blower 15, set the required heating temperature using the up and down keys, start the hot - blowing mode of the hot air blower 15, heat to the set temperature required for the test, and conduct the test after the temperature stabilizes.

[0075] Step 5: Turn on the real - time simulation machine system.

[0076] (1) Run the m - file.

[0077] (2) Run the engine SIMULINK real - time model.

[0078] Step 6: Turn on the variable - geometry low - pressure turbine regulating mechanism test platform (including the PLC measurement and control system).

[0079] (1) Run the LABview simulation software and click Run.

[0080] (2) Turn on the program - controlled power switch, and the program - controlled power indicator light turns green.

[0081] (3) Click the servo mechanism enable.

[0082] (4) Select the manual control mode on the physical entity interface, set the rotation angle of the guide vane blade 4 to 2 degrees, and set the running speed of the linear servo motor 8.

[0083] (5) The linear servo motor 8 stops moving, the guide vane blade 4 rotates 2 degrees, and after the engine model runs stably, switch to model control.

[0084] (6) Click on the engine control panel to set information such as the operating altitude, standard ambient temperature difference, low-pressure shaft speed, and flight Mach number of the engine model, and view the current operating status of the engine model.

[0085] (7) The heating temperature of the guide vane blade 4 can be set in the upper half of the temperature control panel, and the current temperature status of the prototype can be viewed in the lower half of the temperature control panel.

[0086] (5) Switch back to manual control.

[0087] (6) Stop the operation of the SIMULINK engine model.

[0088] (7) Set the angle of the guide vane blade 4 to 0.1 degrees.

[0089] (8) After the linear servo motor 8 moves in place, disable the servo mechanism.

[0090] (9) Turn off the program-controlled power supply.

[0091] (10) Stop running LABview.

[0092] Step 7: After the test is completed, start the cold blowing mode of the hot air blower 15. When the temperature of the guide vane blade 4 drops to 100 °C, stop the hot air blower 15 from blowing, and cut off the power supply of the hot air blower 15. Turn off the "heating" switch of the electric control box, cut off the power supply of the heating component, and the measurement and control system can still detect the furnace temperature during the cooling process.

[0093] Step 8: Cut off the power supply of the test bench and the upper computer.

[0094] Adaptations made according to actual requirements are all within the scope of protection of the present invention.

[0095] Specific examples are used in the present invention to elaborate on the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A semi-physical test device for a variable geometry low-pressure turbine regulating mechanism, characterized in that: Including engine model, variable geometry low-pressure turbine regulating mechanism prototype, heating system, measurement and control system, real-time simulator system and host computer; The variable geometry low-pressure turbine regulating mechanism principle prototype comprises an outer shell, an inner casing, an outer casing, guide vanes and a drive assembly, wherein the outer shell, the outer casing and the inner casing are coaxially sleeved from right outside to inside; an outer duct is formed between the outer shell and the outer casing, the guide vanes are located in the inner duct between the inner casing and the outer casing, and the blade shaft of the guide vanes is rotatably arranged on the outer casing; the blade shaft is fixedly connected to one end of a rocker arm, and the other end of the rocker arm is hinged to a linkage ring; the drive assembly is used to drive the linkage ring to rotate; The heating system is used to heat the inner duct, the outer duct and the guide vane blades respectively; The measurement and control system monitors the temperature of the inner duct, the temperature of the outer duct, the temperature of the guide vane blades, and the angle change of the guide vane blades; The real-time simulator system is used to realize the real-time operation of the engine model; The host computer is connected to the measurement and control system and the real-time simulation system in communication.

2. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 1, characterized in that: The driving assembly includes a linear power unit and a transmission mechanism, the transmission mechanism includes a rotating shaft and a slider, the output end of the linear power unit is hinged to one end of an outer connecting rod, and the other end of the outer connecting rod is hinged to one end of the rotating shaft; the slider is fixedly connected to the linkage ring, the slider is hinged to one end of an inner connecting rod, and the other end of the inner connecting rod is hinged to the other end of the rotating shaft; the rotating shaft is rotatably installed on the outer shell, and the outer connecting rod and the inner connecting rod are respectively located on the inner and outer sides of the outer shell.

3. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 2, characterized in that: The linear power unit is a linear servo motor.

4. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 2, characterized in that: The variable geometry low-pressure turbine regulating mechanism principle prototype also includes a fixed disk, which is fixedly connected to the inner casing, the outer casing and the outer casing, and the fixed disk fixes the linear power unit via a bracket.

5. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 4 is characterized in that: A magnetorheological damper is also fixed on the fixed disk. The magnetorheological damper is transmission-connected to the linkage ring through the transmission mechanism. The end of the magnetorheological damper is hinged to the end of the outer connecting rod. The magnetorheological damper is used to apply a load to the linkage ring.

6. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 5, characterized in that: The magnetorheological damper and the linear power unit are evenly distributed on the fixed disk along the circumferential direction.

7. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 6 is characterized in that: The measurement and control system includes an angular displacement sensor. A support ring is connected to the outer wall of the housing via a fixing frame. The angular displacement sensor is fixed on the support ring. The angular displacement sensor is connected to the blade shaft and is used to measure the rotation angle of the blade shaft.

8. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 7 is characterized in that: The heating system includes a hot air blower, a heating coil and a temperature control module. The air outlet of the hot air blower is connected to the outer duct. The heating coil is arranged in the inner duct for heating the inner duct. A heating plate is arranged inside the guide vane blades. The temperature control module is in communication with the heating plate for heating the guide vane blades.

9. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 8, characterized in that: The measurement and control system also includes a first temperature sensor for measuring the temperature of the guide vane blade and a second temperature sensor for measuring the inner duct temperature.

10. The semi-physical test device for variable geometry low-pressure turbine regulating mechanism according to claim 8, characterized in that: The principle prototype of the variable geometry low-pressure turbine regulating mechanism also includes an end cover, which is fixedly connected to the inner casing, the outer casing and the end of the outer casing, and is provided with a through hole connected to the outer duct; the air outlet of the hot air blower is connected to the through hole.

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