Full-scene nozzle movement mechanism tester under near-critical working condition

Abstract

The invention discloses a full-scene nozzle movement mechanism tester under a near-critical working condition. A cylindrical duct of a nozzle execution mechanism is mounted on a tester mounting table; one end of each convergence adjusting piece is connected with the cylindrical duct through a rotating pair, and the convergence adjusting pieces are installed around the circumferential face of the cylindrical duct in a circle in a circumferential array mode. The other end of the convergence adjusting sheet is connected with the expansion adjusting sheet through a revolute pair; the outer portion of the expansion adjusting piece is hinged to the connecting rod mechanism, the other end of the connecting rod mechanism is hinged to the adjusting ring, and the other side of the adjusting ring is connected with the hydraulic driving system. A ceramic heating sheet is adhered to the inner side surface of each spray pipe adjusting sheet to form a follow-up heating system; the follow-up pressurization system comprises a cylindrical pressurization pipeline, the pressurization pipeline and the spray pipe mechanism are coaxially installed, and a plurality of hose nozzles are arranged at the front end of the pressurization pipeline. According to the invention, uniform loading can be realized, local or overall heating can be realized, and various bionic motion configurations are compatible.

Description

Technical Field

[0001] The present invention relates to the testing field of nozzle motion mechanisms of military aircraft, and specifically, to a full-scenario nozzle motion mechanism tester under near-critical conditions, which has the characteristics of follow-up heating and follow-up pressurization, and can carry out tests on parameters such as the structural function, motion accuracy, reliability and durability of axisymmetric nozzle motion mechanisms. Background Art

[0002] The nozzle motion mechanism is an important component of the integrated design of military aircraft or engines. The aircraft engine produces high-temperature and high-pressure combustion gas, which is discharged into the atmosphere at a certain speed and direction after being adjusted by the motion mechanism of the nozzle device to achieve the thrust required for different flight conditions of the aircraft.

[0003] There are also some problems in the development process of new nozzles. First, if the newly developed new configuration nozzle is only simulated by a virtual prototype and is directly put into the production of the final product without being verified by the test platform principle, it cannot be guaranteed that the new nozzle meets the expected technical requirements; second, for different application scenarios, the design of the nozzle mechanism often requires the support of corresponding tester verification, but the existing tester technology is only designed for a certain type of engine nozzle, and the versatility is insufficient. Third, the existing tester technology is insufficient in simulating the real load environment of the nozzle device, and cannot fully reveal the load characteristics of the nozzle device in the real environment (high temperature and high pressure environment), and cannot fully guide the design of the nozzle device; finally, for the optimization design or redesign of some local positions that may exist in the development process of the nozzle device, according to the existing tester technology solution, it is often necessary to rebuild a set of special testers for verification, which will undoubtedly increase the design cost.

[0004] At present, there is a shortage of complete test equipment for nozzle motion mechanisms. There is no test equipment that can simulate the real working environment of the nozzle, achieve both uniform loading and local or overall heating, be compatible with multiple motion configurations, and have the ability to measure multiple dynamic parameters. Therefore, how to build a nozzle motion mechanism tester and provide test technical guidance to support the design and development of a new generation of nozzle devices has become a difficult problem that needs to be solved in the field of military aircraft propulsion technology. Summary of the invention

[0005] The purpose of the present invention is to address the deficiencies in the experimental research on the nozzle motion mechanism and to provide a full-scenario nozzle motion mechanism tester under near-critical conditions to carry out verification of the nozzle reliability test, help to fully grasp the motion reliability of the nozzle mechanism, and obtain the life cycle of the nozzle motion mechanism.

[0006] A full-scenario nozzle motion mechanism tester under near-critical conditions, comprising a tester mounting platform, on which a hydraulic drive system, a nozzle actuator, a follow-up pressurization system and a follow-up heating system are installed;

[0007] The nozzle actuator includes a cylindrical duct, a convergence adjustment plate, an expansion adjustment plate, a connecting rod mechanism and an adjustment ring; the cylindrical duct is installed on the tester mounting table through a flange structure; one end of the multiple convergence adjustment plates is connected to the cylindrical duct through a rotating pair to realize the rotation of the convergence adjustment plates relative to the cylindrical duct, and the circumferential array of the convergence adjustment plates is installed around the circumferential surface of the cylindrical duct to ensure internal sealing; the other end of the convergence adjustment plate is connected to the expansion adjustment plate through a rotating pair, and the expansion adjustment plate and the convergence adjustment plate rotate with each other; a connecting rod mechanism installation position is set on the outside of the expansion adjustment plate, which is connected to the connecting rod mechanism in a hinged manner, and the other end of the connecting rod mechanism is connected to the adjustment ring in a hinged manner, and the other side of the adjustment ring is connected to the hydraulic drive system, and the hydraulic actuator in the hydraulic drive system is used to push the adjustment ring and the connecting rod mechanism to transfer the force from the adjustment ring to the convergence adjustment plate and the expansion adjustment plate, so as to realize the contraction and expansion of the convergence adjustment plate and the expansion adjustment plate;

[0008] The convergence adjustment plate and the expansion adjustment plate are rectangular nozzle adjustment plates. A ceramic heating plate is attached to the inner surface of each nozzle adjustment plate to form a follow-up heating system. The ceramic heating plate is connected to a temperature control device to simulate the high temperature brought by the exhaust gas after high-temperature combustion in the combustion chamber of the aircraft engine.

[0009] The follow-up pressurization system is used to simulate the uniform load conditions on the convergence adjustment plate and the expansion adjustment plate under the actual working conditions of the aircraft engine, and includes a cylindrical pressurized pipe. The pressurized pipe is installed coaxially with the nozzle mechanism. A plurality of hose nozzles are provided at the front end of the pressurized pipe for uniformly spraying other nozzles onto the inner surfaces of the convergence adjustment plate and the expansion adjustment plate; the rear end of the pressurized pipe is connected to the pneumatic control system.

[0010] The pneumatic control system includes a screw air compressor, an air storage tank, a cold dryer and a valve connected in sequence; when it is necessary to conduct relevant tests on the nozzle movement mechanism, the valve is opened, and the high-temperature gas is filtered at different levels and evenly sprayed onto the inner surfaces of the convergence adjustment plate and the expansion adjustment plate through the hose nozzle in the follow-up pressurization system, providing pneumatic load for the nozzle mechanism.

[0011] Compared with the prior art, the present invention has the following beneficial effects:

[0012] 1. The full-scenario nozzle motion mechanism tester under near-critical conditions provided by the present invention has more reliable test results compared with the existing nozzle motion mechanism tester that cannot be heated and pressurized dynamically. The tester can adjust the temperature and pressure according to the movement of the nozzle mechanism, more realistically simulate the state of the nozzle motion mechanism under high temperature and pneumatic loading environment, and make the test data more accurate and reliable.

[0013] 2. The full-scenario nozzle motion mechanism tester under near-critical conditions provided by the present invention has the characteristic of convenient disassembly and assembly of the overall structure compared with the existing nozzle motion mechanism tester with complex structure. The test can complete the principle verification test of the nozzle configuration scheme, and guide the specific design scheme or structure selection through verification.

[0014] 3. The full-scenario nozzle motion mechanism tester under near-critical conditions provided by the present invention can realize the verification test of local mechanism schemes compared with the existing nozzle tester which is only used for overall verification. That is, the local components are replaced on the tester, and the local components are locally heated and pressurized to simulate the load environment of the local components and study the mechanism motion characteristics, service life, load characteristics and other parameters of the local components, so as to assist in the selection of local components.

[0015] 4. The full-scenario nozzle motion mechanism tester under near-critical conditions provided by the present invention is more versatile than the existing engine nozzle design dedicated tester. It can be widely used in education and scientific research experiments, providing an experimental teaching and scientific research exploration platform for teachers and students in schools and scientific research institutions, and helping students to deeply understand the working principle of the nozzle mechanism and related testing principles.

[0016] 5. The full-scenario nozzle motion mechanism tester under near-critical conditions provided by the present invention has the characteristics of multiple functions compared with the existing nozzle motion mechanism tester with single function. The tests that can be carried out include but are not limited to: verification test of the motion scheme and control scheme of the nozzle motion mechanism, measurement test of the dynamic parameters of the nozzle motion mechanism, reliability test and durability test of the nozzle motion mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings described herein are used to provide a further understanding of the content and embodiments of the present invention, constitute a part of this application, and do not constitute a limitation of the content and embodiments of the present invention. In the drawings:

[0018] Figure 1 It is a schematic diagram of the connection of the components of the nozzle motion mechanism tester of the present invention;

[0019] Figure 2 Schematic diagram of the motion mechanism of the nozzle motion mechanism tester of the present invention;

[0020] Figure 3 It is a schematic diagram of the installation platform of the nozzle motion mechanism tester of the present invention;

[0021] Figure 4 It is a schematic diagram of the MCH ceramic sheet pasting area in the follow-up heating device of the present invention;

[0022] Figure 5 is a schematic diagram of the high-pressure aerodynamic load application principle of the follow-up pressurization system in the embodiment;

[0023] Figure 6 is a schematic diagram of a pneumatic hose of a follow-up pressurization system in an embodiment;

[0024] Figure 7 It is a schematic diagram of the equipment and principle of the follow-up heating device in the embodiment;

[0025] Figure 8 1 is a test principle diagram of the nozzle motion mechanism tester in the embodiment. DETAILED DESCRIPTION

[0026] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with embodiments and drawings. The exemplary embodiments of the present invention and their description are only used to explain the present invention and are not intended to limit the present invention.

[0027] like Figure 1 and Figure 2 As shown, a full-scenario nozzle motion mechanism tester under near-critical conditions includes a tester mounting platform 1, on which a hydraulic drive system 2, a nozzle actuator 3, a follow-up pressurization system 4 and a follow-up heating system 5 are installed;

[0028] The nozzle actuator 3 includes a cylindrical duct 31, a convergence adjustment sheet 32, an expansion adjustment sheet 35, a connecting rod mechanism 34 and an adjustment ring 33; the cylindrical duct 31 is mounted on the tester mounting platform 1 through a flange structure; one end of the multiple convergence adjustment sheets 32 is connected to the cylindrical duct 31 through a rotating pair to realize the rotation of the convergence adjustment sheets 32 relative to the cylindrical duct 31, and the circumferential array of the convergence adjustment sheets 32 is installed around the circumferential surface of the cylindrical duct 31 to ensure internal sealing; the other end of the convergence adjustment sheet 32 ​​is connected to the expansion adjustment sheet 35 through a rotating pair The expansion regulating piece 35 and the convergence regulating piece 32 are connected, and the expansion regulating piece 35 and the convergence regulating piece 32 rotate with each other; the expansion regulating piece 35 is provided with a connecting rod mechanism installation position on the outside, and is connected to the connecting rod mechanism 34 by a hinged manner, and the other end of the connecting rod mechanism 34 is connected to the adjusting ring 33 by a hinged manner, and the other side of the adjusting ring 33 is connected to the hydraulic drive system 2, and the hydraulic actuator in the hydraulic drive system 2 is used to push the adjusting ring 33 and the connecting rod mechanism 34 to transfer the force from the adjusting ring 33 to the convergence regulating piece 32 and the expansion regulating piece 35, so as to realize the expansion and contraction of the convergence regulating piece 32 and the expansion regulating piece 35;

[0029] The convergence adjustment plate 32 and the expansion adjustment plate 35 are rectangular nozzle adjustment plates. A ceramic heating plate 51 is attached to the inner surface of each nozzle adjustment plate to form a follow-up heating system 5. The ceramic heating plate 51 is connected to a temperature control device to simulate the high temperature brought by the exhaust gas after high-temperature combustion in the combustion chamber of the aircraft engine. The ceramic heating plate 51 uses the MCH ceramic heating plate array heating method to heat and realize uniform temperature load loading. Figure 4 First, a groove of the same size as the MCH ceramic heating plate is designed on the surface of the nozzle adjustment plate; then a high-temperature gel is used to stick it to the groove area so that the surface of the nozzle adjustment plate obtains a uniform temperature field to complete the simulation purpose of the test. The MCH heating ceramic plate is a ceramic heating element sintered by ceramic and metal, and the high-temperature gel is HR-8812 copper oxide high-temperature glue. The loading temperature is 200-400℃.

[0030] The follow-up pressurization system 4 is used to simulate the uniform load conditions on the convergence adjustment plate 32 and the expansion adjustment plate 35 under the actual working conditions of the aircraft engine, and includes a cylindrical pressurized pipe 41. The pressurized pipe 41 is installed coaxially with the nozzle mechanism. A plurality of hose nozzles 42 are provided at the front end of the pressurized pipe 41 for uniformly spraying the other onto the inner surface of the convergence adjustment plate 32 and the expansion adjustment plate 35; the rear end of the pressurized pipe 41 is connected to the pneumatic control system 6.

[0031] The uniform pneumatic load is applied by blowing air directly to the surface of the adjustment piece using a hose nozzle 42. A hose nozzle 42 support is provided on the surface of each adjustment piece so that the nozzle is placed vertically to the adjustment piece so that when the adjustment piece moves in a convergent and an expanded manner, the nozzle always sprays uniform air to the convergent adjustment piece 32 and the expanded adjustment piece 35.

[0032] like Figure 2 As shown, the pneumatic control system 6 includes a screw air compressor 61, an air storage tank 62, a cold dryer 63 and a valve 64 connected in sequence; when it is necessary to conduct relevant tests on the nozzle movement mechanism, the valve 64 is opened, and the high-temperature gas is filtered at different levels and evenly sprayed onto the inner surfaces of the convergence adjustment plate 32 and the expansion adjustment plate 35 through the hose nozzle 42 in the follow-up pressurization system 4, providing aerodynamic load for the nozzle mechanism.

[0033] like Figure 8 It also includes information data acquisition devices required for the test, such as high-speed cameras, analytical balances, surface roughness meters, B&K data acquisition systems, pressure measurement: 0-4t, dynamic torque measurement: 0-20000N / m, patch thermocouple temperature sensor: 200-500℃, acceleration measurement, strain measurement, vibration acceleration measurement, linear / angular displacement measurement, and surface wear measurement.

[0034] The calculation process of the diameter of the rubber hose in the pressurization method of the follow-up pressurization system 4 using the hose nozzle 42 is as follows:

[0035] Step S1: List the Bernoulli equation

[0036]

[0037] Where: v represents the fluid velocity in the pipe; g represents the acceleration due to gravity, 9.8 m / s 2 ; z represents the height of the fluid; p represents the pressure of the fluid; ρ represents the density of the fluid, 1.29 kg / m 3 .

[0038] Step S2: Assume that the gas inside the pipeline is an ideal fluid and the gas flows on the same horizontal line. Since the gas is an ideal fluid and there is no compression, the flow rate of the gas flowing inside the pipeline remains unchanged, and its expression is:

[0039]

[0040] Where: d represents the diameter of the pipe.

[0041] Step S3: According to Formula 1, the outlet of the screw air compressor and the outlet of the nozzle loading position hose are used as two reference surfaces to establish the following equation:

[0042]

[0043] In the formula, v 1 represents the flow rate at the outlet of the screw air compressor, which can be calculated by formula 2; v 2 Indicates the flow rate at the nozzle pneumatic loading hose outlet; p 1 Indicates the pressure at the outlet of the air compressor; p 2 Indicates the pressure at the hose outlet.

[0044] Step S4: According to Formula 2, the hose diameter range can be calculated as:

[0045]

[0046] Design method of MCH heating ceramic sheet size of follow-up heating system 5:

[0047] Step S1: measuring the size of the expansion adjustment plate of the nozzle device (length a×width b×thickness h) as the basis for customizing the size of the MCH ceramic heating plate 51;

[0048] Step S2: Set the center point of the rectangular heating ceramic sheet to coincide with the center point of the regulating sheet. In order to ensure that the heat transfer rate of the entire regulating sheet is the same and achieve uniform heating, the thickness dimension is used as a reference to determine the size of the selected MCH ceramic heating sheet 51;

[0049] Step S3: The distances between the edges of the MCH ceramic heating plate 51 in the other two directions and the two boundary lines of the adjustment plate are 1.5 mm respectively. Figure 4 The figure shows the MCH ceramic heating sheet 51 pasting area schematic diagram;

[0050] Step S4: The heat transfer rate of the nozzle expansion and convergence adjustment plate can be obtained according to the following heat transfer rate calculation formula:

[0051]

[0052] Wherein, υ represents the heating rate; ρ represents the density of the nozzle adjusting plate; C represents the density specific heat capacity of the nozzle adjusting plate; V represents the volume of the nozzle adjusting plate; and W represents the heat source power.

[0053] Step S5: According to Formula 5, the power of the heat source can be controlled through the control link to control the temperature on the expansion and convergence adjustment sheet in real time.

[0054] (6) The sixth item provides a design of a nozzle mechanism tester mounting platform 1

[0055] The nozzle mechanism tester mounting platform 1 provided by the present invention is rigidly connected by a flange. Considering that the nozzle mechanism has a long structure, relying on a single left bracket may easily cause the entire tester to overturn. Figure 3 , A U-shaped bracket is set under the tester mounting table 1. The center of the U-shaped bracket is designed with a groove to avoid the installation space of the expansion adjustment plate drive mechanism of the tester mounting table 1. The left bracket and the U-shaped bracket provide two support positions for the horizontally placed tester mounting table 1 to ensure the stability of the entire tester. The two support brackets are installed on the T-slot platform, and the position of the clamp on the T-slot can be adjusted to facilitate the positioning of the two brackets. ,

[0056] Specific technical indicators of the tester provided by the present invention are as follows:

[0057] ①Test bench load: not less than 2t;

[0058] ② Test piece size range: diameter compatible not less than 1080mm, length compatible not less than 1800mm;

[0059] ③The loading equipment is divided into two sets, and the loading capacities are:

[0060] 1) Heating capacity: local heating, overall heating, temperature range: 200~400℃;

[0061] 2) Pressurization capacity: local pressurization, overall pressurization, loading range: 100~500kPa;

[0062] ④ Driving capacity of the test piece mechanism: no less than 4 independent oil supply lines, the oil pressure of each line is not less than 12MPa, and the flow rate of each line is not less than 3L / s.

[0063] The measurement capabilities of the nozzle motion mechanism tester provided by the present invention mainly include:

[0064] ①Pressure measurement: 0~4t

[0065] ②Dynamic torque measurement: 0~20000N / m

[0066] ③SMD thermocouple temperature sensor: 200~500℃

[0067] ④Acceleration measurement;

[0068] ⑤Strain measurement;

[0069] ⑥High-speed camera

[0070] ⑦Analytical balance;

[0071] ⑧Surface roughness tester;

[0072] ⑨Vibration acceleration measurement;

[0073] ⑩B&K data acquisition system.

[0074] This specific implementation method mainly includes three parts: 1. Specific implementation method of the follow-up pressurization system 4; 2. Specific implementation method of the follow-up heating device; 3. Specific implementation method of the overall measurement system.

[0075] 1. Specific implementation method of follow-up pressurization system 4;

[0076] The follow-up pressurization system 4 provides a pressurization method using a hose nozzle 42, such as Figure 1 As shown, the following steps are included:

[0077] Step S1: designing an airflow duct according to the designed nozzle inner wall structure shape, with multiple small nozzles evenly distributed on the duct surface;

[0078] Step S2: installing the air flow duct perpendicular to the surface of the nozzle adjustment plate through the hose;

[0079] Step S3: introducing high-pressure airflow into the airflow duct so that the uniformly arranged nozzles eject high-speed airflow;

[0080] Step S4: The evenly distributed impact airflow acts on the surface of the nozzle tester adjustment plate, thereby completing the simulation of the axisymmetric high-pressure aerodynamic load pressurization process.

[0081] The air compressor pump model of this pressurization method that provides high-pressure gas for the nozzle is a VSD45A fixed compressor, which is lubricated by oil. The working principle adopts a screw-type supercharging method and can realize frequency conversion control. When working, the clean air in the air tank 62 is pressurized by the screw-type supercharging air pump in the air compressor pump to generate 1.3MPa high-pressure gas (exhaust volume is 508m 3 / min), and then stored in the gas storage tank 62. When high-pressure gas is needed, open the valve 64, pass the cold dryer 63 to cool and dry the gas, and then pass through various levels of filtering devices to achieve the supply of high-pressure gas required by the nozzle. The equipment matches the pipe interface model G2, and is installed using a threaded pipe with a diameter of 50.8mm. Figure 5 A schematic diagram of the principle of applying high-pressure aerodynamic loads is provided. In this pressurization method, one nozzle position is evenly arranged on each convergence adjustment plate, and two nozzle positions are evenly distributed on each expansion adjustment plate. The nozzle tester of this pressurization method has a total of 12 expansion adjustment plates 35, 12 convergence adjustment plates 32, and a total of 36 hose nozzles 42. Therefore, a total of 48 pneumatic hoses are required, and the material of the pneumatic hose is rubber steel wire. Substituting the data into the diameter calculation process of the rubber hose in the fourth item of the present invention, it can be determined that the diameter of the rubber hose is 8mm within the allowable range. The schematic diagram of the pneumatic hose of this pressurization method is shown in Figure 6 .

[0082] 2. Specific implementation methods of the follow-up heating device;

[0083] The follow-up heating device provides a heating method for the ceramic heating plate 51 array, such as Figure 7 As shown, the following steps are included:

[0084] Step S1: according to the characteristics of the MCH heating ceramic sheet, a recessed area of ​​a suitable size for installing the heating ceramic sheet is set on the surface of the nozzle adjustment sheet;

[0085] Step S2: Use high temperature resistant gel to stick the MCH heating ceramic sheet to the installation area;

[0086] Step S3: The MCH heating ceramic sheet is embedded in the nozzle adjustment sheet, which will not interfere with the mutual movement between the convergence and expansion adjustment sheets 35 and the convergence adjustment sheet 32, thereby ensuring that the temperature of the nozzle mechanism always follows the system during the expansion and contraction process.

[0087] The MCH heating ceramic sheet selected for this heating method refers to a ceramic heating element made by printing high-melting-point metal heating resistor slurry such as metal tungsten or molybdenum manganese on 92-96% alumina cast ceramic green body according to the requirements of the heating circuit design, and then hot-pressing and laminating. Then, the ceramic and metal are sintered together under the protection of a reducing atmosphere at around 1600°C. It meets environmental protection requirements such as EU RoSH.

[0088] The high temperature gel used in this heating method is HR-8812 copper oxide high temperature glue, the main component of which is inorganic copper oxide. It can withstand temperatures of 700 degrees Celsius for a long time and 980 degrees Celsius for a short time. It is suitable for filling, potting, and bonding socket conditions.

[0089] The size of the MCH heating ceramic sheet in this heating method is based on the size and thickness of the nozzle adjustment sheet. It is necessary to ensure that the heat transfer rate of the entire nozzle adjustment sheet is the same to achieve uniform heating. For the convenience of control, the heating temperature of the heating sheet is controlled by controlling the resistance.

[0090] This heating method requires pasting a patch-type eddy current sensor on the surface of the nozzle adjustment plate to grasp the temperature on the nozzle adjustment plate in real time and ensure that each nozzle adjustment plate can reach the temperature required for the test.

[0091] 3. Specific implementation methods of the overall measurement system.

[0092] The overall measurement system principle diagram of the nozzle motion mechanism tester provided by the present invention is as follows: Figure 8 As shown, including but not limited to the following testing capabilities:

[0093] ① Blocking force measurement: Fix the tension sensor between the hydraulic actuator and the connecting rod mechanism 34 to measure the blocking force change of the driving mechanism;

[0094] ② Stress and strain measurement: stick the strain gauge on the outer surface of the nozzle adjustment plate to measure the stress and strain of the nozzle adjustment plate under high temperature and high pressure environment;

[0095] ③ Temperature measurement: Paste the patch thermocouple temperature sensor on the surface of the nozzle adjustment plate to measure the nozzle surface temperature;

[0096] ④ Linear displacement measurement: Place a high-speed camera at the nozzle outlet to measure the displacement of the nozzle adjustment plate and the change in the nozzle throat area;

[0097] ⑤ Angular displacement measurement: Install the angle encoder on the rotating pair of the mechanism to measure the angular displacement of the mechanism;

[0098] ⑥Vibration acceleration measurement: The Polytec laser scanning vibration measurement system is set up next to the nozzle to measure the vibration acceleration of the nozzle tester;

[0099] ⑦ Surface wear measurement: Disassemble the key components of the nozzle, use a 3D profile measuring instrument to scan the surface profiles of the rotating and moving pairs, and obtain the wear amount of the contact surface.

Claims

1. A full-scenario nozzle motion mechanism tester under near-critical conditions, characterized in that: The tester installation platform (1) comprises a hydraulic drive system (2), a nozzle actuator (3), a follow-up pressurization system (4) and a follow-up heating system (5) installed on the tester installation platform (1); The nozzle actuator (3) comprises a cylindrical duct (31), a convergence adjustment plate (32), an expansion adjustment plate (35), a connecting rod mechanism (34) and an adjustment ring (33); the cylindrical duct (31) is mounted on the tester mounting platform (1) via a flange structure; one end of the plurality of convergence adjustment plates (32) is connected to the cylindrical duct (31) via a rotating pair to enable the convergence adjustment plates (32) to rotate relative to the cylindrical duct (31); the circumferential array of the convergence adjustment plates (32) is installed around the circumferential surface of the cylindrical duct (31) to ensure internal sealing; the other end of the convergence adjustment plate (32) is connected to the expansion adjustment plate (35) via a rotating pair. The expansion regulating piece (35) and the convergence regulating piece (32) are connected to each other, and the expansion regulating piece (35) and the convergence regulating piece (32) are rotated with each other; a connecting rod mechanism installation position is arranged outside the expansion regulating piece (35), and is connected to the connecting rod mechanism (34) by means of a hinge; the other end of the connecting rod mechanism (34) is connected to the regulating ring (33) by means of a hinge; the other side of the regulating ring (33) is connected to the hydraulic drive system (2); the hydraulic actuator in the hydraulic drive system (2) is used to push the regulating ring (33) and the connecting rod mechanism (34) to transfer the force from the regulating ring (33) to the convergence regulating piece (32) and the expansion regulating piece (35), so as to realize the contraction and expansion of the convergence regulating piece (32) and the expansion regulating piece (35); The convergence adjustment plate (32) and the expansion adjustment plate (35) are rectangular nozzle adjustment plates, and a ceramic heating plate (51) is attached to the inner surface of each nozzle adjustment plate to form a follow-up heating system (5). The ceramic heating plate (51) is connected to a temperature control device to simulate the high temperature brought by the exhaust gas after high-temperature combustion in the combustion chamber of the aircraft engine; The follow-up pressurization system (4) is used to simulate the uniform load on the convergence adjustment plate (32) and the expansion adjustment plate (35) under the actual working conditions of the aircraft engine, and includes a cylindrical pressurization pipe (41). The pressurization pipe (41) is installed coaxially with the nozzle mechanism. The front end of the pressurization pipe (41) is provided with a plurality of hose nozzles (42) for uniformly spraying the other onto the inner surface of the convergence adjustment plate (32) and the expansion adjustment plate (35); the rear end of the pressurization pipe (41) is connected to the pneumatic control system (6).

2. A full-scenario nozzle motion mechanism tester under near-critical conditions according to claim 1, characterized in that: The pneumatic control system (6) comprises a screw air compressor (61), an air storage tank (62), a cold dryer (63) and a valve (64) connected in sequence; during the test, the valve (64) is opened, and the high-temperature gas is filtered at different levels and then evenly sprayed onto the inner surfaces of the convergence adjustment plate (32) and the expansion adjustment plate (35) through the hose nozzle (42) in the follow-up pressurization system (4), thereby providing a pneumatic load for the nozzle mechanism.

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