Variable parameter dynamic simulation device and method for aero-engine guide vane

Abstract

The application discloses an aero-engine guide vane variable parameter dynamic simulation device and method, and relates to the technical field of aero-engine guide vane parameter simulation. The application dynamically simulates various parameters of the aero-engine guide vane under near-working condition, so as to obtain dynamic change parameters of the aero-engine under various turbine inlet flame states in a typical flight cycle, and realizes accurate control of the surface temperature of the aero-engine guide vane and rapid and accurate tracking control of the temperature, pressure and flow of the cooling airflow through a fuzzy self-adaptive PID algorithm, thereby effectively solving the problem of dynamic simulation of the aero-engine guide vane variable parameters under near-working condition, providing experimental conditions for the design of the blade cooling channel shape, the measurement of the heat insulation effect of the thermal barrier coating and the service life prediction of the blade, and facilitating the dynamic simulation research of the aero-engine guide vane under different service conditions by researchers.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of parameter simulation of aero-engine guide vane, and particularly relates to a device and method for dynamic simulation of variable parameters of aero-engine guide vane. BACKGROUND

[0002] With the gradual improvement of the performance of an aero-engine, the flame temperature at the outlet of a combustion chamber is increased, and the temperature of cooling air inside a turbine guide vane is also changed from normal temperature to high temperature due to heat transfer. During the flight of an airplane, different modes need to be switched, such as take-off, climbing, cruising, flight slow speed, and reverse thrust, at this time, the parameters of turbine inlet temperature, cooling air temperature, pressure, flow rate, and the like are dynamically changed, different airplane design parameters are different, the turbine inlet temperature of the turbine guide vane can reach 1600-2300K, the pressure can reach 2-3MPa, the average flow rate can reach 1kg / s, the flow velocity can reach 0.2-0.3 Mach, the turbine guide vane cooling air temperature can reach 800-900K, the pressure can reach 1.5MPa, and the average flow rate can reach 0.1kg / s. In the development of the aero-engine guide vane variable parameter dynamic simulation method and device under the near working condition, the research and development of the parameter dynamic change simulation is still relatively less in the domestic, and the problems of how to accurately and quickly control the temperature, pressure, and flow rate are difficult to solve.

[0003] The service environment of an aero-engine is very complex, and the environments of high temperature, high pressure, large temperature change, CMAS corrosion, and fatigue become the norm. In the research of the existing simulation equipment, the cooling air is mostly processed at normal temperature and pressure, it is difficult to accurately control and measure the temperature, pressure, and flow rate of the cooling air, and the simulation of the turbine inlet flame is also carried out under the static and unchanged condition. SUMMARY

[0004] To solve the above problems in the prior art, the present application provides an aero-engine guide vane variable parameter dynamic simulation device and method.

[0005] To achieve the above purpose, the present application provides the following scheme:

[0006] An aero-engine guide vane variable parameter dynamic simulation device, comprising: a flame spraying system, an air compressor, a booster, a heater, an adapter sleeve, a monitoring system, and a control system;

[0007] The monitoring system, the air compressor, the booster, and the heater are electrically connected with the control system; the air compressor is connected with the booster through a pipeline; the booster is connected with the heater through a pipeline; the heater is connected with the adapter sleeve through a pipeline; the adapter sleeve is connected with a sample; the sample is an aero-engine guide vane or a simulated piece in the shape of a disc or a cylinder;

[0008] The monitoring system is used for monitoring simulation parameters; the simulation parameters include: flame temperature of the flame spraying system, flame speed of the flame spraying system, sample surface temperature, heater bore temperature, heater outlet pipe temperature, sample end gas temperature, sample back temperature, gas and oxygen inlet and outlet rate, gas and cooling gas flow, and cooling gas flow pressure; the control system is used for generating simulation parameter dynamic adjustment instructions, determining sample service parameters based on the simulation parameters, predicting service time of the sample based on the simulation parameters, and calculating and tracking the simulation parameters through a fuzzy adaptive PID algorithm according to a measured service parameter change curve; the air compressor, the supercharger and the heater are respectively acted on based on the simulation parameter dynamic adjustment instructions;

[0009] The air compressor is used for compressing air to provide a gas source for sample service simulation; the supercharger is used for pressurizing the gas to a pressure under sample service simulation conditions to obtain compressed gas; and the heater is used for heating the compressed gas.

[0010] Optionally, the monitoring system includes: a first thermocouple, a vortex flowmeter, a second thermocouple, a third thermocouple, a temperature measuring instrument, a particle speed meter and a fourth thermocouple;

[0011] The first thermocouple and the vortex flowmeter are sequentially arranged on a connecting pipeline of the heater and the adapter sleeve; the second thermocouple and the third thermocouple are both arranged on the sample; and the fourth thermocouple is arranged in the bore of the heater.

[0012] The first thermocouple, the vortex flowmeter, the second thermocouple, the third thermocouple, the temperature measuring instrument, the fourth thermocouple and the particle speed meter are all electrically connected with the control system.

[0013] The first thermocouple is used for measuring the heater outlet pipe temperature; the vortex flowmeter is used for measuring the gas and cooling gas flow; the second thermocouple is used for measuring the sample back temperature; the third thermocouple is used for measuring the sample end gas temperature; the fourth thermocouple is used for measuring the bore temperature of the heater; the temperature measuring instrument is used for measuring the sample surface temperature; the particle speed meter is used for measuring the flame temperature and the flame speed of the flame spraying system; a sensor in the flame spraying system can monitor the gas and oxygen inlet and outlet rate in real time; and an adjusting valve of the supercharger is used for adjusting the cooling gas flow pressure.

[0014] Optionally, the flame spraying system includes: a spray gun and a spray gun holding device.

[0015] The spray gun is arranged on the spray gun holding device; and the spray gun is used for providing a gas heat source in the sample service simulation process.

[0016] Optionally, the spray gun holding device adopts any one of a roller type, a fixed type, and a mechanical arm type to hold the spray gun.

[0017] Optionally, the heat preservation system is further included.

[0018] The heat preservation system is arranged on the heater, and the heat preservation system wraps the input and output pipelines of the heater.

[0019] Optionally, the heat preservation system is aluminum silicate heat preservation cotton or aluminum silicate ceramic fiber blanket.

[0020] Optionally, the maximum supercharging range of the supercharger is 1-3 MPa.

[0021] Optionally, the maximum heating temperature of the heater is 900 K.

[0022] Optionally, the output gas temperature of the flame spraying system is at most 2300 K, and the flow rate is at most 2 Mach.

[0023] Optionally, the control system includes a computer control system and a parameter display and control cabinet.

[0024] The monitoring system, the air compressor, the supercharger, the heater, and the computer control system are electrically connected to the parameter display and control cabinet.

[0025] An aero-engine guide vane variable parameter dynamic simulation method applied to the aero-engine guide vane variable parameter dynamic simulation device provided above; the method comprises:

[0026] Obtaining simulation parameters of an aero-engine guide vane;

[0027] Simulating operation parameters of an aero-engine at different operations in a typical flight cycle based on the simulation parameters; the operation parameters include turbine inlet temperature, cooling air temperature, pressure, and flow rate.

[0028] Obtaining a historical service parameter change curve;

[0029] Implementing parameter calculation and simulation tracking of the aero-engine guide vane based on the historical service parameter change curve by using a fuzzy self-adaptive PID algorithm;

[0030] Testing the temperature difference before and after the aero-engine guide vane and determining the heat insulation temperature of the aero-engine guide vane based on the parameters collected in the service simulation process.

[0031] Predicting the service time of the aero-engine guide vane based on the historical service parameter change curve by using a machine learning algorithm.

[0032] According to the specific embodiments of the present application, the following technical effects are disclosed:

[0033] The aviation engine guide vane variable parameter dynamic simulation device and method provided by the present application can simulate various parameters of the aviation engine guide vane under near working condition, so as to obtain dynamic change parameters of the aviation engine under various turbine inlet flame states in a typical flight cycle, and realize accurate control of the surface temperature of the aviation engine guide vane and rapid and accurate tracking control of the temperature, pressure and flow of the cooling air flow through the fuzzy self-adaptive PID algorithm, thereby effectively solving the problem of dynamic simulation of the aviation engine guide vane variable parameters under near working condition, providing experimental conditions for the design of the blade cooling channel shape, the measurement of the heat insulation effect of the thermal barrier coating, and the service life prediction of the blade, and facilitating the dynamic simulation research of the aviation engine guide vane under different service conditions by researchers. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0035] Figure 1 The structure diagram of the aviation engine guide vane variable parameter dynamic simulation device provided by the present application is shown in the figure.

[0036] Figure 2 The flow chart of the aviation engine guide vane variable parameter dynamic simulation method provided by the present application is shown in the figure.

[0037] Figure 3 The temperature change curve of the sample provided by the present application is shown in the figure.

[0038] Symbol explanation:

[0039] 1-air compressor, 2-connection pipeline, 3-supercharger, 4-heater inlet pipeline, 5-heater, 6-first thermocouple, 7-vortex flowmeter, 8-heater outlet pipeline, 9-switching sleeve, 10-second thermocouple, 11-third thermocouple, 12-sample, 13-temperature measuring instrument, 14-oxygen feeding inlet, 15-fuel feeding inlet, 16-lance, 17-lance clamping device, 18-computer control system, 19-parameter display and control cabinet, 20-particle speedometer. DETAILED DESCRIPTION

[0040] Clearly, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative efforts fall within the protection scope of the present application.

[0041] The object of the present application is to provide an aero-engine guide vane variable parameter dynamic simulation device and method, which can accurately control and measure the temperature, pressure and flow of cooling air flow, and simulate various states of turbine inlet flame.

[0042] In order to make the above-mentioned objects, characteristics and advantages of the present application more apparent and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0043] The aero-engine guide vane variable parameter dynamic simulation device provided by the present application, as shown in Figure 1 The aero-engine guide vane variable parameter dynamic simulation device provided by the present application, as shown in

[0044] The monitoring system comprises a first thermocouple 6, a vortex flowmeter 7, a second thermocouple 10, a third thermocouple 11, a temperature measuring instrument 13, a particle speedometer 20 and a fourth thermocouple. The flame spraying system comprises a spray gun 16 and a spray gun holding device 17. The spray gun 16 is provided with an oxygen inlet 14 and a fuel inlet 15. The control system comprises a computer control system 18 and a parameter display and control cabinet 19.

[0045] The air compressor 1 is connected with the supercharger 3 through the connecting pipeline 2. The first end of the heater inlet pipeline 4 is connected with the supercharger 3, the second end of the heater inlet pipeline 4 is connected with the heater 5, the first end of the heater outlet pipeline 8 is connected with the heater 5, the second end of the heater outlet pipeline 8 is connected with the adapter sleeve 9, and the vortex flowmeter 7 is fixed on the heater outlet pipeline 8. The adapter sleeve 9 can connect the outlet pipeline with the sample 12. The sample 12 is fixed on the adapter sleeve 9. The inner bore of the heater 5 and the pipeline outlet are both provided with thermocouples for temperature measurement. The heat preservation system uses aluminum silicate ceramic fiber blanket (or aluminum silicate heat preservation cotton) to heat the inside of the heating device, and wraps the input and output pipelines of the heating device to reduce heat loss, and uses nichrome wire for fixing. The flow testing system uses the vortex flowmeter 7, the spray gun holding device 17 can use a roller type, fixed clamping or use a mechanical arm for clamping. The particle speedometer 20 can measure the speed and temperature of the flame by monitoring the state of different flame particles. The temperature measuring instrument 13 can perform non-contact temperature measurement on the surface of the sample 12. The thermocouples can measure the temperature of the cooling gas at the back of the sample and the end of the sample.

[0046] The fire system is used to provide the gas heat source for the sample 12 during service. The temperature measuring instrument 13 is used to measure the surface temperature of the sample 12. The air compressor 1 is used to compress air to provide the gas source. The booster 3 is used to boost the pressure to the service condition. The heater 5 is used to heat the compressed gas. The adapter sleeve 9 is used to connect the outlet pipe. The monitoring system measures the flame temperature and speed through the particle speedometer 20, measures the sample surface temperature through the temperature measuring instrument 13, measures the heater bore temperature, the heater outlet pipe temperature, the sample end gas temperature, and the sample back temperature through different thermocouples, monitors the cooling gas flow pressure through the booster 3 pressure regulating valve, and measures the gas and oxygen inlet and outlet rates and the thermocouple measurement values can be displayed on the parameter display and control cabinet 19 and the computer. The heat preservation system is used for heat preservation and insulation of the heater 5 and the cold gas outlet. The heater 5 is connected with the parameter display and control cabinet 19. The parameter display and control cabinet 19, the flow meter, and the booster 3 pressure regulating valve are connected with the computer control system 18. The control system uses computer software to adjust the flame by controlling the gas and oxygen rates, controls the cold gas temperature by controlling the heater 5 heating power, and controls the cooling gas flow pressure and flow by controlling the booster 3. Among them, the computer control system 18 uses a fuzzy self-adaptive PID algorithm to control the surface temperature, the cooling gas flow temperature, the pressure, and the flow.

[0047] In the present application, the sample 12 used above is an aero-engine guide vane, including but not limited to a simulation piece in the shape of a disc, a cylinder, and a blade.

[0048] Based on the above description, the monitoring system realizes the monitoring of the gas, the cooling gas flow temperature, the pressure, and the flow. The control system can calculate and quickly track the changing gas and cooling gas flow parameters through the fuzzy self-adaptive PID algorithm according to the measured service parameter change curve. The heat preservation system can greatly improve the heat utilization rate.

[0049] A specific implementation is provided below to illustrate the specific implementation process and advantages of the aero-engine guide vane variable parameter dynamic simulation device provided above.

[0050] In the experiment process of parameter dynamic simulation using the above-mentioned aero-engine guide vane variable parameter dynamic simulation device provided in the embodiment, the air compressor 1 can provide a pressure of 1.2 MPa, the supercharger 3 can be supercharged to 1-3 MPa, the heater 5 can be heated to a temperature of 900 K, the heater 5 uses nickel-chromium wire rapid heating, and a PID control is used to control the internal temperature and outlet temperature of the heating pipe, the power is 10 KW, the voltage is 380 V, a parameter display and control cabinet 19 uses a silicon controlled cabinet, can display temperature and high temperature early warning, the parameter display and control cabinet 19 is connected with the computer control system 18, the inner bore of the heater 5 is made of 310s high-temperature-resistant stainless steel, and the heater 5 and the thermocouple are connected with the silicon controlled cabinet. The vortex flowmeter 7 is battery-powered and can withstand a temperature of 900 K. The temperature measurement system, the vortex flowmeter 7 and the supercharger 3 can be connected with the computer control system 18 through a wireless module or a wired module (RS485 communication protocol, etc.), and the computer control system 18 can be monitored and controlled.

[0051] In the embodiment, the control system uses a fuzzy self-adaptive PID algorithm to automatically and accurately and quickly control the temperature, flow and pressure.

[0052] The time domain transfer function of the PID controller is described as:

[0053]

[0054] The three terms are proportional, integral and differential terms, wherein K p is the proportional gain. T i is the integral time constant. T d is the differential time constant. u(t) is the control amount (controller output). e(t) is the deviation of the controlled quantity from the given value.

[0055] Proportional control can quickly reflect the error and thus reduce the error, but proportional control cannot eliminate the steady-state error. As long as there is an error in the system, the integral control action will continuously accumulate to eliminate the error. Therefore, as long as there is enough time, the integral control will be able to completely eliminate the error, but too strong integral action will increase the overshoot of the system and even cause the system to oscillate. The differential control can reduce the overshoot, overcome the oscillation, improve the stability of the system, and at the same time, speed up the dynamic response speed of the system, reduce the adjustment time, and thus improve the dynamic performance of the system.

[0056] In the embodiment, the temperature, flow and pressure are the controller outputs u(t), and the fuzzy self-adaptive PID algorithm is used, on the basis of the classical PID, to add a fuzzy control rule library to automatically adjust K p , T i , T d in real time, so that the reaction can be quickly and accurately controlled.

[0057] Since heating of gases with different flow rates is required, heaters 5 with different heating powers need to be selected through calculation. In this embodiment, the conversion principle between heating pipe temperature and maximum intake volume is as follows:

[0058] Relationship between heating pipe and compressed air flow rate:

[0059] P = c × m × △T × w / 863.

[0060] P is power, c is specific heat capacity (J / (kg·K)), m is weight (or flow rate weight), ΔT is temperature difference, and w is heat loss.

[0061] m = V × ρ.

[0062] Calculate the weight per flow rate (based on the weight per flow rate). Air has a specific heat capacity of 0.24 and a heat loss of 1.2.

[0063] From the formula P1 is the pressure, in MPa; ρ is the air density, taken as 1.19 kg / m³ at room temperature (20℃); v is the flow velocity, in m / s; and Q is the flow rate, in m / s, calculated using the formula Q = s × v, where Q is the flow rate, in s, and s is the cross-sectional area of ​​the pipe. D is the pipe diameter. According to the formula, the pipe diameter is 20mm. The actual flow rate is less than the theoretically calculated maximum air intake flow rate. Therefore, when the pressure is 0.2MPa, the temperature can reach 600℃.

[0064] During use, the operator first fixes the sample 12 onto the adapter sleeve 9. The surface temperature of the blades is measured using a dual-color infrared thermometer 13, and the back temperature is measured using a K-type thermocouple fixed with electric welding machine and high-temperature glue. The air compressor 1 is turned on, the pressure regulating valve is opened, and the pressure is set to 0.1MPa on the computer control system 18. Then, the output temperature of the outlet section of the heater 5 channel is set to 600℃. The actual temperature, flow rate, and pressure are monitored on the computer. The computer software automatically controls and adjusts the system using a fuzzy adaptive PID algorithm to achieve stable, accurate, and rapid control. The computer monitoring system shows that the controlled cooling gas pressure quickly rises to 0.1MPa, the flow rate is 100m3 / h, and the temperature is 600℃. The temperature stabilizes after 10 minutes. The pressure change is <0.001MPa, the flow rate change is <1m3 / h, and the temperature fluctuation is <1℃, achieving the expected control target. When a measured service parameter variation curve is input into the simulation system, the control system can calculate and quickly track the data using a fuzzy adaptive PID algorithm. It saves the experimental results of the surface and back temperatures every second, calculates the surface and back temperature difference, and the temperature variation curves are shown below. Figure 3 As shown. When the simulation experiment ends, heating should be stopped first, and then cold air should be continuously circulated to rapidly cool the heater 5 and the sample 12.

[0065] The experimental process of parameter dynamic simulation by using the above-provided aero-engine guide vane variable parameter dynamic simulation device is as shown in the figure. Figure 2

[0066] The present application has the following advantages over the prior art:

[0067] 1) The control system can calculate and quickly track the changing gas and cooling gas parameters through the fuzzy self-adaptive PID algorithm according to the measured change curve of the service parameters, simulate the dynamic changes of parameters such as turbine inlet temperature, cooling gas temperature, pressure, flow rate, etc. in a typical flight cycle when the aero-engine is in take-off, climb, cruise, flight slow car, reverse thrust, etc.

[0068] 2) The present application can quickly heat the compressed air through a high-power heater, and the supercharger can pressurize to 1-3Mpa and heat to 900K, simulating the high-pressure, high-flow rate, high-temperature cooling gas of the turbine guide vane in service state.

[0069] 3) The gas temperature can reach 2300K, the flow rate can reach 2 Mach, and the flow rate is greater than 1kg / s.

[0070] 4) The adapter sleeve device can be used to clamp different samples.

[0071] 5) The present application can predict and continuously draw known curves through machine learning algorithms, and the control system can perform long-term simulation experiments to test the heat insulation temperature and service time of the vane when it changes dynamically.

[0072] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same or similar parts between each embodiment can be referred to each other.

[0073] The principles and implementation modes of the present application are described by applying specific examples in this paper, and the above embodiment description is only used to help understand the method and core idea of the present application; at the same time, for those skilled in the art, according to the idea of the present application, the specific implementation mode and application range will be changed. In view of the above, the content of the specification should not be understood as a limitation of the present application.​

Claims

1. An aeroengine guide vane variable parameter dynamic simulation device, characterized in that, The system comprises a flame spraying system, an air compressor, a pressure booster, a heater, an adapter sleeve, a monitoring system and a control system. The monitoring system, the air compressor, the pressure booster and the heater are electrically connected with the control system; the air compressor is connected with the pressure booster through a pipeline; the pressure booster is connected with the heater through a pipeline; the heater is connected with the adapter sleeve through a pipeline; the adapter sleeve is connected with a sample; the sample is an aero-engine guide vane or a circular plate or a cylindrical simulation piece. The monitoring system is used for monitoring simulation parameters; the simulation parameters include flame temperature of the flame spraying system, flame speed of the flame spraying system, sample surface temperature, heater bore temperature, heater outlet pipeline temperature, sample end gas temperature, sample back temperature, gas and oxygen inlet and outlet rate, gas and cooling gas flow rate and cooling gas flow pressure; the control system is used for generating simulation parameter dynamic adjustment instructions, determining sample service parameters based on the simulation parameters, predicting service time of the sample based on the simulation parameters, calculating and tracking the simulation parameters through a fuzzy self-adaptive PID algorithm according to a measured service parameter change curve; the air compressor, the pressure booster and the heater are respectively acted on the simulation parameter dynamic adjustment instructions. The air compressor is used for compressing air to provide a gas source for sample service simulation; the pressure booster is used for pressurizing the gas to a pressure under sample service simulation conditions to obtain compressed gas; the heater is used for heating the compressed gas. The monitoring system comprises a first thermocouple, a vortex flowmeter, a second thermocouple, a third thermocouple, a temperature measuring instrument, a particle speed meter and a fourth thermocouple.

2. The variable parameter dynamic simulation device for aero-engine guide vanes according to claim 1, characterized in that, The first thermocouple and the vortex flowmeter are sequentially arranged on a connecting pipeline of the heater and the adapter sleeve; the second thermocouple and the third thermocouple are arranged on the sample; the fourth thermocouple is arranged in a bore of the heater. The first thermocouple, the vortex flowmeter, the second thermocouple, the third thermocouple, the temperature measuring instrument, the fourth thermocouple and the particle speed meter are electrically connected with the control system. The first thermocouple is used for measuring heater outlet pipeline temperature; the vortex flowmeter is used for measuring cooling gas flow rate; the second thermocouple is used for measuring sample back temperature; the third thermocouple is used for measuring sample end gas temperature; the fourth thermocouple is used for measuring the heater bore temperature; the temperature measuring instrument is used for measuring sample surface temperature; the particle speed meter is used for measuring flame temperature and flame speed of the flame spraying system; a sensor in the flame spraying system can monitor gas and oxygen inlet and outlet rate in real time; an adjusting valve of the pressure booster is used for adjusting cooling gas flow pressure. The flame spraying system comprises a spray gun and a spray gun holding device.

3. The variable parameter dynamic simulation device for aero-engine guide vanes according to claim 1, characterized in that, The spray gun is arranged on the spray gun holding device; the spray gun is used for providing a gas heat source in the sample service simulation process. The spray gun holding device adopts any one of a roller type, a fixed type and a mechanical arm type to clamp the spray gun.

4. The variable parameter dynamic simulation device for aeroengine guide vanes according to claim 3, characterized in that, Further comprising:

5. The variable parameter dynamic simulation device for aeroengine guide vanes according to claim 1, characterized in that, a heat preservation system. ​ The heat preservation system is arranged on the heater, and the heat preservation system wraps the input and output pipelines of the heater.

6. The variable parameter dynamic simulation device for aero-engine guide vanes according to claim 5, characterized in that, The heat preservation system is aluminum silicate heat preservation cotton or aluminum silicate ceramic fiber blanket.

7. The variable parameter dynamic simulation device for aero-engine guide vanes according to claim 1, characterized in that, The maximum pressure boosting range of the pressure booster is 1-3 Mpa.

8. The variable parameter dynamic simulation device for a gas turbine engine guide vane of claim 1, wherein, The maximum heating temperature of the heater is 900 K; the output gas temperature of the flame spraying system is at most 2300 K, and the flow rate is at most 2 Mach.

9. The variable parameter dynamic simulation device for a gas turbine engine guide vane of claim 1, wherein, The control system comprises a computer control system and a parameter display and control cabinet. The monitoring system, the air compressor, the pressure booster, the heater and the computer control system are respectively electrically connected with the parameter display and control cabinet.

10. A method of variable parameter dynamic simulation of a gas turbine engine guide vane, the method comprising: The method is applied to the variable parameter dynamic simulation device of the guide vane of the aero-engine as claimed in any one of claims 1-9, and the method comprises: Obtaining simulation parameters of the guide vane of the aero-engine; Simulating operation parameters of the aero-engine at different operations in a typical flight cycle based on the simulation parameters, wherein the operation parameters comprise turbine inlet temperature, cooling air temperature, pressure and flow rate; Obtaining a historical service parameter change curve; Realizing parameter calculation and simulation tracking of the guide vane of the aero-engine based on the historical service parameter change curve by using a fuzzy self-adaptive PID algorithm; Testing the temperature difference before and after the guide vane of the aero-engine and determining the heat insulation temperature of the guide vane of the aero-engine based on parameters collected in the service simulation process; Predicting the service time of the guide vane of the aero-engine based on the historical service parameter change curve by using a machine learning algorithm.

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