Research On Control Law And Overall Performance Design Of High Bypass Ratio Turbofan Engine Based On GasTurb Software

The high bypass ratio turbofan engine has a wide range of external conditions and working parameters during the working process,and has high requirements on stability and component strength,so that it can be stable and reliable under any environmental conditions and working conditions.Ground operation,exerting its performance benefits,and research on engine control laws are extremely important.The overall performance design is not only an important part of the overall engine design but also an important part of the aero engine design.Therefore,it is especially important to study the overall performance design of the engine.At present,domestic research on the overall performance of civil high bypass ratio turbofan engines is less and in the preliminary research stage.In this paper,the overall performance design of the high bypass ratio turbofan engine is studied.The completed work is mainly divided into the following four parts: The first part introduces the control law of the aeroengine,analyzes the engine’s use limit,stabilizes the working state and affects the stability work.The state factor,as well as the choice of controlled parameters,control parameters and engine steady-state control law,and give three control laws of the engine under steady state,namely low-pressure rotor speed n₁=constant,high-pressure rotor speed n₂=constant,and The exit temperature of the combustion chamber T₄^*=constant.In the second part,the application of GasTurb performance analysis software to the geometrically non-adjustable twin-shaft turbojet engine is tested for its practicality in engine performance analysis.The velocity and height characteristics under different regulation laws are analyzed.The results show that the application of GasTurb software in the performance analysis of aeroengine is practical.In the third part,the GasTurb software adopts the same control law as the two-axis turbojet engine,and also carries out the height characteristics,speed characteristics and temperature characteristics of the engine under different regulation rules of the separate exhaust high bypass ratio turbofan engine.Analyze and summarize the advantages and disadvantages of different control parameters on engine performance.The results show that the engine can obtain relatively good height characteristics when the low-pressure rotor speed is kept constant.In the fourth part,the CFM56-7B26 civil high bypass ratio turbofan engine is taken as the research object.Firstly,the engine design characteristics,design point selection,cycle parameter selection,and design point parameters are determined.Then the sensitivity of the engine cycle parameters and the influence of the main cycle parameters on the thrust and fuel consumption rate are discussed.The results are consistent with the engine performance.Finally,this engine is taken as an example.According to the overall design requirements of the engine,the flow path size and the high and low pressure rotor speeds of the main components of the three engines of the fan,the compressor,and the turbine are sequentially determined.The calculation results are combined with the actual measured flow path size of each component of the same model,and the results are satisfactory.