Investigation On The Application Of Tubercle Leading-edge In High-loaded Stator Blade

With the development of the aviation industry,designing aero-engines with high thrust-to-weight ratio and high efficiency is a manifestation of the strength of a country's national defense science and technology.As a core component of aero-engine,the engine pressure ratio and efficiency of the compressor directly affect the design requirements of the aero-engine.The single stage load of the compressor gradually increases,which leads to the gradual increase of the stator blade angle,leading to the complexity of the flow field in the passage and affects the aerodynamic stability of the compressor.It is harder to improve compressor performance with traditional design methods,so we find a new way for the designing of the compressor blade and it is based on the bionics principle,which named by tubercle leading-edge blade.In this study,we tried to introduce the leading edge blade into the high-load compressor stator blades to research the principle of action.At the same time we study the impact on the aerodynamic stability and influence of the compressor stability marlin.This study includes the following sections:(1)Numerical simulation of tubercle leading-edge blade within the entire blade height range on the effect of aerodynamic stability of cascades with large camber.The effects of different camber angles,design parameters of tubercle leading-edge blade and load on the flow characteristics of the cascades and the results show: in the unsteady operating range of the stator cascade(with large flow separation),tubercle leading-edge blade can significantly reduce the total pressure loss of the cascade and enhance the unsteady stall aerodynamic performance of cascade.The amplitude of the tubercle Am has a significant effect on the performance of the cascade,while the number of the tubercles has a relatively small effect.The effect of tubercle leading-edge on performance is due to the twin swirl structure at the leading-edge which caused a radial migration of the leading edge airflow and thus improving the flow field structure and improving the cascade performance.(2)Numerical simulation of tubercle leading-edge blade within part of the blade height range on the effect of aerodynamic stability of cascades with large camber and the results show: the distribution of the tubercle leading-edge at the part of the blade also enhances the aerodynamic performance of the cascade.Cascades performance enhancements exist only in areas where there is distribution of the tubercle,and there is no effect in the area where there is no tubercle.The study found that the distribution of tubercle in the 80% blade high range can make the best performance cascade.(3)Numerical simulation of tubercle leading-edge blade on performance and stability of the first stage of a four-stage high pressure compressor and the results show: the tubercle leading-edge blade can increase compressor efficiency and total pressure ratio under most operating conditions.The tubercle leading-edge can significantly improve the flow field at the end wall of the compressor,reduce the range of separation of the corner and widen the stall margin of the compressor.In summary,tubercle leading-edge blade can be applied to high-load large turning angle compressor stator,which can not only enhance the performance of the compressor,but also widen the stall margin of the compressor.