Numerical Investigation On The Influence Of Non-Axisymmertic Stator On Compressor With Distorted Inlet

As the core component of modern aero-engine,the stability and load capacity of compressor have an important effect on the efficiency and aerodynamic performance of the engine.However,in practical application,it is inevitable that the turbo-machine should work under the condition of non-uniform inlet at present,in which the distortion of total pressure of inlet is particularly common.When the total pressure distortion attenuates through the moving blade,the inlet air flow angle of the stator blade is uneven and the aerodynamic stability of compressor decrease due to the serious separation in the stator blade angle region.Scholars have done a lot of research on the problem of inlet distortion of compressor,and put forward the methods of non-axisymmetric structure modeling,curved blade and others to reduce the loss of stator blade angle region.However,the proposed non-axisymmetric modeling design is mainly aimed at the end wall,and the application of the curved blade is mostly used for the whole blade.Therefore,the proposed concept of non-axisymmetric stator blade,that is,the partly modified modeling of compressor stator blade,put forward a new way to improve the compressor performance under the condition of distortion.In this paper,a new type of non-axisymmetric compressor is obtained by modifying the stator blade which is influenced by distortion so that the angle region separation is serious.The effect of compressor performance on non-axisymmetric stator blade was studied by numerical calculation of two types of compressor under uniform inlet and distorted inlet respectively.The numerical results show:the performance of the non-axisymmetric compressor is poor under the uniform inlet condition and is improved under the distorted inlet condition compared with the prototype.It is shown that the propositon and application of non-axisymmetric stator blade has a positive effect on improving the compressor performance under distorted conditions.On the basis of non-axisymmetric compressor,the influence of the range of non-axisymmetric stator blade on the performance of compressor is studied by changing the numbers of modified stator blade,and a more perfect design method of non-axisymmetric stator blade is expected.The numerical results show:The reduce of non-axisymmetric range.leads to lower compressor performance,while increase the number of non-axisymmetric stators which are changed,the compressor performance has been improved obviously.That declares within certain limits,improving the non-axisymmetric range has a positive effect on improving compressor performance.