The Design And Research Of Supersonic Low Reaction Compressor Rotor

The lifting of a compressor's single stage load can improve the thrust-weight ratio of an aeroengine.The lifting of a single stage load is generally achieved by increasing the torsional speed or increasing the blade tip rim speed,which will lead to supersonic compressors.There are shock waves in the flow field of supersonic compressors.On the one hand,shock waves make the flow obtain static pressure boost to improve the pressure ratio;on the other hand,shock waves will directly cause shock loss.Shock waves have become one of the main research directions of supersonic compressors.In this paper,the head moving blade of a compressor with low reaction degree is taken as the research object,and the influence of the modified blade on the aerodynamic performance and shock wave structure of flow field is studied by using the method of suction surface concave modeling.This paper first introduces the technology development status of supersonic and transonic compressors.Based on the discussion and exploration of previous scholars,it is found that appropriate blade modifications can effectively reduce the loss caused by shock waves.Based on this idea,many modification schemes have been proposed,among which the concave design of suction surface is more feasible and effective.Based on this idea,this paper first designs a moving vane for the head of a compressor that is 8.1% higher than the conventional tangent velocity,and explores the changes of geometric parameters and flow field structure of the two kinds of moving blades before and after the increase of rotating speed.The results show that the loss increases with the increase of pressure ratio as the rotating speed increases.On the one hand,the shock loss increases;on the other hand,the boundary layer after the flow through the shock wave thickens,the separation scale of suction surface increases,and the blade stability and stall margin decrease.In this paper,under the high speed of the suction side of the moving blade using a concave characteristics within the large turning Angle of leaf shape modelling method,high and 75% to 100% / high profile within the suction side of the first half of concave design,in the second part USES the arc overlay thickness distribution in modelling methods,explore the suction surface concave length and depth of three-dimensional blade aerodynamic performance and the influence of the flow field of shock wave structure.The results show that the introduction of the concave design of suction surface can indeed affect the flow field,and the different length and depth of the concave have different effects on the performance of the blade,which is closely related to the characteristics of the blade and the position of shock wave.The intensity of shock wave and boundary layer loss is the focus of this article explores the direction,through the blades of different inner concave scheme were analyzed,found in optimal concave depth,change the length of the concave,with the decrease of the concave length,leaf loss increased,lower efficiency and compression ratio is reduced,this is because the introduction of concave make wavefront Mach number increases,the mainstream flow area is complex,loss increase,also can see separation suction surface damage is serious,the tip leakage flow also lead to loss increases,the two factors is led to increasing blade loss,the main cause of separation is aggravating.