Research On Influence Of Boundary Layer Suction On Compressor Aerodynamic Performance Under Supersonic Flow Condition

As one of the core components of aero-engine,compressor can effectively reduce the number of engine stages and increase the thrust-to-weight ratio by increasing its single-stage pressure ratio.One of the effective ways to improve the single stage pressure ratio is to increase the blade tip rim speed,which will lead to flow supersonic and cause shock waves in the channel.The shock wave can increase the static pressure on the one hand and increase the flow loss on the other.This characteristic also makes the shock wave one of the core researches of supersonic compressors.Therefore,this paper takes a typical supersonic blade as the research object,analyzes the influence of aerodynamic parameters,deeply studies the effect of suction method on the shock wave structure and aerodynamic parameters of the cascade flow channel,and analyzes the shock loss structure.In this paper,the numerical method and grid independence are verified by the supersonic plane cascade DLR-PAV-1.5.The simulation results are basically consistent with the experimental results,which proves the accuracy of the numerical method.By studying the aerodynamic parameters affecting the flow field,the influence of the parameter change on the shock structure and aerodynamic performance of the flow field is analyzed.The shock wave structure of the cascade flow field under different working conditions is analyzed and summarized.The suction position and suction volume of PAV-1.5 cascade are simulated,and a better suction scheme is obtained.The suction position of the scheme is at the axial chord length of 0.65 from the leading edge of the cascade,the suction volume is 0.204% of the inlet flow,and its total pressure loss coefficient is reduced by 2.65% compared with the design condition.By comparing the different suction angles,it is concluded that under the same suction pressure,the suction flow rate of the vertical suction scheme is 10.3% and 19.1% higher than that of the flow suction scheme and the countercurrent suction scheme respectively.By comparing the structure of three different suction holes,it is found that the suction effect of the inverted angle suction structure(SS3 scheme)is better.Under the same suction pressure,the suction capacity of the suction structure is 22% higher than that of the vertical suction structure(SS1 scheme).The results show that the dual slot suction scheme can effectively improve the original single slot suction scheme,and the total pressure loss coefficient of the scheme is reduced by 3.37% compared with the design conditions.The total pressure loss factor of the program was reduced by 3.37% compared with the design condition.Through the shock loss model analysis method,it was found that the suction at the suction position of 0.65 can significantly reduce the shock loss of the channel,while the effect at the 0.75 suction position is not good.The loss of blade shape decreases with the backward movement of the suction position,and the loss caused by the detachment of the bow shock is not substantially affected by the amount of suction.