Investigation Of Transonic Compressor Rotor Performance Affected By The Circumferential Casing Groove With Suction

High-pressure ratio and high-efficiency of compressor are always required in modern high-performance aircraft design,on the basis of the traditional compressor,the new type of blade has been studied gradually.The emergence of supersonic and transonic compressors makes it’s the boost capability improved Obviously.However,compared with the conventional subsonic compressor,the existence of shock waves in the supersonic and transonic compressors makes the internal flow more complicated and more unstable.Complex flow structure in Transonic compressor,such as rotor shock,leakage vortex interaction,the radial separation vortex et,leads compressor stalled when the environment become deteriorated,so controlling the transonic compressor leakage flow and shock structure has long-term significance.In this paper,a modified transonic compressor rotor as the research object,mainly focuses on the mechanism of the transonic compressor flow and aerodynamic performance witch is improved by casing circumferential grooves.Using ROTOR37 to verify the accuracy and feasibility of CFD method for it’s complete experimental data.And exploring the effect of casing groove,vacuum gas collecting chamber and combinations of slots on flow performance of transonic compressor.Firstly exploring mechanism of transonic aerodynamic performance witch is influenced by the single case of circumferential groove,by comparing the total performance,Maher number and the surface load parameters of prototype and modification,founding that by pulling away part of the leakage flow,single case of circumferential groove can control the intensity of shock wave,and then improve the transonic compressor internal flow.Secondly,the vacuum cavity is added outside the suction slot to make the numerical simulation process closer to the actual engineering results.By contrast with the efficiency,pressure ratio,Maher number and other aerodynamic parameter of modification and prototype of transonic compressor rotor,found that suction flow of casing circumferential groove suction with cavity can still achieve reasonable results while the suction flow is 2%of the mainstream flow in prototype near stall condition and improve the transonic compressor aerodynamic performance obviously,show that flow in casing groove with the cavity become more smoothly,so that the suction effect is better.Finally,after the vacuum chamber was added,the combined suction casing circumferential groove was studied.Through comparing suction effect of three kinds of scheme in two kinds of suction flow,found the suction effect worse than single suction slot while the suction flow rate is low,but when the suction flow rate is large enough the suction effect is obviously improved,the aerodynamic performance better than single suction slot.