High Load Compressor Stator Blade Flow Separation Control Method

At present,we need to further reduce the quality of the engine by facing the increasing development state of the engine thrust-weight ratio and how to reduce the "weight penalty" of the power plant in the non-working state in the TBCC study.In the current research results,the single stage compressure ratio of traditional subsonic compressor and transonic compressor have been difficult to jump in order of magnitude.So based on this background,we choose supersonic compressor as research object,compared to traditional subsonic and transonic blade,supersonic cascade has the advantages high single stage pressure ratio and low weight.At the same time,supersonic blade has the properties of complicated flow.The large area of flow separation pull down the overall efficiency of the supersonic blade,so it is not used in real industrial field.This is an exploratory paper,this paper compared the supersonic inlet which has been studied by research group for a long time with supersonic blade.The research method of the supersonic inlet was used in the supersonic blade.At the same time,in combination with the concept of high load adsorption of subsonic and transonic blade.The flow control method is proposed to suppress the flow separation in the supersonic blade to improve the efficiency of supersonic blade.In this paper,firstly theoretical analysis was carried out and then numerical calculation was used.Finally the numerical results were used to design the experiment.The research was finished by flow cont rol experiment.Firstly,the feasibility of shock boosting is studied theoretically.The past methods of shock boosting were summarized and analyzed.The suitable research object for this article was chosed.The two-dimensional flow of cascade was studied inc luding the flow shock structure of the cascade.And the flow in supersonic cascade and supersonic inlet was compared,the similarities and differences were founed.The starting problem of the supersonic cascade was compared with starting problem of inlet.The crit ical operation and supersonic operation of the supersonic inlet both apply to the supersonic cascade.However,the subcrit ical opeartion of supersonic inlet don't apply to supersonic cascade.At the same time,the unsteady operation condit ions of the cascade starting was analyzed by using DES numerical simulation.The anti-pressure prequel characteristics of cascade was also analyzed by using DES numerical simualt ion.The further study of flow characteristics was carried out by using three-dimensional model.The uniform degree of the flow affect the start of the cascade.The problem was analyzed by combinating numerical results.The anti-pressure prequel characteristics of three-dimensional model was analysed and compared with the numerical results of two-dimensional.We found that the back pressure resistance ability of cascade decline with the effect of three-dimensional.The flow separation of the cascade under the three-dimensional effect and the structural evolution of the angular vortices are studied.O n this basis,the qualitative study of the suction and blowing is carried out.And then the flow control combined with the above.The flow control strategy after using suction and blowing was analyzed.Furthermore,the effects of geometric posit ion,angle and suction pressure ratio on the efficiency of suction / blowing flow control were analyzed in this paper.And the change of the structure of shaking wave system in the cascade after the flow control was adopted.At the same time,the back pressure resistance ability was compared under the suction flow control.It was found that different suction posit ions effect the structure of shock wave in flow field.It was found that due to the difference of suction angle,the shock wave may be moved forwa rd when the suction position is not far away after the shock wave.Finally,on the basis of a large number of numerical simulations,this paper designs and constructs the experimental system to complete the experimental study on the separation and flow control of supersonic cascade flow.The flow separation(10 °,20 °,and 30 ° simulated working conditions at different blocking angles)of through-flow state of cascade and pressure throttle working condition was mainly studied.And the shape of the flow separation after flow control are simulated...