Investigation For Experimental Method Of Supersonic Compressor Cascade

In order to obtain real pneumatic parameters and performance in the actual flow field ofcompressor cascade, correct and effective cascade test had played an important role incompressor and turbine type design method in new leaves and theoretical exploration. On theone hand, the cascade test verified the new design theory of blades, on the other hand detailedtest data had been provided as the reference of checking and correcting design model.In this paper, some cascade test rigs had been designed for verifying a zero stagecompressor cascade pneumatic parameters and performance. According to different structures,flow characteristics and aerodynamic parameters of zero stage compressor cascades, an annualstator cascade test and a plane rotor cascade test had been designed respectively.First of all, the original compressor had been modeled and narrowed according to theprinciple of gas turbine similarity criterion and the experimental condition. The influence offlow condition with different modeling ratios had been discussed. Secondly, in the investigationof stator annual cascade experimental method, the influence of cascade performance withdifferent nozzle structure forms had been discussed intensively. In the investigation of rotorplane cascade experimental method, the influence of Mach number and flow quality on thenozzle exit with different nozzle expansion angles and different boundary layer correctionangles had been discussed intensively. At the same time, the influence of cascade periodicityand aerodynamic parameters with different flow organization forms around the plane cascadeshad been detailed analyzed. In this part, transonic wall, boundary layer suction structure andsuction pressure had been discussed for finding the best cascade periodicity. Finally, in view ofthe two cascade test different data acquisition requirements, the data acquisition system andsome visual sampling methods had been designed respectively.The pneumatic and structure design of stator annual cascade test rig and rotor planecascade test rig had been instituted. Some structure and aerodynamic factor about influence ofcascade performance had been discussed. Test scheme could not only meet the testrequirements, and also achieve the best use of resources.