Experiment Of Integrated Strut OGV Configuration Plane Cascade

There is a circle of outlet guide vanes at the bypass duct of a high bypass ratio turbofan engine,which can rectify and turn the air flow from the outlet of the fan into axial.Near the outlet of by-pass duct,there are also some struts to support the bypass duct and the casing.The differences of the shapes and sizes between the two parts have a greater impact on the flow of the bypass duct.Generally,both of them distribute along the axis of the duct.Now,the strut and OGV are distributed side by side at the same axis,which is called integrated strut OGV configuration.This configuration can effectively reducing the size of the engine,the mass of the engine,and has a good effect of improving the aerodynamic performance and reducing the noise.In order to study the full operating performance of the integrated strut OGV cascade at different blade heights,the flow field numerical calculation of the branch-plate fused OGV cascade at 20%,50% and 80% blade heights was carried out,and the plane cascade blowing test was carried out for 50% cascade.The experimental results were compared with the calculated results.The full text is mainly divided into three parts:Introduced the plane cascade test: introduce the test bench and test equipment in detail;analyze the feasibility of the test by numerical calculation method,study the influence of flow periodicity,scale model,two-dimensional and three-dimensional flow field structure on cascade performance;study the measurement method of cascade aerodynamic performance parameters.The experiment was carried out by 50% cascade at-6°,0°and 10°incidence with 0.4 inlet Ma and 0°incidence with 0.7 inlet Ma.After comparing the results with calculation.It was found that the experiment results were in good agreement with those of calculation.The wake of cascade increased with the increase or decrease of incidence or the increase of inlet Mach number.The OGV outlet angle of the whole cascade basically distributed around 0 degrees.When the incidence or inlet Mach number increases,the flow loss-turn at the pressure side of strut.The position of maximum load of the blade moves forward with the increase of incidence.Numerical calculated the 20%,50% and 80% cascade at different incidences and different inlet Mach numbers by NUMECA software.After analyzing the results,it was found that the total pressure loss of cascade at zero incidence is relatively small.With the increase or decrease of incidence,the boundary layer on the blade surface separates and the loss increases gradually,and the loss increases more obviously at positive incidence.With the increase of Mach number,the loss of cascade is also increased.At large negative incidence,Shock waves are generated in cascade.The flow-path is blocked and the incidence range of cascade decreases gradually.When inlet Mach number increases to about 0.8,the cascade can only work at positive incidence.