Research Of Aerodynamics On Vane Segment And Support Segment Of A Ram-rotor Test System

In order to improve the performance of gas turbine,it is inevitable to develop high pressure ratio and high efficiency supersonic compression.As a neoteric rotor of the supersonic compression,the ram-rotor has many advantages such as high pressure ratio,lighter weight,and smaller volume.This paper is based on the research of the ram-rotor test system by research group,and a further research on the vane segment and support segment of the ram-rotor test system is carried out.It is hoped that the result of this research can provide theoretical basis for the experiment in future.Vane segment was firstly researched in this paper.The vane opening,bottom clearance and axial distance of the vane and the ram-rotor were studied respectively.Results show that the reduction variation of the vane opening makes the flow has a better accelerating ability in a smaller flow area.And then it is benefit to the starting performance of the ram-rotor.The increase of the vane bottom clearance aggravates the leakage at the vane bottom,leading to the migration of high entropy region along the pitch direction.Meanwhile,the flow angle at the outlet of the vane would be more approximate to the design value,which makes the coming flow matching the ram-rotor better.The vane bottom clearance has no effect on the efficiency of the ram-rotor,but it influences the pressure ratio of the ram-rotor.When the axial distance of the vane segment and the ram-rotor increases,the outlet Mach number of the vane segment gets smaller.Meanwhile,the uniformity of the flow parameters alone the circle direction is improved,and the pressure ratio and efficiency of the ram-rotor diminishes and increases respectively.Sequentially,the support segment of the ram-rotor test system was researched.The mounting angle and splitter blades were mainly considered.It can be concluded that when the mounting angle increases,the flow separation in the support segment was restrained,resulting in a lower total pressure loss.When the mounting angle is 20°,the flow density at the inlet and outlet of the support segment is the highest,that means the airflow can flow out of the support segment smooth.When the support segment was mounted 1 splitter blade,the total pressure of the support segment was the lowest.When the support segment was mounted 2 splitter blades,the flow area decreased due to the number of blades increased,leading to a blocking in the support segment and the total pressure loss varied higher.