Performance Evaluations for the Partial-Admission Type Turbine System

부분흡입노즐방식의 터빈시스템에 대한 성능 평가

3-D compressible flow analysis was conducted by using mixing plane method for turbine system which is consisted of partial admission nozzle and rotor. Computational results are shown oblique shock wave in blade leading and trailing edge and also shown flow separation along suction surface of blade due to abrupt blade curvature. But computational results are well agree with 1-D calculation results and experimental data.