Bong-Gun Shin and Kui-Soon Kim/Jin-Han Kim
International Journal of Aeronautical and Space Sicences, vol. 6, no. 1, pp.1-7, 2005

Abstract : The inlet boundary condition of computations about the supersonic turbine flow is commonly applied as far-field inlet boundary condition with specified velocity. However, the inflow condition of supersonic turbine is sometimes affected by the shocks or expansion waves propagated from leading edges of blade. These shocks and expansion waves alter the inlet boundary condition. In this case, the inlet boundary condition can not be specified Therefore, in this paper, numerical analyses for three different inlet conditions - fa-field inlet boundary condition, inlet boundary condition with a linear nozzle and inlet boundary condition with a converging-diverging nozzle - have been performed and compared with experimental results to solve the problem. It is found that the inlet condition with a linear nozzle or a converging-diverging nozzle can prevent changing of inlet boundary condition, and thus predict more accurately the supersonic flow within turbine cascade than a far-field inlet boundary condition does.

Keyword : Supersonic Turbine, Fine Turbo, Inlet Boundary Condition with a Nozzle, Far-Field Inlet Boundary Condition, Partial Admission