超音速軸流圧縮機の動翼内の流れに関する研究(第4報)

Shock-in-rotor型動翼の設計上の2, 3の問題

抄録

From the point of view of designing an actual shock-in-rotor type rotor according to the radial equilibrium consideration, a few problems on the blade passage and its thickness are mainly investigated in connection with the flows at the inlet, before and behind normal shock, and at the outlet. Cases having the uniform inlet flow with no swirl component and the reasonable value of relative Mach number are treated in this report.
The results show the possibility of designing a blade for practical use, whose supersonic portion can satisfy the starting condition for a supersonic diffuser at every radial station, if the turning angles are appropriately taken along the radius. But the blade has a tendency to take a subsonic portion having an adverse turning or the flow acceleration in relation to the magnitude of the energy addition in the rotor blade.