B-9 単動翼列多段チップタービン駆動ファン(第二報)(空力III・ガスタービンシステム,一般講演)

概要

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Numerical simulation of the single rotor blade row with multistage tip turbine by using the CFD code "UPACS" is conducted to investigate unsteady flow inside the tip turbine. From detailed analyses of the result of the numerical simulation, an efficiency of the turbine rotor blades is dropped at boarders where the turbine rotor blade proceeds into from low-pressure to high-pressure stage. At the borders of the stages, inverse pressure gradient between suction surface and pressure surface of the rotor blade is observed. Large amount of mass flow leaks from a blade row to the following blade row through a tip clearance at the boarder, since the inverse pressure gradient and static pressure rise at the exit of the rotor blade accelerate the flow. The leakage of mass flow causes secondary flow and drastically lower an adiabatic efficiency of the turbine blade.
社団法人日本ガスタービン学会の論文
2004-10-01