입사각이 터빈 동익 팁누설유동 영역에서의 압력손실에 미치는 영향

Abstract

The effect of incidence angle on the three-dimensional flow and aerodynamic loss in the tip leakage flow region downstream of a turbine rotor cascade has been investigated for two tip gap-to-chord ratios of h/c＝0.0% (no tip gap) and 2.0%. The incidence angle is changed to be i＝-10°, 0°, and 5°. The results show that for i＝5°, secondary flows including the passage vortex are intensified noticeably, and there is a strong interaction between the passage and tip leakage vortices. For i＝-10°, however, the passage vortex is weakened significantly, so that there exists only a strong leakage-jet-like secondary flows near the casing wall. For h/c＝0.0% and 2.0%, aerodynamic loss tends to increase with increasing i from -10° to 5°. A small increment of i in its positive incidence range results in a remarkable aerodynamic loss increase, while increasing i in the negative incidence range leads to a small change in the aerodynamic loss generation.