Effect of Inlet Flow Angle on Gas Turbine Blade Tip Film Cooling

摘要: The influence of incidence angle on film-cooling effectiveness is studied for a cutback squealer blade tip. Three angles are investigated ―0 deg at design condition and ±5 off-design conditions. Based mass transfer analogy, the measured with pressure sensitive paint techniques. distribution side near tip region, cavity floor, rim presented three varying blowing ratios. average ratio controlled to be 0.5, 1.0, 1.5, 2.0. One row shaped holes provided along just below tip; two rows cylindrical arranged in such way that one offset suction profile other camber line. wall cut trailing edge allow accumulated coolant escape cool edge. internal coolant-supply passages tipped modeled similar those GE-E 3 rotor blade. Test done five-blade linear cascade blow-down facility gap clearance 1.5% span. Mach number turbulence intensity level inlet were 0.23 9.7%, respectively. It observed affects jet direction region also altered. peak laterally averaged shifted up-stream or downstream depending angle. film cooling inside can increase by 25% positive However, general, overall area-averaged not significantly changed range study.