Heat Transfer Coefficient and Film-Cooling Effectiveness on a Gas Turbine Blade Tip

摘要: The detailed distributions of heat transfer coefficient and film cooling effectiveness on a gas turbine blade tip were measured using hue detection based transient liquid crystal technique. Tests performed five-bladed linear cascade with blow down facility. was 2-dimensional model first stage rotor profile the GE-E3 aircraft engine blade. Reynolds number exit velocity axial chord length 1.1 × 106 total turning angle 97.7°. overall pressure ratio 1.32 inlet Mach 0.25 0.59, respectively. turbulence intensity level at 9.7%. equipped single row holes both portion along camber line near region pressure-side. All measurements made three different gap clearances 1%, 1.5%, 2.5% span blowing ratios 0.5, 1.0, 2.0. Results showed that, in general, increased increasing clearance. As increased, decreased, while increased. also that adding pressure-side coolant injection would further decrease but increase effectiveness.Copyright © 2002 by ASME