Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade IV - Comparison of Experimental and Analytical Aerodynamic Results for Blade With 12 Rows of 0.076-Centimeter- (0.030-in.-) Diameter Holes Having Stream wise Ejection Angles

摘要

Previously published, experimentally determined changes in aerodynamic efficiency due to coolant ejection from a film-cooled turbine stator blade having 12 spanwise rows of coolant holes are compared with efficiency changes predicted by two published analytical methods. One of the methods was used as published;the other was modified. The experimental results were from tests in a two-dimensional cascade with both the coolant flow and the primary flow at near-ambient temperatures. The tests included coolant discharge from each of the single rows and from various combinations of rows, including full-film discharge.