The present study investigates local film cooling effectiveness values and heat/mass transfer coefficients around a conical-shaped film cooling hole with compound angle orientations. Three types of film cooling hole geometry are compared in this study; one is cylindrical hole geometry with constant cross section and the others are shaped hole geometries with conically-enlarged hole exits. The shaped holes have cylindrical passage sections at the hole inlet region to obtain a certain pressure drop through the holes. One shaped hole expands 40 in all directions from the middle of hole to the exit. The other shaped hole has the tilted center-line by 4° between the conical and metering holes and is enlarged by 8° to downstream side. The hole area ratios of the exit to the inlet are 2.55 and 2.48, respectively. The compound-angled film cooling jet is ejected through the single holes, which are inclined at 30 0 to the surface based on the metering hole and are rotatable in lateral direction from 00 to 90°. The blowing rates ale changed from 0.5 to 2.0. The naphthalene sublimation technique is used to determine local heat/mass transfer coefficients and local adiabatic/impermeable wall film cooling effectiveness around the injection hole. The results indicate that the injected jet protects the surface effectively with low blowing rates and spreads more widely with the compound angle injections than the axial injection. For the shaped hole enlarged by 4° in all directions, the penetration of jet is reduced and higher cooling performance is obtained even at relatively high blowing rates because the increased hole exit area reduces hole exit velocity. Furthermore, the film cooling effectiveness is fairly uniform near the hole due to the wide lateral spreading of coolant with the expanded cooling hole exit.
|Title of host publication||Heat Transfer; Electric Power; Industrial and Cogeneration|
|Publisher||American Society of Mechanical Engineers (ASME)|
|Publication status||Published - 1999|
|Event||ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1999 - Indianapolis, United States|
Duration: 1999 Jun 7 → 1999 Jun 10
|Name||Proceedings of the ASME Turbo Expo|
|Other||ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1999|
|Period||99/6/7 → 99/6/10|
Bibliographical notePublisher Copyright:
Copyright © 1999 by ASME.
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