Film cooling performance for injection through discrete holes in the endwall of a turbine blade is investigated. The effectiveness is measured at sixty locations in the region covered by injection. Three nominal blowing rates, two density ratios, and two approaching flow Reynolds numbers are examined. Analysis of the data reveals that even sixty locations are insufficient for the determination of the field of film cooling effectiveness with its strong local variations. Visualization of the traces of the coolant jets on the endwall surface, using ammonium-diazo-paper, provides useful qualitative information for the interpretation of the measurements, revealing the paths and interaction of the jets which change with blowing rate and density ratio.
|Original language||English (US)|
|Title of host publication||Heat Transfer; Electric Power; Industrial and Cogeneration|
|Publisher||American Society of Mechanical Engineers (ASME)|
|State||Published - 1994|
|Event||ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, GT 1994 - The Hague, Netherlands|
Duration: Jun 13 1994 → Jun 16 1994
|Name||Proceedings of the ASME Turbo Expo|
|Other||ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition, GT 1994|
|Period||6/13/94 → 6/16/94|
Bibliographical notePublisher Copyright:
© 1994 by ASME.