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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
Heat Transfer Research
Импакт фактор: 0.404 5-летний Импакт фактор: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN Печать: 1064-2285
ISSN Онлайн: 2162-6561

Выпуски:
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Heat Transfer Research

DOI: 10.1615/HeatTransRes.v41.i8.50
pages 849-865

Trailing Edge Film Cooling of Gas Turbine Airfoils — Effects of Ejection Lip Geometry on Film Cooling Effectiveness and Heat Transfer

Tim Horbach
Institut fuer Thermische Stroemungsmaschinen (ITS), Karlsruhe Institute of Technology (KIT), 76131 Karlsruhe, Germany
Achmed Schulz
Institut fuer Thermische Stroemungsmaschinen (ITS), Karlsruhe Institute of Technology (KIT), 76131 Karlsruhe, Germany
Hans-Jorg Bauer
Institut fuer Thermische Stroemungsmaschinen (ITS), Karlsruhe Institute of Technology (KIT), 76131 Karlsruhe, Germany

Краткое описание

The present paper concentrates on trailing edge film cooling of modern high-pressure turbine blades using cooling ejection through planar slots with a pressure side cutback. The experimental test section consists of a generic scaled-up trailing edge model. The effects of different geometric configurations on the structure and the performance of the cooling film are investigated in terms of film cooling effectiveness, heat transfer coefficients, and discharge behavior. The interaction between an internal turbulator array of ribs with the ejection slot lip is of major interest. Different designs of the cooling ejection lip are applied. Four different ratios of lip thickness to ejection slot height (t/H = 0.2, 0.5, 1.0, 1.5) are investigated, as well as three different lip contours representing typical manufacturing imperfections and wear. The experiments are performed at engine-realistic density ratios. The blowing ratios are varied between 0.2 < M < 1.25. The results show a strong dependency on ejection lip thickness and only marginal changes when the lip shape is varied.


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