Investigation of a novel discrete slot film cooling scheme

Karim M. Shalash, Lamyaa A. El-Gabry, Mohamed M.Abo El-Azm

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations


The future of the gas turbine industry is strongly relying on the development of new efficient cooling schemes. Film cooling is one popular and reliable cooling technique, one way to increase the film cooling effectiveness is through the use of shaped holes. In this paper two proposed shaped holes are being studied and compared thoroughly against the conventional round hole film cooling. The two proposed holes are based on the theoretically perfect continuous slot film cooling, however, these slots are not continuous, and preserves the solid surface to the total blade surface ratio. The first design to be studied is the Rectangular Divergent Slot, and the second is the Aeroslot, which is a discrete aerodynamically shaped slot; both designs showed an increase in the centerline film cooling effectiveness when compared to the conventional round holes. The Aeroslot showed a large increase in film cooling effectiveness for the same blowing ratio, and mass flow rate of coolant, when compared to the other shapes. A sensitivity study of the blowing ratio to the centerline film cooling effectiveness is carried out for several blowing ratios, covering different jet in cross flow behaviors, fully attached jet, and detached-reattached jet.

Original languageEnglish (US)
Title of host publicationHeat Transfer
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791845721
StatePublished - 2014
EventASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014 - Dusseldorf, Germany
Duration: Jun 16 2014Jun 20 2014

Publication series

NameProceedings of the ASME Turbo Expo


ConferenceASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014

All Science Journal Classification (ASJC) codes

  • General Engineering


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