Effectiveness of normal and angled slot cooling

A. C. Smith, J. H. Hatchett, A. C. Nix, W. F. Ng, K. A. Thole, Frank J. Cunha

Research output: Contribution to conferencePaperpeer-review


An experimental and numerical investigation was conducted to determine the film cooling effectiveness of a normal slot and angled slot under realistic engine Mach number conditions. Freestream Mach numbers of 0.65 and 1.3 were tested. For the normal slot, hot gas ingestion into the slot was observed at low blowing ratios (M < 0.25). At high blowing ratios (M < 0.6) the cooling film was observed to "lift off" from the surface. For the 30° angled slot, the data was found to collapse using the blowing ratio as a scaling parameter. Results from the current experiment were compared with the subsonic data previously published. For the angle slot, at supersonic freestream Mach number, the current experiment shows that at the same x/Ms, the film-cooling effectiveness increases by as much as 25% as compared to the subsonic case. The results of the experiment also show that at the same x/Ms, the film cooling effectiveness of the angle slot is considerably higher than the normal slot, at both subsonic and supersonic Mach numbers. The flow physics for the slot tests considered here are also described with computational fluid dynamic (CFD) simulations in the subsonic and supersonic regimes.

Original languageEnglish (US)
Number of pages8
StatePublished - 2004
Event2004 ASME Turbo Expo - Vienna, Austria
Duration: Jun 14 2004Jun 17 2004


Other2004 ASME Turbo Expo

All Science Journal Classification (ASJC) codes

  • General Engineering


Dive into the research topics of 'Effectiveness of normal and angled slot cooling'. Together they form a unique fingerprint.

Cite this