Flowfield measurements for film-cooling holes with expanded exits

K. Thole, M. Gritsch, A. Schulz, S. Wittig

Research output: Contribution to journalConference articlepeer-review

25 Scopus citations

Abstract

One viable option to improve cooling methods used for gas turbine blades is to optimize the geometry of the film-cooling hole. To optimize that geometry, effects of the hole geometry on the complex jet-in-crossflow interaction need to be understood. This paper presents a comparison of detailed flowfield measurements for three different single, scaled-up, hole geometries all at a blowing ratio and density ratio of unity. The hole geometries include a round hole, a hole with a laterally expanded exit, and a hole with a forward-laterally expanded exit. In addition to the flowfield measurements for expanded cooling hole geometries being unique to the literature, the testing facility used for these measurements was also unique in that both the external mainstream Mach number (Ma∞ = 0.25) and internal coolant supply Mach number (Mac = 0.3) were nearly matched.

Original languageEnglish (US)
Pages (from-to)10
Number of pages1
JournalAmerican Society of Mechanical Engineers (Paper)
StatePublished - Jan 1 1996
EventProceedings of the 1996 International Gas Turbine and Aeroengine Congress & Exhibition - Burmingham, UK
Duration: Jun 10 1996Jun 13 1996

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

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