Numerical modeling of heat transfer and pressure losses for an uncooled gas turbine blade tip: Effect of tip clearance and tip geometry

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

3 Scopus citations

Abstract

A computational study has been performed to predict the heat transfer distribution on the blade tip surface for a representative gas turbine first stage blade. CFD predictions of blade tip heat transfer are compared to test measurements taken in a linear cascade, when available. The blade geometry has an inlet Mach number of 0.3 and an exit Mach number of 0.75, pressure ratio of 1.5, exit Reynolds number based on axial chord of 2.57x106, and total turning of 110 deg. Three blade tip configurations were considered; they are flat tip, a full perimeter squealer, and an offset squealer where the rim is offset to the interior of the tip perimeter. These three tip geometries were modeled at three tip clearances of 1.25, 2.0, and 2.75% of blade span. The tip heat transfer results of the numerical models agree fairly well with the data and are comparable to other CFD predictions in the open literature.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
PublisherAmerican Society of Mechanical Engineers (ASME)
Pages1-9
Number of pages9
ISBN (Print)079184790X, 9780791847909
DOIs
StatePublished - 2007
Externally publishedYes
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Publication series

NameProceedings of the ASME Turbo Expo
Volume4 PART A

Conference

Conference2007 ASME Turbo Expo
CountryCanada
CityMontreal, Que.
Period5/14/075/17/07

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Fingerprint Dive into the research topics of 'Numerical modeling of heat transfer and pressure losses for an uncooled gas turbine blade tip: Effect of tip clearance and tip geometry'. Together they form a unique fingerprint.

  • Cite this

    El-Gabry, L. A. (2007). Numerical modeling of heat transfer and pressure losses for an uncooled gas turbine blade tip: Effect of tip clearance and tip geometry. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air (pp. 1-9). (Proceedings of the ASME Turbo Expo; Vol. 4 PART A). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/gt2007-27008