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http://dx.doi.org/10.3795/KSME-B.2005.29.8.956

Effects of the Inlet Boundary Layer Thickness on the Flow in an Axial Compressor(II) - Loss Mechanism -  

Choi, Min-Suk (포항공과대학교 대학원 기계학과)
Park, Jun-Young (한국기계연구원 에너지기계연구센터)
Baek, Je-Hyun (포항공과대학교 기계공학과)
Publication Information
Transactions of the Korean Society of Mechanical Engineers B / v.29, no.8, 2005 , pp. 956-962 More about this Journal
Abstract
A three-dimensional computation was conducted to make a study about effects of the inlet boundary layer thickness on the total pressure loss in a low-speed axial compressor operating at the design condition ($\phi=85\%$) and near stall condition($\phi=65\%$). Differences of the tip leakage flow and hub corner-stall induced by the inlet boundary layer thickness enable the loss distribution of total pressure along the span to be altered. At design condition, total pressure losses for two different inlet boundary layers are almost alike in the core flow region but the larger loss is generated at both hub and tip when the inlet boundary layer is thin. At the near stall condition, however, total pressure loss fer the thick inlet boundary layer is found to be greater than that for the thin inlet boundary layer on most of the span except the region near hub and casing. Total pressure loss is scrutinized through three major loss categories in a subsonic axial compressor such as profile loss, tip leakage loss and endwall loss using Denton's loss model, and effects of the inlet boundary layer thickness on the loss structure are analyzed in detail.
Keywords
Inlet Boundary Layer Thickness; Loss; Axial Compressor;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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