Endwall film-cooling in a cascade with filleted vane, upstream discrete slots, and holes

被引：1
|
作者：
Shote, Adeola S. [1 ,2 ]
Huyssen, Barbara B. [1 ]
Mahmood, Gazi I. [1 ,3 ]
机构：
[1] Univ Pretoria, Dept Mech & Aeronaut Engn, Engn 1 Bldg,Hatfield Campus,Lynnwood Rd, ZA-0028 Pretoria, South Africa
[2] Olabisi Onabanjo Univ, Dept Mech Engn, Ago Iwoye, Nigeria
[3] Prince Mohammad Bin Fahd Univ, Dept Mech Engn, Al Khobar, Saudi Arabia
来源：
EXPERIMENTAL HEAT TRANSFER | 2024年
基金：
新加坡国家研究基金会;
关键词：
Passage-vortex; endwall heat transfer; film-cooling effectiveness; total pressure-loss; film-cooling distributions; HEAT-TRANSFER; INFRARED THERMOGRAPHY; TURBULENCE; PERFORMANCE; PASSAGE;
D O I：
10.1080/08916152.2024.2424820
中图分类号：
O414.1 [热力学];
学科分类号：
摘要：
In vane cascades, large filleted vanes influence aerodynamics, while upstream endwall film-cooling arrangement impacts aero-thermal performance. This study explores experimental investigations on endwall flows and film-cooling effectiveness in a filleted vane cascade using discrete slots and holes. Two fillet profiles are examined covering the leading-edge area to either the throat or 62% of the axial chord. Film-cooling employs two slots and two rows of holes in the leading-edge region with inlet blowing ratios ranging from 1.0 to 2.8. Results show variations in total pressure loss and Nusselt number between filleted and un-filleted vanes, highlighting optimal film-cooling effectiveness with the smaller fillet profiles.
引用
收藏
页数：33
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