遷音速圧縮機動翼列の失速点近傍における流れ場の数値解析 : 第2報・tip clearance高さの流れ場に及ぼす影響

概要

論文の詳細を見る
A dominant influence of tip clearance on efficiency and aerodynamic stability of fan/compressor rotors is well-known and has been widely confirmed. So it is increasingly important to understand the detailed flowfield around the tip region of modern fan/compressor rotors. Conventional analytical and experimental methods have several drawbacks to examine this complex flowfield and were not necessarily successful in finding out direct relationship between cause of aerodynamic instability and specific flow phenomena inside rotors. On the other hand, CFD has been able to provide an alternative measure in turbomachinery flow recently. In our accompanying paper, the flowfield transition around the tip region along the design speed operating line was clearly captured with 0.5% tip clearance and the process in which the steady flow in transonic fan/compressor rotors breaks down into tip stall was qualitatively resolved. Based upon the calculated results, a model was proposed on the onset of tip stall in transonic rotors. In this paper, the numerical experiments are conducted by altering tip clearance height in order to examine the effect on both loss generation and the onset of tip stall and to verify the model proposed above. From a qualitative point of view, the model works well with 0.25% and 1.0% tip clearance as well as 0.5% one and the conclusions drawn in our accompanying paper are numerically validated. Also our numerical results show that tip clearance has a dominant influence on pressure ratio, efficiency and stable operating range of transonic fan/compressor rotors.
社団法人日本ガスタービン学会の論文
1997-12-10

遷音速圧縮機動翼列の失速点近傍における流れ場の数値解析 : 第2報・tip clearance高さの流れ場に及ぼす影響

スポンサーリンク

概要

著者

関連論文

スポンサーリンク