航空计算技术
航空計算技術
항공계산기술
AERONAUTICAL COMPUTER TECHNIQUE
2014年
2期
70-73
,共4页
线性级联叶栅%叶尖间隙%泄漏涡流%数值模拟
線性級聯葉柵%葉尖間隙%洩漏渦流%數值模擬
선성급련협책%협첨간극%설루와류%수치모의
liner cascade%tip clearance%leakage vortex%numerical simulation
利用NUMECA软件对某线性叶栅的三维流场进行了数值模拟，对比研究了小叶尖间隙和大叶尖间隙时叶尖泄漏涡流的形成和发展，探讨了叶尖间隙大小对叶栅流场和气动性能的影响。研究表明，随着叶尖间隙的增大，叶尖泄漏射流发展成为叶尖泄漏涡，涡流范围不断增大，涡流强度增大趋缓，涡流使得气流偏转减小。从小间隙逐渐增大到大间隙，总压损失与叶片载荷均增大，而在大叶尖间隙时，总压损失增加并不显著，叶片载荷增大趋缓。其结论为进一步揭示叶尖间隙涡流的流动机理以及工业燃气轮机的优化设计提供了参考。
利用NUMECA軟件對某線性葉柵的三維流場進行瞭數值模擬，對比研究瞭小葉尖間隙和大葉尖間隙時葉尖洩漏渦流的形成和髮展，探討瞭葉尖間隙大小對葉柵流場和氣動性能的影響。研究錶明，隨著葉尖間隙的增大，葉尖洩漏射流髮展成為葉尖洩漏渦，渦流範圍不斷增大，渦流彊度增大趨緩，渦流使得氣流偏轉減小。從小間隙逐漸增大到大間隙，總壓損失與葉片載荷均增大，而在大葉尖間隙時，總壓損失增加併不顯著，葉片載荷增大趨緩。其結論為進一步揭示葉尖間隙渦流的流動機理以及工業燃氣輪機的優化設計提供瞭參攷。
이용NUMECA연건대모선성협책적삼유류장진행료수치모의，대비연구료소협첨간극화대협첨간극시협첨설루와류적형성화발전，탐토료협첨간극대소대협책류장화기동성능적영향。연구표명，수착협첨간극적증대，협첨설루사류발전성위협첨설루와，와류범위불단증대，와류강도증대추완，와류사득기류편전감소。종소간극축점증대도대간극，총압손실여협편재하균증대，이재대협첨간극시，총압손실증가병불현저，협편재하증대추완。기결론위진일보게시협첨간극와류적류동궤리이급공업연기륜궤적우화설계제공료삼고。
In this paper ,the three-dimensional flow of a liner cascade has been numerical simulated by u-sing the commercial software Numeca .To investigate the formation and development of the leakage vortex and the influence of the tip clearance size in the aerodynamic characteristics and flow field of the cas-cade ,the calculation of the cascade in different tip clearance , such as small tip clearance and large tip clearance has been done .The result showed that while the tip clearance increased ,the jet gradually devel-oped into a vortex ,and the scope of the vortex increased ,but the intensity of the vortex didn′t increased notably .Meanwhile ,the deflection of the flow caused by the vortex decreased .When the tip clearance size increased from small one to large one ,both the total pressure loss and the blade force increased remark-ably.However,within the large tip clearance,the total pressure loss didn′t increase clearly and the in-crease of the blade force tended to be slow .These results might provide significant inference to the study of leakage vortex and the design of industrial gas turbines .
