南京航空航天大学学报(英文版)
南京航空航天大學學報(英文版)
남경항공항천대학학보(영문판)
TRANSACTIONS OF NANJING UNIVERSITY OF AERONATICS & ASTRONAUTICS
2011年
1期
103-111
,共9页
涡轮%泄漏%逆向涡流器%周向载荷%涡轮效率
渦輪%洩漏%逆嚮渦流器%週嚮載荷%渦輪效率
와륜%설루%역향와류기%주향재하%와륜효솔
turbines%leakage%backward vortex generators%circumferential load%turbine efficiency
提出了一种逆向涡流发生器控制叶尖泄漏流的新技术,利用压力面和叶顶面的压力差将气流从压力面引入,在叶顶面逆着叶尖泄漏流方向高速射出从而控制和减小叶尖泄漏流.对某典型毫米尺度涡轮叶栅进行了有/无逆向涡流发生器流场的数值研究,分析了逆向涡流发生器对流场及叶栅性能的影响.结果表明在典型进口条件下,逆向涡流发生器使得叶尖间隙泄漏流量降低了2.8%,周向载荷升高了7.7%;与无逆向涡流器情形相比,有逆向涡流器时涡轮效率提高了约1.2%.
提齣瞭一種逆嚮渦流髮生器控製葉尖洩漏流的新技術,利用壓力麵和葉頂麵的壓力差將氣流從壓力麵引入,在葉頂麵逆著葉尖洩漏流方嚮高速射齣從而控製和減小葉尖洩漏流.對某典型毫米呎度渦輪葉柵進行瞭有/無逆嚮渦流髮生器流場的數值研究,分析瞭逆嚮渦流髮生器對流場及葉柵性能的影響.結果錶明在典型進口條件下,逆嚮渦流髮生器使得葉尖間隙洩漏流量降低瞭2.8%,週嚮載荷升高瞭7.7%;與無逆嚮渦流器情形相比,有逆嚮渦流器時渦輪效率提高瞭約1.2%.
제출료일충역향와류발생기공제협첨설루류적신기술,이용압력면화협정면적압력차장기류종압력면인입,재협정면역착협첨설루류방향고속사출종이공제화감소협첨설루류.대모전형호미척도와륜협책진행료유/무역향와류발생기류장적수치연구,분석료역향와류발생기대류장급협책성능적영향.결과표명재전형진구조건하,역향와류발생기사득협첨간극설루류량강저료2.8%,주향재하승고료7.7%;여무역향와류기정형상비,유역향와류기시와륜효솔제고료약1.2%.
A new technique for controlling the tip leakage flow of micro turbine is presented. It uses backward vortex generators (BVGs) to control and reduce the tip leakage flow. The gas is driven by the pressure difference between pressure surface and blade tip, so it flows into BVGs from the pressure side of blade and flows out from the blade tip with high speed in the inverse-direction of leakage flow. Numerical simulations of typical turbine cascade in millimeter scale with and without BVGs are performed. The influence of BVGs on the flow fields and the performance of cascade is analyzed. The results show that the mass of leakage flow decreases by 2.8% and the circumferential load increases by 7.7% under typical entrance condition. Moreover, compared with the case without BVGs, the turbine efficiency grows about 1.2 % in case with BVGs.