【摘要】：針對葉頂間隙的高速泄漏流及復(fù)雜的流動問題,采用求解三維Reynolds-Averaged NavierStokes(RANS)和S-A湍流模型的方法研究了跨聲速流動條件下渦輪葉片頂部的流動傳熱特性,同時計算分析了葉頂間隙高度和進口湍流強度對頂部流動換熱特性的影響。研究結(jié)果表明:葉頂間隙為0.188%動葉高度(小間隙)時,間隙泄漏流為亞聲速(0.3Ma0.8)并具有最大的葉頂換熱系數(shù);當(dāng)葉頂間隙高度增大至0.75%動葉高度時,間隙泄漏流出現(xiàn)超聲速流動(1.0Ma1.3),葉頂平均換熱系數(shù)最小;隨著間隙高度增大,超聲速流動區(qū)域從尾緣向前緣擴展,頂部換熱系數(shù)先減小后增大。葉頂間隙高度的增大使得馬蹄渦向吸力面?zhèn)纫苿?從而改變?nèi)~頂前緣附近換熱系數(shù)分布;泄漏流在間隙區(qū)域急劇加速使得湍流水平顯著降低,而進口湍流強度變化對于葉頂換熱影響很小,但進口湍流強度增大時葉頂前緣吸力面?zhèn)榷瘟鳒p弱。
[Abstract]:In order to solve the problem of high speed leakage and complex flow in tip clearance, the flow and heat transfer characteristics at the top of turbine blade under transonic flow are studied by solving the three dimensional Reynolds-Averaged NavierStokes (RANS) and S-A turbulence models. The effects of tip clearance height and inlet turbulence intensity on the heat transfer characteristics of the top flow are also calculated and analyzed. The results show that when the tip clearance is 0.188% moving blade height (small clearance), the gap leakage flow is subsonic (0.3Ma0.8) and has the largest tip heat transfer coefficient, and when the tip clearance height increases to 0.75%, There is supersonic flow (1.0Ma1.3) in the interstitial leakage flow, and the average heat transfer coefficient at the top of the blade is the smallest. With the increase of the clearance height, the supersonic flow region extends from the front edge of the tail edge, and the heat transfer coefficient at the top decreases first and then increases. With the increase of the height of the tip clearance, the horseshoe vortex moves to the suction side, thus changing the distribution of heat transfer coefficient near the front edge of the tip of the blade, and the leakage flow accelerates sharply in the gap region, and the turbulent level decreases significantly. But the change of inlet turbulence intensity has little effect on the heat transfer at the top of the blade, but the secondary flow on the suction surface of the front edge of the blade tip weakens with the increase of the inlet turbulence intensity.
【作者單位】： 西安交通大學(xué)能源與動力工程學(xué)院;先進航空發(fā)動機協(xié)同創(chuàng)新中心;
【基金】：國家自然科學(xué)基金資助項目(51376144)
【分類號】：TK471

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