燃气涡轮试验与研究
燃氣渦輪試驗與研究
연기와륜시험여연구
GAS TURBINE EXPERIMENT AND RESEARCH
2013年
4期
28-32,62
,共6页
高压涡轮导叶%大涡模拟%分离转捩%逆转捩%拟序结构
高壓渦輪導葉%大渦模擬%分離轉捩%逆轉捩%擬序結構
고압와륜도협%대와모의%분리전렬%역전렬%의서결구
high pressure turbine vane%large eddy simulation%separated flow transition%reverse transition%coherent structure
采用自主开发的大涡模拟程序NUL-TURBO，对MT1高压涡轮导叶的跨声速流场进行了数值模拟。在对半叶高位置叶片表面等熵马赫数分布实验数据对比验证的基础上，研究了有无气膜冷却两种情况下叶片表面流场的拟序结构。结果表明：无气膜射流时，叶片吸力面近尾缘位置存在分离转捩过程，并在此过程中发现了发卡涡“森林”现象；有气膜射流时，射流出口位置叶片表面边界层直接转捩为湍流，并发现了叶片压力面逆转捩过程中存在的涡拉伸形态。
採用自主開髮的大渦模擬程序NUL-TURBO，對MT1高壓渦輪導葉的跨聲速流場進行瞭數值模擬。在對半葉高位置葉片錶麵等熵馬赫數分佈實驗數據對比驗證的基礎上，研究瞭有無氣膜冷卻兩種情況下葉片錶麵流場的擬序結構。結果錶明：無氣膜射流時，葉片吸力麵近尾緣位置存在分離轉捩過程，併在此過程中髮現瞭髮卡渦“森林”現象；有氣膜射流時，射流齣口位置葉片錶麵邊界層直接轉捩為湍流，併髮現瞭葉片壓力麵逆轉捩過程中存在的渦拉伸形態。
채용자주개발적대와모의정서NUL-TURBO，대MT1고압와륜도협적과성속류장진행료수치모의。재대반협고위치협편표면등적마혁수분포실험수거대비험증적기출상，연구료유무기막냉각량충정황하협편표면류장적의서결구。결과표명：무기막사류시，협편흡력면근미연위치존재분리전렬과정，병재차과정중발현료발잡와“삼림”현상；유기막사류시，사류출구위치협편표면변계층직접전렬위단류，병발현료협편압력면역전렬과정중존재적와랍신형태。
The flow field of MT1 high pressure turbine vane was numerically simulated using NUL-TUR-BO, which was a large eddy simulation program developed. Based on the validation of isentropic Mach num-ber distribution test data, coherent structures of blade surface with and without film cooling were analyzed. Without film cooling, coherent structures of shock-induced separated flow transition were on blade suction surface near the trailing edge. With film cooling, the airflow of blade surface boundary layer on the jet exit directly transit to turbulence, and the vortex stretching by influence of reverse transition were shown.
