本文選題：高亞聲速 + 擴壓葉柵��； 參考：《大連海事大學學報》2017年02期

【摘要】：壓氣機正逐漸向著高負荷、高穩(wěn)定性的方向發(fā)展.為有效控制該趨勢下間隙區(qū)域內(nèi)的流動損失加劇現(xiàn)象,可在高亞聲速的擴壓葉柵中加裝葉尖小翼.本文對原型葉片及不同寬度的壓力面與吸力面葉尖小翼葉片進行數(shù)值研究.結果表明:高亞聲速下不同安裝方案下的葉尖小翼均可以改善壓氣機的氣動特性,削弱泄漏渦的強度,其中,壓力面小翼對于流場的改善效果更為明顯,與原型相比,PW2.0的總壓損失系數(shù)降低了4.47%.
[Abstract]:The compressor is developing towards high load and high stability. In order to effectively control the increase of flow loss in the gap region under this trend, the tip wing can be added to the high subsonic diffuser cascade. In this paper, the tip blade of prototype blade, pressure surface and suction surface with different widths are studied numerically. The results show that the blade tip wing at high subsonic velocity can improve the aerodynamic characteristics of the compressor and weaken the strength of the leakage vortex, and the pressure surface wing can improve the flow field more obviously. Compared with the prototype, the total pressure loss coefficient of PW2.0 is reduced by 4.47.
【作者單位】： 大連海事大學輪機工程學院;
【基金】：國家自然科學基金重點項目(51436002);國家自然科學基金青年科學基金項目(51406021) 中央高�；究蒲袠I(yè)務費專項資金資助項目(3132014319;3132016334) 遼寧省高等學校創(chuàng)新團隊支持計劃資助項目(LT2015004)
【分類號】：TH45
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本文編號：2109099