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亚声速扩压叶栅中端弯积叠方式的研究

ISSN号：1001-4055
期刊名称：《推进技术》
时间：0
分类：V231.3[航空宇航科学与技术—航空宇航推进理论与工程;航空宇航科学技术]
作者机构：[1]哈尔滨工业大学发动机气体动力研究中心,黑龙江哈尔滨150001, [2]中国船舶重工集团公司第七0三研究所,黑龙江哈尔滨150078
相关基金：国家自然科学基金（51206035）;国家自然科学基金（51436002）;国家自然科学基金创新研究群体项目（51121004）

关键词：扩压叶栅, 弯曲叶片, 端弯叶片, 数值仿真, Compressor cascade , Bowed blade , Re-camber blade , Numerical simulation

中文摘要：

为了改善扩压叶栅端区的流动匹配,通过数值模拟的方式,以直叶片和正弯叶片扩压叶栅为应用背景,详细对比研究了不同的端弯叶片积叠方法对扩压叶栅气动性能的影响。研究结果表明,在亚声速扩压叶栅中,前缘增弯的端弯造型可以有效降低来流攻角,以相同端弯弯角为前提,最为有效的端弯积叠方式是保持尾缘不变的尾缘积叠。无论采用何种端弯积叠方式,都会造成叶片的前部或者后部的局部弯曲,对叶栅流道产生类似于弯叶片的流动控制作用。将尾缘积叠端弯造型应用于正弯叶片中,一定程度上会抵消叶片前部的正弯效果,但并不会完全抑制;而前缘积叠端弯造型则会促进叶片后部的正弯效果。在亚声速环境下直叶片流道内应用前缘增弯的端弯造型技术时,推荐采用前缘积叠的端弯造型方法;但在正弯叶片流道内应用端弯造型技术时,推荐采用尾缘积叠的端弯积叠方式。

英文摘要：

To ameliorate the flow matching of end region in compressor cascade, by numerical simula- tion, with straight blade and positive bowed blade compressor cascade as application background, different stacking of re-camber blade have been adopted for comparative study of their effect on compressor cascade aero- dynamic performance. The results show that, in subsonic compressor cascade, leading edge （LE） re-camber can reduce the incidence effectively. Subject to the same re-camber angle, trailing edge （TE） stacking is the most effective way by fixing the TE immobile. No matter what kind of stacking has been adopted, front or rear blade will be locally bowed, affecting on flow field in compressor cascade similar to bowed blade. Applied in pos- itive bowed blade, TE stacking re-camber will partly counteract the effect of positive bowed on front blade, but not entirely suppress the effeteness. While LE stacking re-camber will promote the effect of positive bowed on rear blade. It is recommended that LE stacking re-camber can be applied in subsonic straight blade, and TE stacking re-camber can be applied in subsonic positive bowed blade.

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