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Comparison of aerodynamic characteristics between a novel highly loaded injected blade with curvature induced pressure-recovery concept and one with conventional design

ISSN号：1000-9361
期刊名称：《中国航空学报：英文版》
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] TE353[石油与天然气工程—油气田开发工程]
作者机构：[1]Stute Key Laboratory fot Turbulenee and Complex Systems, College of Engineering, Peking University, Beijing 100871, China, [2]BIC-ESA T, Peking University, Beijing 100871, China, [3]Collabarative Innovation Center of Advaneed Aero-Engine, Beijing 100083, China
相关基金：co-supported by the National Natural Science Foundation of China（Nos.51576003 and 11521091）; China Postdoctoral Science Foundation（No.2016M600015）

作者： Zhiyuan CAO[1], Chao ZHOU[1,2,3], Zhili SUN[1]

关键词：压气机叶片, 压力恢复, 曲率, 常规设计, 气动特性, 诱导, 高载荷, 流动分离, Axial compressor Air injection Curvature induced ‘Shock’ Flow control Separation

中文摘要：

Corresponding author at： State Key Laboratory for Turbulence and Complex Systems, College of Engineering, Peking University, Beijing 100871, China. E-mail address： czhou@ pku.edu.cn （C. ZHOU）.

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