Effects of Configuration Parameters on Aerodynamic Performance for Chevron Nozzle in Turbofan Engine

被引：0

作者：

Zheng G.-Y. ^{[1
]}

Li W.-P. ^{[1
]}

Lin J.-J. ^{[2
]}

Sun Y.-F. ^{[3
]}

机构：

[1] School of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai

[2] AECC Shenyang Engine Institute, Shenyang

[3] Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Ltd., Shanghai

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 12期

关键词：

Aerodynamic performance; Chevron nozzle; Configuration parameter; Streamwise vortex; Thrust loss; Turbofan engine;

D O I：

10.13675/j.cnki.tjjs.200233

中图分类号：

学科分类号：

摘要：

In order to evaluate aerodynamic performance of chevron nozzle accurately, one definition of its outlet based on flow conservation was firstly proposed. And the consistency between outlet definition method and physical outlet was verified. Then aerodynamic performance of chevron nozzle was assessed and investigated systematically at the design point and off-design point. The results show that among chevron parameters bend angle has the greatest influence on thrust performance, chevron number has less influence and length has the least influence at the design point. Streamwise vortices introduced by chevrons result in thicker shear layer, faster turbulent energy decay and shorter potential core. Chevron nozzle can efficiently decrease shock wave intensity downstream the exit at the off-design point. Larger pressure ratio is needed for chevron nozzle to reach to blockade condition accordingly. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：2734 / 2743

页数：9

共 23 条

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