Effect of serrated cut at trailing edge on performance of lobed mixer in forced mixing exhaust system

DING Yu-lin; LIU You-hong; XIE Yi; SHAO Wan-ren; WU Fei

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Effect of serrated cut at trailing edge on performance of lobed mixer in forced mixing exhaust system

更新时间：2026-07-07

- Effect of serrated cut at trailing edge on performance of lobed mixer in forced mixing exhaust system
- Vol. 27, Issue 10, (2012)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 中国航空工业集团公司沈阳发动机设计研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
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DING Yu-lin, LIU You-hong, XIE Yi, et al. Effect of serrated cut at trailing edge on performance of lobed mixer in forced mixing exhaust system[J]. 2012, 27(10).
DOI：

DING Yu-lin, LIU You-hong, XIE Yi, et al. Effect of serrated cut at trailing edge on performance of lobed mixer in forced mixing exhaust system[J]. 2012, 27(10). DOI：

摘要

针对某涡扇发动机波瓣强迫混合排气系统建立了尾缘锯齿修形流场数值计算模型

通过三维数值模拟研究

得到了不同尾缘锯齿修形波瓣强迫混合排气系统流场的演变规律和热混合效率、总压恢复系数的变化规律.结果表明:在强迫混合排气系统出口截面处

热混合效率随修形量的增加而增大

总压恢复系数随修形量的增加而减少.1个三角形(1-SJ)锯齿修形模型的热混合效率最大

达到79.73%;2个梯形修形(2-TX)的综合效果最优

其热混合效率达到77.50%

总压恢复系数比1-SJ高出0.5%.

Abstract

Based on a lobed mixer in the forced mixing exhaust system of a turbofan engine

geometric models of different serrated cuts at trailing edge were constructed.Through three-dimensional computational fluid dynamic simulations

the effect of serrated cut at trailing edge on the performance of a lobed mixer in a forced mixing exhaust system on the thermal mixing efficiency and total-pressure recovery coefficient were studied.The results show that the thermal mixing efficiency rises while the total-pressure recovery coefficient declines as the cut size of the serrated cut increases.The thermal mixing efficiency of one triangle (1-SJ) serrated modification model was 79.73%.The thermal mixing efficiency of two trapezoidal modifications (2-TX) was 77.50%

and the total-pressure recovery coefficient of 2-TX was 0.5 percentage higher than that of 1-SJ.

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Related Author

LI Teng

LIU Yong-hong

XIE Yi

WU Fei

SHAO Wan-ren

LIU You-hong

XIE Yi

刘友宏

Related Institution

Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

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