Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine

LIU Chun-yang; WANG Zhan-xue; FU Peng-zhe

Chinese

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Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine

更新时间：2026-07-07

- Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine
- Vol. 25, Issue 8, (2010)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,710072
  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：2010
- 稿件说明：
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LIU Chun-yang, WANG Zhan-xue, FU Peng-zhe. Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine[J]. 2010, 25(8).
DOI：

LIU Chun-yang, WANG Zhan-xue, FU Peng-zhe. Numerical simulation on thrust reverser based on secondary flow for high-bypass-ratio turbofan engine[J]. 2010, 25(8). DOI：

摘要

基于CFD(计算流体动力学)数值模拟技术

分别对两个不同涵道比涡扇发动机叶栅式射流控制反推模型进行计算

分析了反推力的产生及控制机理

并详细分析了二次流喷射压比、喷射位置、喷射角度及主流压比对流场结构和反推性能的影响.采用与反推力成正比的参数反推质量流量比来衡量反推性能的优劣

计算结果表明:二次流喷射压力、喷射位置和喷射角度是影响反推性能的重要参数

并且在一定的风扇涵道流前提下

存在最佳的二次流喷射位置、喷射角度和喷射压力;由于二次流引气量的限定

限制了二次流射入深度

因此射流控制反推技术不能用于超大涵道比发动机.

Abstract

The study for thrust reverser based on secondary flow injection was carried out with the method of CFD(computational fluid dynamics).The two-dimensional flow field of thrust reversers with secondary flow injection was numerically simulated to study the effect of location of secondary injection

angle of secondary injection

total pressure ratio of secondary injection and total fan nozzle pressure ratio on the performance of the thrust reverser.The important parameter is cascade flow ratio

which is in direct proportion to reverse thrust.The results show that the configuration of flow field presented in this thesis is similar to the referenced flow field.Location and angle of injection with optimum values are important factors while the total pressure ratio of injection has a fitting value.Due to the limitation of secondary mass flow

the injection depth is finite

so the new reverse thrust concept can not be adopted by super high-bypass-ratio turbofan engines.

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Related Institution

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School of Astronautics, Beijing University of Aeronautics and Astronautics

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