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[1]杨振鹏.引射冷却系统设计与数值模拟[J].火箭推进,2010,36(06):11-14.
　Design and numerical simulation of cooling ejector system[J].Journal of Rocket Propulsion,2010,36(06):11-14.

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引射冷却系统设计与数值模拟

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 36 期数: 2010年06期页码: 11-14 栏目: 研究与设计出版日期: 2010-12-15

Title:: Design and numerical simulation of cooling ejector system

文章编号:: 1672-9374(2010)06-0011-05

作者:: 杨振鹏; 西安航天动力研究所，陕西西安 710100

Author(s):: Xi’an Aerospace Propulsion Institute, Xi’an 710100, China

关键词:: 引射喷管; 复合可压流法; 粘性影响; 数值模拟

Keywords:: ejector nozzle; a complex compressible method; viscid effect; numerical simulation

分类号:: O354-34

文献标志码:: A

摘要:: 采用复合可压流法和考虑粘性影响的一维流法设计了满足最大次流流量的引射喷管冷却结构，并采用Delphi语言开发了具有友好人机界面的设计应用软件，对引射喷管抽吸特性规律进行了研究，利用Fluent商用软件进行了设计引射喷管结构的数值模拟，验证了计算方法的有效性。

Abstract:: A cooling ejector system that has the maximum secondary flux was designed with a composite compressible flow method and viscid one-dimensional flow method which considers the effect of viscidity. A design software with man-machine friend interface was developed with Delphi cooling language. The pump characteristics of ejector nozzle was investigated by the numerical simulation. Numerical simulation of the designed structure by Fluent demonstrates that the method is effective.

备注/Memo

收稿日期：2010-０8-１３；修回日期：2010-09-16
基金项目：中国航天科技集团公司支撑项目
作者简介：杨振鹏（1984—），男，硕士，研究领域为冲压发动机燃烧室设

更新日期/Last Update: 1900-01-01