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[1]南向军,张 锐,张留欢.壁面散热对超声速喷管性能的影响[J].火箭推进,2015,41(03):33-38.
　NAN Xiang-Jun,ZHANG Rui,ZHANG Liu-huan.Effect of wall surface heat dissipation on performance of supersonic nozzle[J].Journal of Rocket Propulsion,2015,41(03):33-38.
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壁面散热对超声速喷管性能的影响

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年03期 页码: 33-38 栏目: 研究与设计 出版日期: 2015-06-30
Title:
Effect of wall surface heat dissipation on performance of supersonic nozzle
作者:
南向军1;  张 锐2; 张留欢1
1. 西安航天动力研究所，陕西 西安 710100；2. 北京航天动力研究所， 北京 100076
Author(s):
NAN Xiang-Jun1;  ZHANG Rui2;  ZHANG Liu-huan1
1. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China; 2. Beijing Aerospace Propulsion Institute, Beijing 100076, China
关键词:
喷管; 散热规律; 推力系数; 理论分析
Keywords:
nozzle;  heat dissipation law;  thrust coefficient;  theory analysis
分类号:
V434-34
文献标志码:
A
摘要:
采用一维无粘理论对扩张喷管的流动和性能进行了计算，研究了壁面散热量和散热规律对喷管流动、出口气流参数和性能参数的影响。结果表明：壁面散热会导致喷管沿程静压、静温和总温减小、出口马赫数和总压增大，并且随散热量增大，喷管的工作状态可依次经历欠膨胀状态、临界状态和过膨胀状态，但是喷管的推力系数逐渐减小，性能下降；壁面散热规律对喷管性能有很大影响，入口附近散热量较大出口附近散热量较小时，喷管的性能下降最大。从研究结果可以看出，壁面散热可以调节喷管的欠膨胀度，使喷管从欠膨胀状态趋于过膨胀状态，采用侧重于后半部分散热的规律可以取得良好的调节效果。
Abstract:
One dimensional non-viscous theory is used to calculate the flow characteristics and performance of a divergent nozzle, and analyze the effect of wall surface heat dissipation and heat dissipation law on flowfield, exit dynamic parameters and performance parameters of the nozzle. The calculated results show that the wall surface heat dissipation may cause decrease of static pressure, static temperature and total temperature, but increase of exit Mach number and total pressure, and descend of the nozzle performance, and may result in, with gradual addition of heat dissipation, the nozzle will suffer from under-expansion and over-expansion, but its thrust coefficient becomes gradually decreased. Besides, the law of heat dissipation will have great influence on nozzle performance. The research result indicates when heat dissipating capacity is higher near inlet and lower near from under expansion to critical expansion. The heat dissipation from rear part of the nozzle can achieve a perfect adjusting effect.

参考文献/References:

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备注/Memo

收稿日期：2014-11-27；修回日期：2015-01-20 基金项目：国家863项目（2012AA702308） 作者简介：南向军（1985—），男，博士，研究领域为内流气体动力学

更新日期/Last Update: 1900-01-01