Effect of Internal Flow Guide in Pintle Tip on Pintle Injector Thruster Combustion

被引：3

作者：

Lee, Keonwoong ^{[1
]}

Nam, Jeonsoo ^{[1
]}

Radhakrishnan, Kanmaniraja ^{[1
]}

Koo, Jaye ^{[2
]}

机构：

[1] Korea Aerosp Univ, Grad Sch, Goyang, South Korea

[2] Korea Aerosp Univ, Sch Aerosp & Mech Engn, Goyang, South Korea

来源：

JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES | 2020年 / 48卷 / 09期

关键词：

Multi-Hole Pintle Injector; Flowguide; Bi-propellant Thruster;

D O I：

10.5139/JKSAS.2020.48.9.703

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Pintle injector is known to have been adopted as injector of Lunar Module Descent Engine (LMDE) and contributed to success of the Apollo program and recently used in merlin engine. In this study, 500N Lab-Scale pintle injector thruster was manufactured and the combustion experiment with LOx/GCH4 was conducted. However, the proto-type thruster was showed some problems, such as low combustion efficiency and melting of pintle tip. To solve these problems, the flow guide in pintle tip was suggested through the CFD simulation. After addition of flow guide module, the combustion efficiency increased and pintle tip did not melt until the end of combustion.

引用

页码：703 / 709

页数：7

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