Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism

被引：2

作者：

Lai, A. ^{[1
]}

Chou, T. -H. ^{[1
]}

Wei, S. -S. ^{[1
]}

Lin, J. -W. ^{[1
]}

Wu, J. -S. ^{[1
]}

Chen, Y. -S. ^{[2
]}

机构：

[1] Natl Chiao Tung Univ, Dept Mech Engn, Hsinchu, Taiwan

[2] Natl Space Org, Natl Appl Res Labs, Hsinchu, Taiwan

来源：

INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING | 2018年 / 2018卷

关键词：

D O I：

10.1155/2018/6513084

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground I-sp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6 similar to 0.8 mm/s at the surface of disk walls and 1.5 similar to 1.7 mm/s at the surface of central core of the fuel grain.

引用

页数：13

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