N<sub>2</sub>O/HTPB固液火箭发动机喷管两相流计算

N₂O/HTPB固液火箭发动机喷管两相流计算

1.
School of Astronautlcs, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
The 41st Research Institute, The 6th Academy of China Aerospace Science and Industry Corporation, Hohhot 010010, China

摘要: 利用二维轴对称N-S方程对选用氧化亚氮/丁羟基燃料推进剂的固液混合火箭发动机的喷管两相流进行了计算.计算采用MacCormack时间推进预报校正二步格式,采用了Baldwin-Lomax代数湍流模型和两相平衡流模型.计算了三种氧燃比下4个不同喷管的喷管流场参数,并计算了喷管性能,通过比较两相流和气相流的计算结果,分析了不同氧燃比和喷管形状对喷管性能的影响,认为固液火箭发动机的性能主要受氧燃比的影响,为固液混合火箭发动机的设计提供了依据.
- 固液混合火箭发动机 /
- 喷管 /
- 两相流 /
- 氧化亚氮 /
- 丁羟基燃料
Abstract: Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N₂O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.MacCormack decomposition scheme and B-Lalgebraic turbulence model and two-phase equilibrium flow model were used.The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated.Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results.Vacuum specific impulse is bound up with oxidizer-to-fuel ratio.This paper will be useful for the hybrid rocket motor design.
- hybrid rocket motor /
- nozzle /
- two-phase flow /
- N₂O /
- HTPB-based fuels

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