Numerical Exploration of Solid Rocket Motor Blast Tube Flow Field

被引：0

作者：

Jayed, Afroz ^{[1
]}

Sinha, P. K. ^{[2
]}

Chakraborty, Debasis ^{[2
]}

机构：

[1] Def Res & Dev Lab, Directorate Computat Dynam, Hyderabad, Andhra Pradesh, India

[2] Def Res & Dev Lab, Hyderabad, Andhra Pradesh, India

来源：

DEFENCE SCIENCE JOURNAL | 2013年 / 63卷 / 06期

关键词：

Blast tube; total pressure loss; computational fluid dynamics; SIMULATION;

D O I：

10.14429/dsj.63.5763

中图分类号：

O [数理科学和化学]; P [天文学、地球科学]; Q [生物科学]; N [自然科学总论];

学科分类号：

07 ; 0710 ; 09 ;

摘要：

The blast tube flowfield of a solid rocket motor is explored numerically by solving 3-D RANS equations with SST Turbulence model using a commercial computational fluid dynamics (CFD) software CFX-10. Parametric studies are carried out to find out the effect of the blast tube diameter on the total pressure loss in the rocket motor. It is observed that the total pressure loss in the rocket motor is less than 4 per cent and the blast tube is contributing less than 1 per cent. It is also found out that higher the blast tube diameter, the lesser the drop in the total pressure. Blast tube geometry is not found to contribute significantly in the overall thrust and specific impulse in the rocket motor.

引用

页码：616 / 621

页数：6

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