Pulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modeling task. A quasi-1-D, finite-rate chemistry computational fluid dynamics model for PDREs is described and implemented. Four different PDRE geometries are evaluated in this work: a baseline detonation tube, a detonation tube with a straight extension, and a detonation tube with two types of converging-diverging (C-D) nozzles. The effect of extension length and C-D nozzle area ratio on the single-shot gasdynamics and performance of a PDRE is studied over a wide range of blowdown pressure ratios (1-1000). The results indicate that a C-D nozzle is generally more effective than a straight extension in improving PDRE performance, particularly at higher pressure ratios. Additionally, the results show that the blowdown process of the C-D nozzle systems could be beneficially cut off well before the pressure at the end-wall reaches the ambient value. The performance results are also compared to a steady-state rocket system using similar modeling assumptions.
Numerical Modeling of Pulse Detonation Rocket Engine Gasdynamics And Performance
2004
34 pages
Report
No indication
English
NUMERICAL MODELING OF PULSE DETONATION ROCKET ENGINE GASDYNAMICS AND PERFORMANCE
British Library Conference Proceedings | 2004
|Numerical Modeling of Single-Pulse Gasdynamics and Performance of Pulse Detonation Rocket Engines
Online Contents | 2005
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