Improvement of a Propulsion Equipment with a Supersonic Nozzle for Single Pulse Detonation
Improvement of a Propulsion Equipment with a Supersonic Nozzle for Single Pulse Detonation
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DOI：
10.4236/ojfd.2014.45035
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发表时间：
2014-12
期刊：
影响因子：
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通讯作者：
Kazuhiko Toshimitsu;Shuuto Mikajiri;R. Takahashi
中科院分区：
文献类型：
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作者：
Kazuhiko Toshimitsu;Shuuto Mikajiri;R. Takahashi
脉冲爆震发动机是超音速发动机的候选发动机之一。本文设计了一种超音速喷管引射器，用于增加甲烷-氧气和氢氧混合物的单脉冲爆轰推力。设计方法以常规特征线法为基础，进口条件为甲烷-氧气和氢氧混合物爆轰波的平均值。为了保证设计喷管的性能，对有设计喷管和无喷管(直型)的推力进行了比较。在此基础上，利用商用软件Ansys CFX对所设计的喷嘴的流速、温度和速度进行了计算，以确保其合理性。从而成功地提高了甲烷-氧气和氢氧混合气的单脉冲爆震推力，分别是直喷式的1.4倍和2.0倍。
A pulse detonation engine (PDE) is one of candidates of aerospace engines for supersonic cruse. In the paper, a supersonic nozzle ejector is designed to increase thrust of single pulse detonation for methane-oxygen and hydrogen-oxygen mixtures. The design method is based on the conventional characteristic method and inlet condition is averaged value of detonations of methane-oxygen and hydrogen-oxygen mixtures. Comparison of thrusts with a design nozzle and no nozzle (straight- type) is conducted to ensure the designed nozzle performance. Furthermore, the flow velocity, temperature and velocity of the designed nozzle are calculated to ensure its appropriateness with the commercial software ANSYS CFX. Consequently, we succeed in increasing the thrusts of the single pulse detonation with the nozzle, which are 1.4 and 2.0 times as large as ones of straight- type for methane-oxygen and hydrogen-oxygen mixtures respectively.