雙旋流混合火箭引擎Dual Vortical Flow Hybrid Rocket Engine

專利類型

發明

專利國別 (專利申請國家)

中華民國

專利申請案號

102119323

專利證號

I 504538

專利獲證名稱

雙旋流混合火箭引擎Dual Vortical Flow Hybrid Rocket Engine

專利所屬機關 (申請機關)

財團法人國家實驗研究院

獲證日期

2015/10/21

技術說明

本發明為一創新的混合火箭引擎，它使用配對雙旋流設計構成的燃燒室。本發明使得能夠增加靠近固態燃料表面燃燒的總滯留特性時間，並經由流體轉灣及反向旋流效應，所造成強大的流體應力效果，達成完全的混合增益效果，最後達成幾近理想的燃燒及推進效率，同時可使本混合火箭引擎的設計長度大幅縮短。本發明包括的範圍：混合火箭引擎裝置配對的雙旋流燃燒室組合；各燃燒室最外圍，裝置在環繞方向近切線的氧化劑喷注嘴組合；而臨近的雙燃燒室的氧化劑噴注方向為相反方向，形成對轉旋流的基本流體結構。 The present invention is an innovative hybrid rocket engine that utilizes sets of dual vortical flow design to form its combustion chambers. This innovation enables the increase in the overall combustion residence time along the proximity of the solid propellant surfaces. It also achieves close to perfect mixing due to largely increased stresses caused by flow turning and the counter rotations. The net effect is close to ideal mixing efficiency and thrust performance. It also renders much reduced engine length in the hybrid rocket engine design. The claim of this invention includes: hybrid rocket engine with installation of sets of dual vortical flow combustion chambers; each combustion chamber is equipped with a set of oxidizer injectors on the outer radius surface that have close to tangential injection in the circumferential direction; and opposite circumferential injections are utilized for the dual chambers to form the counter-rotating basic flow structure.

備註

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