主催: 一般社団法人 日本機械学会
会議名: 2019年度 年次大会
開催日: 2019/09/08 - 2019/09/11
In this study investigated that the effect of fuel length and geometric swirl number (Sg) on the local regression rate in swirling-oxidizer-flow-type hybrid rocket using a low-melting-point thermoplastic (LT) fuel. The LT fuel has excellent mechanical and adhesive properties, as well as a high regression rate compared to conventional hybrid rocket fuel. In the static firing test with logn fuel length, low values of averaged-regression rate are observed and these results show the different tendency of results from a previous study. It is considered that the effect of the oxidant swirling flow diminishes toward the fuel trailing edge and the average fuel retraction rate decreases. The equation of average regression rate of the LT fuel including Sg (0, 9.7, 19.4, 37.4) and fuel length was shown as r = 0.059Sg 0.224Gp0.788Lf-0.166. The local regression rate at Sg = 9.7 and 19.4 increase the local regression rate behind the fuel compared to Sg = 0. Influence of the development of the turbulent boundary layer might be considered. At Sg = 9.7, the fuel residue amount is approximately 29.8% of Sg = 0. These results show that it is possible to realize a hybrid rocket engine with high fuel regression rate and low fuel residue by selecting the appropriate shape swirl number corresponding to the fuel length.