Experimental studies on combustion performance of beeswax-paraffin blended solid fuels in a hybrid rocket

Indian Journal of Chemical Technology

article

Saravanan G¹  Adithy Shah¹  Shawon Saha¹ 

[1] Department of Aerospace Engineering, SRM Institute of Science and Technology

关键词: Blended solid wax fuels;    Combustion;    Hybrid rocket;    Axial flow;    Swirl flow;    Regression rate;    Characteristic velocity;    Article;   

DOI  :  10.56042/ijct.v30i1.69681

学科分类：化学（综合）

来源: National Institute of Science Communication and Information Resources

【 摘 要 】

The study intends to investigate the physical, chemical and thermal characteristics of paraffin blended fuels to determine their suitability as a solid fuel in a hybrid rocket. Wax fuels are a viable and efficient alternative to conventional rocket fuels, having excellent structural strength and thermal and mechanical properties. By utilizing both axial and swirl injection technique, the combustion performance of paraffin – beeswax blended fuels have been tested with a fabricated cylindrical grain in a laboratory-scale rocket setting along with oxygen. The test outcomes revealed solid fuel compositions of more beeswax content in paraffin wax on an oxygenated gaseous environment with a swirl-flow injection method has the highest average regression rate of 1.649 mm/sec at 181 kg/m2s mass flux. Axially injected oxygen with pure paraffin wax has the lowest value of 0.85 mm/sec at 96 kg/m2s. The regression rate comparisons revealed that oxygen injection by a swirl injector increased the regression rates by 40% for mass fluxes greater than 80 kg/m2s. Compared to other studies, the combustion efficiencies have been obtained in this study are good. Blended fuels can manage and increase combustion efficiencies for axial and swirl flow conditions. Swirl injectors outperform axial injectors for oxygen injection and allow for a higher proportion of Beeswax combined with paraffin. This study exclusively designed and manufactured an axial injector and swirl injector, according to the required dimensions of a lab-scale hybrid rocket's combustion chamber, injector, and exhaust nozzle, and their performances have been evaluated.

【 授权许可】

CC BY-NC-ND