Indian Journal of Chemical Technology

Open Access Open Access  Restricted Access Subscription Access

Experimental Studies on Combustion Performance of Beeswax-Paraffin Blended Solid Fuels in a Hybrid Rocket


Affiliations
1 Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulatur, Chennai, Tamil Nadu India, 603203, India
 

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/m<sup>2</sup>s mass flux. Axially injected oxygen with pure paraffin wax has the lowest value of 0.85 mm/sec at 96 kg/m<sup>2</sup>s. 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/m<sup>2</sup>s. 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.

Keywords

Blended Solid Wax Fuels, Combustion, Hybrid Rocket, Axial Flow, Swirl Flow, Regression Rate, Characteristic Velocity.
User
Notifications
Font Size

  • Han S & Moon H, J Mech Sci Technol, 33 (2019) 3011.

  • Wu Y, Yu, X, Lin X, Li S, Wei X, Zhu C & Wu L, Aerosp Sci Technol, 82 (2018) 620.

  • Alessandro M, Merotto L & Pinarello G, Acta Astronaut, 126 (2016) 286.

  • Karabeyoglu M A, Zilliac G, Cantwell B J, DeZilwa S & Castellucci P, Propul Power, 20 (2004) 1037.

  • Rajiv Kumar & Ramakrishna P A, Acta Astronaut, 103 (2014) 226.

  • Sakote R, Yadav N, Srinibas K, Chand Joshi P & Chatterjee, Propellant Explos Pyrotech, 39 (2014) 859.

  • Yuasa S, Ide T, Masugi M, Sakurai T, Shiraishi N & Shimada T, J Therm Sci Technol, 6 (2011) 268.

  • Berwal P & Biswas S, Int J Turbomach Propuls Power, 5 (2020) 1.

  • Guobiao C, Guobiao C, Zeng Zhao, Bo Zhao, Yufei Liu & Nanjia Yu, Aerosp Sci Tecnol, 103, (2020) 1.

  • Martino G D, Carmicino C & Savino R, J Propuls Power, 33 (2017) 1395.

  • Martino G D, Malgieri P, Carmicino C & Savino R, Acta Astronaut, 129 ( 2016) 8.

  • Lee T S & Tsai H L, 9th Asian Pacific International Symposium on Combustion and Energy Utilization, Beijing, China, November, 2 (2008) 1.

  • Santos L M C, Almeida L A R & Veras C A G, Proceedings of the 18th International Congress of Mechanical Engineering, CD-ROM, ABCM, Rio de Janeiro, Brasil (2005).

  • Tarmizi A, Razali A, Taha A, Anudip & Amzaryi, AIP Conference Proceedings, 1930 (2018) 020010.

  • Putnam S, University of Tennessee, Knoxville Doctoral Dissertation, (2007).

  • Lyne J, Naoumov V, Scholes, J, Dodge M, Elton B, Wozniak P, Austin D & Combs C, 43rd Aerospace Sciences Meeting and Exhibit, Reno, NV, (2005).

  • Scholes J, University of Tennessee, Knoxville Master’s Thesis, (2005).

  • Naoumov V & Al-Masoud N, AIAA Sci Tech Forum, Kissimmee, FL(2018).

  • Naoumov V, Al-Masoud N, Butt J , Correa C, Parmelee D , Couillard M , Nguyen H, Ampofo J & Patel K, AIAA SciTech Forum, Orlando, FL (2020).

  • Naoumov V, Al-Masoud N, Sansevero P, Guadagnoli L, Moni A M & Loukides D, AIAA SciTech Forum, National Harbor, MD, (2014).

  • Naoumov V, Al-Masoud N , Sherman K , Doolittle M , Ziegler M & Thorne D, AIAA Sci Tech Forum, Grapevine, TX, (2017).

  • Naoumov V, Haramboulous A, Goldreich A & Mons E, 51st AIAA Aerospace Sciences Meeting, Grapevine, TX, (2013).

  • Naoumov V, Nguyen H & Alcalde B, 54th AIAA Aerospace Sciences Meeting (2016).

  • Naoumov V, Al-Masoud N, Sherman K, Doolittle M, Ziegler Thorne D, 55th AIAA Aerospace Sciences Meeting, 9 - 13 January, Grapevine, Texas, (2017).

  • Naoumov V, Nguyen H & Alcalde B, AIAA Sci Tech Forum, San Diego, CA, (2016).

  • Naoumov V, Skomin P & Deptula P, AIAA Sci Tech Forum, Kissimmee, FL, (2015).

  • Makled A, Adv Military Technol, 14 (2019) 99.

  • Gomes S R, Leopoldo R & Fritz J A F, J Aerosp Technol, 7 (2015) 418.

  • Shin K H, Lee C & Yu Yung H, J Mech Sci Technol, 19 (2005) 1939.

  • Bertoldi A E, Veras C A G & Hendrick P, 7th European Conference for Aeronautics and Space Sciences, (2017).

  • Heydari M M & Massoom N G, Int J Aerosp Eng, 2017 (2017) 1.

  • Carmicino C & Russo Sorge, J Propul Power, 21 (2005) 606.

  • Carmicino C & Russo Sorge, Aerosp Sci Technol, 11 (2007) 61.

  • James G Speight, Handbook of Industrial Hydrocarbon Processes, Second Edition, (2020).

  • Battista F, Cardillo D, Fragiacomo M, Martino M G, Mungiguerra S & Savino R, Aerospace, 6 (2019) 89.


Abstract Views: 116

PDF Views: 92




  • Experimental Studies on Combustion Performance of Beeswax-Paraffin Blended Solid Fuels in a Hybrid Rocket

Abstract Views: 116  |  PDF Views: 92

Authors

Saravanan G.
Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulatur, Chennai, Tamil Nadu India, 603203, India
Adithy Shah
Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulatur, Chennai, Tamil Nadu India, 603203, India
Shawon Saha
Department of Aerospace Engineering, SRM Institute of Science and Technology, Kattankulatur, Chennai, Tamil Nadu India, 603203, India

Abstract


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/m<sup>2</sup>s mass flux. Axially injected oxygen with pure paraffin wax has the lowest value of 0.85 mm/sec at 96 kg/m<sup>2</sup>s. 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/m<sup>2</sup>s. 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.

Keywords


Blended Solid Wax Fuels, Combustion, Hybrid Rocket, Axial Flow, Swirl Flow, Regression Rate, Characteristic Velocity.

References