Record Details

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

NOPR - NISCAIR Online Periodicals Repository

View Archive Info
 
 
Field Value
 
Title Experimental studies on combustion performance of beeswax-paraffin blended solid fuels in a hybrid rocket
 
Creator G, Saravanan
Shah, Adithy
Saha, Shawon
 
Subject Blended solid wax fuels
Combustion
Hybrid rocket
Axial flow
Swirl flow
Regression rate
Characteristic velocity
 
Description 35-45
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.
 
Date 2023-01-27T07:06:14Z
2023-01-27T07:06:14Z
2023-01
 
Type Article
 
Identifier 0975-0991 (Online); 0971-457X (Print)
http://nopr.niscpr.res.in/handle/123456789/61300
https://doi.org/10.56042/ijct.v30i1.69681
 
Language en
 
Publisher NIScPR-CSIR,India
 
Source IJCT Vol.30(1) [January 2023]