Preliminary Analysis and Design of Turborocket Combustion Chamber

The focus of this research is to provide a preliminary design of the combustion chamber of the turborocket engine. The present study delineates the specific steps for designing a combustion chamber. Firstly, the expected chemical composition was calculated by Gibbs Minimization. Knowing the composition of the mixture, the physical properties like density, the ratio of specific heats, etc., are calculated at temperatures that have been obtained from Glassman [2]. Then, the time frame of the reaction was calculated. The dimensions of the combustion chamber were calculated after obtaining all the above information. A parametric analysis was performed to characterize the behavior of the combustion chamber when its geometrical factors like flameholder positions and length are changed. The novelty of this study lies in the fact that there has not been any study that provides a complete framework for designing a combustion chamber and at the same time focuses on turborocket engine. The preliminary results show that the length leads to very significant changes in temperature wherein temperature increases up to a point after which it decreases as a result of completion of the reaction.