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© 2022 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/). Notwithstanding the ProQuest Terms and Conditions, you may use this content in accordance with the terms of the License.

Abstract

Thrust regulation is applied to maintain the performance of the liquid propellant rocket engine. The thrust level of a rocket engine can be readily controlled by adjusting the number of propellants introduced into the combustion chamber. In this study, a gas generator design is proposed in which thrust regulation is maintained by performing secondary combustion in the divergent section of the nozzle of a gas generator. Tangential and normal injection techniques have also been studied for better combustion analyses. A normal injection technique is used for the experiment and CFD results are validated with the experimental data. Chemical equilibrium analyses are also performed by minimizing Gibbs free energy with the steepest descent method augmented by the Nelder–Mead algorithm. These equilibrium calculations give the combustion species as obtained through the CFD results. Performance evaluation of the rocket engine, with and without secondary combustion in the gas generator, led to an increase of 42% thrust and 46.15% of specific impulse with secondary combustion in the gas generator.

Details

Title
Effect of Secondary Combustion on Thrust Regulation of Gas Generator Cycle Rocket Engine
Author
Khan, Sohaib 1 ; Sohail, Muhammad Umer 2   VIAFID ORCID Logo  ; Qamar, Ihtzaz 2 ; Muzna Tariq 3 ; Raees Fida Swati 2   VIAFID ORCID Logo 

 Department of Aeronautics and Astronautics Engineering, Institute of Space Technology, Islamabad 44000, Pakistan 
 Faculty of Aeronautics and Astronautics Engineering Department, Institute of Space Technology, Islamabad 46000, Pakistan 
 Researcher Assistant Rocket Propulsion Lab, Department of Aeronautics and Astronautics, Institute of Space Technology, Islamabad 44000, Pakistan 
First page
10563
Publication year
2022
Publication date
2022
Publisher
MDPI AG
e-ISSN
20763417
Source type
Scholarly Journal
Language of publication
English
ProQuest document ID
2728428050
Copyright
© 2022 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/). Notwithstanding the ProQuest Terms and Conditions, you may use this content in accordance with the terms of the License.