Using shock generator for the fuel mixing of the extruded single 4-lobe nozzle at supersonic combustion chamber

• Published in: Scientific reports Vol. 14; no. 1; p. 6405
• Main Authors: Alizadeh, As’ad, Jasim, Dheyaa J., Sohrabi, Neaman, Ahmed, Mohsen, Ameer, S. Abdul, Ibrahim, Safaa Mohammed, Dabis, Hasan Khalid, Hussein, Ali Adhab, Sultan, Abbas J.
• Format: Journal Article
• Language: English
• Published: London Nature Publishing Group UK 17-03-2024; Nature Publishing Group; Nature Portfolio
• Subjects: 639/166/984; 639/166/988; CFD; Combustion; Combustion chamber; Extruded nozzle; Fuel mixing; Humanities and Social Sciences; Injection; multidisciplinary; Science; Science (multidisciplinary); Turbulence models; CFD; Extruded nozzle; Combustion chamber; Fuel mixing
• ISSN: 2045-2322; 2045-2322
• DOI: 10.1038/s41598-024-57103-0

The importance of the fuel injection configuration on the propulsion efficiency of high-speed vehicles is apparent. In this article, the use of an annular extruded 4-lobe nozzle for the injection of fuel jet in a supersonic combustor of a scramjet engine in the existence of a shock generator is examined. The main aim of this study is to obtain the efficient jet arrangement for efficient fuel mixing inside the engine of hypersonic vehicles. A numerical approach is used to model the supersonic air stream and cross-jet flow with the SST turbulence model. The role of nozzle altitude and internal air jet on the fuel mixing of the hydrogen within the high-speed domain are disclosed. The importance of the horseshoe vortex and counter-rotating vortex on the fuel distribution is also presented. Our results show that the usage of a coaxial jet instead of an annular jet would increase fuel mixing by more than 40% in the combustion chamber.