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

As'ad Alizadeh; Dheyaa J Jasim; Neaman Sohrabi; Mohsen Ahmed; S Abdul Ameer; Safaa Mohammed Ibrahim; Hasan Khalid Dabis; Ali Adhab Hussein; Abbas J Sultan

doi:10.1038/s41598-024-57103-0

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

Sci Rep. 2024 Mar 17;14(1):6405. doi: 10.1038/s41598-024-57103-0.

Authors

As'ad Alizadeh^{1

2}, Dheyaa J Jasim³, Neaman Sohrabi⁴, Mohsen Ahmed⁵, S Abdul Ameer⁶, Safaa Mohammed Ibrahim⁷, Hasan Khalid Dabis⁸, Ali Adhab Hussein⁹, Abbas J Sultan^{10

11}

Affiliations

¹ Department of Civil Engineering, College of Engineering, Cihan University-Erbil, Erbil, Iraq. asad.alizadeh2010@gmail.com.
² Department of Mechanical Engineering, College of Engineering, Urmia University, Urmia, Iran. asad.alizadeh2010@gmail.com.
³ Department of Petroleum Engineering, Al-Amarah University College, Maysan, Iraq.
⁴ Department of Mechanical and Mechatronics Engineering, Southern Illinois University, Edwardsville, IL, 62026, USA.
⁵ Imam Abdulrahman Bin Faisal University, P.O. Box 1982, Dammam, 31441, Eastern Province, Kingdom of Saudi Arabia.
⁶ Department of Automobile Engineering, College of Engineering, Al-Musayab University of Babylon, Hillah, Iraq.
⁷ Department of Optical Techniques, Al-Noor University College, Mosul, Iraq.
⁸ Ahl Al Bayt University, Kerbala, Iraq.
⁹ Department of Medical Laboratory Technics, Al-Zahrawi University College, Karbala, Iraq.
¹⁰ Department of Chemical Engineering, University of Technology-Iraq, Baghdad, Iraq.
¹¹ Department of Chemical and Biochemical Engineering, Missouri University of Science and Technology, Rolla, MO, 65409-1230, USA.

Abstract

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.

Keywords: CFD; Combustion chamber; Extruded nozzle; Fuel mixing.