Effects of nozzle types on mass diffusion mechanism of hydrogen multi-jets at supersonic combustion chamber

Z. Li; Jiaxuan Leng; Nidal H. Abu-Hamdeh; Abdullah M. Abusorrah; Awad Musa

doi:10.1016/j.icheatmasstransfer.2022.106509

Effects of nozzle types on mass diffusion mechanism of hydrogen multi-jets at supersonic combustion chamber

Z. Li
, Jiaxuan Leng
, Nidal H. Abu-Hamdeh
, Abdullah M. Abusorrah
, Awad Musa

Physics

Research output: Contribution to journal › Article › peer-review

7 Scopus citations

Abstract

The fuel injection technique is the most effective procedure in the combustion chamber of supersonic/hypersonic vehicles. This work tries to explore the impact of the nozzle type on the fuel mixing of four multi-jet at a supersonic air stream of Mach = 4. Three different nozzles of rectangular (1:4), (1:16), and arc injector (1:16) are examined to obtain the efficient model for the injection system in combustor section. CFD method is used to simulate the flow and jet for the proposed nozzles inside the high-speed domain of the combustor. Our achieved results specify that increasing the jet injection along the direction of the airstream would significantly improve the mixing of hydrogen downstream of the injector and the rectangular nozzle (1:16) has the most efficient performance in this aspect. Strengths of circulation are improved by the concentrated injection system in which the fuel is injected through the limited nozzle.

Original language	English
Article number	106509
Journal	International Communications in Heat and Mass Transfer
Volume	139
DOIs	https://doi.org/10.1016/j.icheatmasstransfer.2022.106509
State	Published - Dec 2022

Keywords

CFD
Combustion chamber
Fuel mixing
Mass diffusion
RANS
Supersonic vehicles

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

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10.1016/j.icheatmasstransfer.2022.106509

Cite this

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title = "Effects of nozzle types on mass diffusion mechanism of hydrogen multi-jets at supersonic combustion chamber",

abstract = "The fuel injection technique is the most effective procedure in the combustion chamber of supersonic/hypersonic vehicles. This work tries to explore the impact of the nozzle type on the fuel mixing of four multi-jet at a supersonic air stream of Mach = 4. Three different nozzles of rectangular (1:4), (1:16), and arc injector (1:16) are examined to obtain the efficient model for the injection system in combustor section. CFD method is used to simulate the flow and jet for the proposed nozzles inside the high-speed domain of the combustor. Our achieved results specify that increasing the jet injection along the direction of the airstream would significantly improve the mixing of hydrogen downstream of the injector and the rectangular nozzle (1:16) has the most efficient performance in this aspect. Strengths of circulation are improved by the concentrated injection system in which the fuel is injected through the limited nozzle.",

keywords = "CFD, Combustion chamber, Fuel mixing, Mass diffusion, RANS, Supersonic vehicles",

author = "Z. Li and Jiaxuan Leng and Abu-Hamdeh, \{Nidal H.\} and Abusorrah, \{Abdullah M.\} and Awad Musa",

note = "Publisher Copyright: {\textcopyright} 2022",

year = "2022",

month = dec,

doi = "10.1016/j.icheatmasstransfer.2022.106509",

language = "English",

volume = "139",

journal = "International Communications in Heat and Mass Transfer",

issn = "0735-1933",

publisher = "Elsevier Ltd",

}

TY - JOUR

T1 - Effects of nozzle types on mass diffusion mechanism of hydrogen multi-jets at supersonic combustion chamber

AU - Li, Z.

AU - Leng, Jiaxuan

AU - Abu-Hamdeh, Nidal H.

AU - Abusorrah, Abdullah M.

AU - Musa, Awad

PY - 2022/12

Y1 - 2022/12

N2 - The fuel injection technique is the most effective procedure in the combustion chamber of supersonic/hypersonic vehicles. This work tries to explore the impact of the nozzle type on the fuel mixing of four multi-jet at a supersonic air stream of Mach = 4. Three different nozzles of rectangular (1:4), (1:16), and arc injector (1:16) are examined to obtain the efficient model for the injection system in combustor section. CFD method is used to simulate the flow and jet for the proposed nozzles inside the high-speed domain of the combustor. Our achieved results specify that increasing the jet injection along the direction of the airstream would significantly improve the mixing of hydrogen downstream of the injector and the rectangular nozzle (1:16) has the most efficient performance in this aspect. Strengths of circulation are improved by the concentrated injection system in which the fuel is injected through the limited nozzle.

AB - The fuel injection technique is the most effective procedure in the combustion chamber of supersonic/hypersonic vehicles. This work tries to explore the impact of the nozzle type on the fuel mixing of four multi-jet at a supersonic air stream of Mach = 4. Three different nozzles of rectangular (1:4), (1:16), and arc injector (1:16) are examined to obtain the efficient model for the injection system in combustor section. CFD method is used to simulate the flow and jet for the proposed nozzles inside the high-speed domain of the combustor. Our achieved results specify that increasing the jet injection along the direction of the airstream would significantly improve the mixing of hydrogen downstream of the injector and the rectangular nozzle (1:16) has the most efficient performance in this aspect. Strengths of circulation are improved by the concentrated injection system in which the fuel is injected through the limited nozzle.

KW - CFD

KW - Combustion chamber

KW - Fuel mixing

KW - Mass diffusion

KW - RANS

KW - Supersonic vehicles

UR - https://www.scopus.com/pages/publications/85142187515

U2 - 10.1016/j.icheatmasstransfer.2022.106509

DO - 10.1016/j.icheatmasstransfer.2022.106509

M3 - Article

AN - SCOPUS:85142187515

SN - 0735-1933

VL - 139

JO - International Communications in Heat and Mass Transfer

JF - International Communications in Heat and Mass Transfer

M1 - 106509

ER -

Effects of nozzle types on mass diffusion mechanism of hydrogen multi-jets at supersonic combustion chamber

Abstract

Keywords

UN SDGs

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