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Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion

Detonation is a shock wave obtained from the energy that releases after the combustion. Chapman-Jouguet(CJ) theory can be used to identify the behaviour of the detonation in gasses. Pulse Detonation Engines (PDEs) is one of the engines that implement the detonat...

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Main Authors:	Ismail, Izham Izzat, Azami, Muhammad Hanafi
Format:	Article
Language:	English
Published:	Penerbit Akademia Baru 2022
Subjects:	TJ163.13 Power resources TJ807 Renewable energy sources TP267.5 Explosives and pyrotechnics TP315 Fuel
Online Access:	http://irep.iium.edu.my/97310/7/97310_Thrust%20chamber%20dynamic%20and%20propulsive%20performance.pdf http://irep.iium.edu.my/97310/ https://semarakilmu.com.my/journals/index.php/fluid_mechanics_thermal_sciences/article/view/396/207 https://doi.org/10.37934/arfmts.92.2.7193
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spelling	my.iium.irep.973102022-03-23T03:44:47Z http://irep.iium.edu.my/97310/ Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion Ismail, Izham Izzat Azami, Muhammad Hanafi TJ163.13 Power resources TJ807 Renewable energy sources TP267.5 Explosives and pyrotechnics TP315 Fuel Detonation is a shock wave obtained from the energy that releases after the combustion. Chapman-Jouguet(CJ) theory can be used to identify the behaviour of the detonation in gasses. Pulse Detonation Engines (PDEs) is one of the engines that implement the detonation in its combustion system. The Humphrey cycle is the thermodynamic cycle which is similar to the Pulse Detonation Engines (PDEs). It is the modification of the Brayton cycle where the constant-pressure heat addition process of the Brayton cycle is replaced by a constant-volume heat addition process. The Humphrey cycle can provide the pressure rise combustion by utilizing the shock inside the combustion chamber. Compared to the Brayton cycle, the Humphrey cycle has higher thermodynamic efficiency. However, the detonation process has unsteady combustion which makes it more difficult to handle. The purpose of the study is to calculate the performance of the aircraft by using alternative fuel in the ZND model. An analytical model is started by having the molecular structure of each biofuel and it has been used to determine detonation velocity, Mach number at C-J point, temperature ratio, pressure ratio, density ratio, Brayton and Humphrey efficiency, specific impulse, and specific thrust. In addition, the physical properties of the flow are investigated by changing the initial temperature, initial pressure, and mass flux. The pressure ratio, temperature ratio, and density ratio will all decreases the initial pressure varies. The variation of mass flux and initial temperature, on the other hand, generates the opposite outcome as the change of pressure. The feasibility of the fuels in the detonation combustion can be known as they show high propulsive performance after the initial condition is changing. Penerbit Akademia Baru 2022-02-18 Article PeerReviewed application/pdf en http://irep.iium.edu.my/97310/7/97310_Thrust%20chamber%20dynamic%20and%20propulsive%20performance.pdf Ismail, Izham Izzat and Azami, Muhammad Hanafi (2022) Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 92 (2). pp. 71-93. ISSN 2289-7879 https://semarakilmu.com.my/journals/index.php/fluid_mechanics_thermal_sciences/article/view/396/207 https://doi.org/10.37934/arfmts.92.2.7193
institution	Universiti Islam Antarabangsa Malaysia
building	IIUM Library
collection	Institutional Repository
continent	Asia
country	Malaysia
content_provider	International Islamic University Malaysia
content_source	IIUM Repository (IREP)
url_provider	http://irep.iium.edu.my/
language	English
topic	TJ163.13 Power resources TJ807 Renewable energy sources TP267.5 Explosives and pyrotechnics TP315 Fuel
spellingShingle	TJ163.13 Power resources TJ807 Renewable energy sources TP267.5 Explosives and pyrotechnics TP315 Fuel Ismail, Izham Izzat Azami, Muhammad Hanafi Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
description	Detonation is a shock wave obtained from the energy that releases after the combustion. Chapman-Jouguet(CJ) theory can be used to identify the behaviour of the detonation in gasses. Pulse Detonation Engines (PDEs) is one of the engines that implement the detonation in its combustion system. The Humphrey cycle is the thermodynamic cycle which is similar to the Pulse Detonation Engines (PDEs). It is the modification of the Brayton cycle where the constant-pressure heat addition process of the Brayton cycle is replaced by a constant-volume heat addition process. The Humphrey cycle can provide the pressure rise combustion by utilizing the shock inside the combustion chamber. Compared to the Brayton cycle, the Humphrey cycle has higher thermodynamic efficiency. However, the detonation process has unsteady combustion which makes it more difficult to handle. The purpose of the study is to calculate the performance of the aircraft by using alternative fuel in the ZND model. An analytical model is started by having the molecular structure of each biofuel and it has been used to determine detonation velocity, Mach number at C-J point, temperature ratio, pressure ratio, density ratio, Brayton and Humphrey efficiency, specific impulse, and specific thrust. In addition, the physical properties of the flow are investigated by changing the initial temperature, initial pressure, and mass flux. The pressure ratio, temperature ratio, and density ratio will all decreases the initial pressure varies. The variation of mass flux and initial temperature, on the other hand, generates the opposite outcome as the change of pressure. The feasibility of the fuels in the detonation combustion can be known as they show high propulsive performance after the initial condition is changing.
format	Article
author	Ismail, Izham Izzat Azami, Muhammad Hanafi
author_facet	Ismail, Izham Izzat Azami, Muhammad Hanafi
author_sort	Ismail, Izham Izzat
title	Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
title_short	Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
title_full	Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
title_fullStr	Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
title_full_unstemmed	Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
title_sort	thrust chamber dynamic and propulsive performance of biofuels under detonation combustion
publisher	Penerbit Akademia Baru
publishDate	2022
url	http://irep.iium.edu.my/97310/7/97310_Thrust%20chamber%20dynamic%20and%20propulsive%20performance.pdf http://irep.iium.edu.my/97310/ https://semarakilmu.com.my/journals/index.php/fluid_mechanics_thermal_sciences/article/view/396/207 https://doi.org/10.37934/arfmts.92.2.7193
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score	13.211869

Thrust chamber dynamic and propulsive performance of biofuels under detonation combustion

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