Compressible Flows and Propulsion Systems (Mechanical Pathway)

Données Générales
Programme Académique	ECAM LaSalle Mechanical and Electrical Engineering Programme			Responsable(s) Module : AHMAD Hafiz Muhammad,MAJDOUB Fida
Type d'EC : Cours	Compressible Flows and Propulsion Systems (Mechanical Pathway) (LIIEEng07ECompFlowPropSystMECHA)
TD : 12h00 Cours : 12h00 Travail personnel : 36h00 Durée totale: 70h00	Statut	Periode Semester 7	Langue d'enseignement : English

Objectifs Généraux
1. Acquire solid knowledge on the different jet propulsion related technologies, applied to various types of vehicles. 2. Ability to use an isentropic model for nozzle design(Convergent and Convergent-Divergent Nozzle). 3. Ability to apply a thermodynamic approach to analyse the behaviour and performance of propulsion systems based on air-breathing turbomachines (turbojets and turbofans).

Contenu
• Jet propulsion systems and their performance criteria applied to Air-Breathing and Rocket engines: Thrust; Specific Impulse; Propulsion efficiency; Tsiolkovsky rocket equation; Breguet aircraft equation. • Fundamental of Compressible flows: Mach number and thermodynamics of compressible flows; Shockwaves; Conservation laws; application to Isentropic flows. • Rocket engine design: Stagnation and critical states; operating mode of nozzles in rocket engines; influence of combustion pressure and temperature and of nozzle geometry on the thrust finally produced. Calculation of the resulting specific impulse. • Propulsion systems combustion processes: influence of fuel composition and of Air-Fuel Ratio on the performance of air-breathing combustion processes; use of liquid and solid propellants in rocket engine combustion processes. • Air-breathing propulsion turbomachines: Thermodynamic cycles used in turbojet or turbofans engines; influence of pressure ratios, air and fuel mass flow rates, blades geometries on the engine performances (specific impulse, propulsion efficiency and specific fuel consumption).

Contenu

• Jet propulsion systems and their performance criteria applied to Air-Breathing and Rocket engines: Thrust; Specific Impulse; Propulsion efficiency; Tsiolkovsky rocket equation; Breguet aircraft equation.
• Fundamental of Compressible flows: Mach number and thermodynamics of compressible flows; Shockwaves; Conservation laws; application to Isentropic flows.
• Rocket engine design: Stagnation and critical states; operating mode of nozzles in rocket engines; influence of combustion pressure and temperature and of nozzle geometry on the thrust finally produced. Calculation of the resulting specific impulse.
• Propulsion systems combustion processes: influence of fuel composition and of Air-Fuel Ratio on the performance of air-breathing combustion processes; use of liquid and solid propellants in rocket engine combustion processes.
• Air-breathing propulsion turbomachines: Thermodynamic cycles used in turbojet or turbofans engines; influence of pressure ratios, air and fuel mass flow rates, blades geometries on the engine performances (specific impulse, propulsion efficiency and specific fuel consumption).

Prérequis
IBENG-1-MATHS-S1, IBENG-1-MATHS-S2, IBENG-2-MATHS-S3, IBENG-2-FLUID-S3, IBENG-2-FLUID-S4, IBENG-1-THERM-S2

Bibliographie
• J. D. Anderson Jr., Modern Compressible Flow with Historical Perspective, 3rd edition, McGraw-Hill, 2003. • E. A. Baskharone, Principles of Turbomachinery in Air-Breathing Engines, Cambridge University Press, 2006. • G. P. Sutton & O. Biblarz, Rocket Propulsion Elements, 9th edition, Wiley, 2017.

Évaluation(s)
N°	Nature	Coefficient	Objectifs
1	Understanding about propulsion systems and Shock wave phenomenon Ability to solve isentropic flow in conduits.	50	In this exam following topic will be analyzed: 1. propulsion systems 2. Governing equations for flow induced by disturbance 3. Fundamentals of Compressible flow (Sonic, sub-sonic and super-sonic) through nozzles
2	Ability to calculate the AFR/LHV and stoichiometric ratios of air-breathing and rocket engines. Solving complex cases of gas turbine, turbojets (Ideal/actual), turpo prop and ramjet engines.	50	In this exam, the following topic will be analyzed: 1. Combustion in air breathing engines 2. Combustion in rocket engines 3. Jet engines But we may need to apply the concepts learned in first half of the course.