Compressible Flows et Propulsion Systems

Données Générales
Programme Académique	Incoming Exchange Student Courses			Responsable(s) Module : AHMAD Hafiz Muhammad
Type d'EC : Cours	Compressible Flows et Propulsion Systems (LIIExp07ECompFlowPropSyst)
TD : 12h00 Cours : 12h00 Travail personnel : 36h00 Durée totale: 60h00	Status Obligatoire	Periode Semester 7_Sustainable Energy	Langue d'enseignement : English

Objectifs Généraux
Acquire solid knowledge on the different jet propulsion related technologies, applied to various types of vehicles. Ability to usean isentropic model of a nozzle to design the latter for a specific purpose (thrust). Ability to apply a thermodynamic approachto analyze the behavior and performance of propulsion systems.

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; Conservationlaws; application to Isentropic flows. • Rocket engine design: Stagnation and critical states; operating mode of nozzles in rocket engines; influence of combustionpressure 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 pressureratios, air and fuel mass flow rates, blades geometries on the engine performances (specific impulse, propulsion efficiency andspecific 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; Conservationlaws; application to Isentropic flows.
• Rocket engine design: Stagnation and critical states; operating mode of nozzles in rocket engines; influence of combustionpressure 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 pressureratios, air and fuel mass flow rates, blades geometries on the engine performances (specific impulse, propulsion efficiency andspecific 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.