Compressible Flows & Propulsion Systems

General Data
Academic program	ECAM ENGINEERING PROGRAM			:
Type d'EC	Classes
Lectures : 12h00 Tutorials : 24h00 Total duration : 82h00	Status :	Period : SEMESTER 7	Education language : English

Learning Outcomes
1-Acquire solid knowledge on the different jet propulsion related technologies, applied to various types of vehicles. 2-Ability to use an isentropic model of a nozzle to design the latter for a specific purpose (thrust). 3-Ability to apply a thermodynamic approach to analyze the behavior and performance of propulsion systems.

Content
• 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).

Content

• 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).

Pre-requisites / co-requisites
IBENG-1-MATHS-S1, IBENG-1-MATHS-S2, IBENG-2-MATHS-S3, IBENG-2-FLUID-S3, IBENG-2-FLUID-S4, IBENG-1-THERM-S2

Bibliography
• 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.

Assessment(s)
N°	Nature	Coefficient	Observable objectives
1	In-depth explination of operation of rocket and air-breathing engines.	40	1-Acquire solid knowledge on the different jet propulsion related technologies, applied to various types of vehicles.
2	Applying the basic knlowledge of mass, heat and energy balance on the sub-parts of air-breathing and rocket engines. Furthermore, some know-how about the chemistry of the fuels used .	60	2-Ability to use an isentropic model of a nozzle to design the latter for a specific purpose (thrust). 3-Ability to apply a thermodynamic approach to analyze the behavior and performance of propulsion systems.