AO4012 Component Design of Aircraft Engines Syllabus:
AO4012 Component Design of Aircraft Engines Syllabus – Anna University PG Syllabus Regulation 2021
COURSE OBJECTIVES:
1. This course provides the fundamental principles of fluid mechanics and thermodynamics on jet engine design.
2. This course brings out the differences in the design of various types of gas turbine engines.
3. This course imparts knowledge on the effect of inlet design on aerodynamic and propulsive aspects of aircrafts.
4. This course also addresses the problems associated with the design of combustion chambers.
5. This course deals with the practical difficulties in the matching of compressor and turbine.
UNIT I DESIGN FUNDAMENTALS OF GAS TURBINE ENGINE
Design Process – Constraint Analysis – Preliminary estimates – Aircraft weight and fuel consumption data- Mission analysis – Performance cycle analysis – Engine installation drag and sizing – Current challenges in gas turbine technology.
UNIT II INLET DESIGN
Elements of an Inlet – Engine Integration – Subsonic inlet – Engine Operational Requirements – Supersonic Inlet – Engine Operational Requirements – Engine Impact on Inlet Design – Inlet Impact on Engine Design- Validation of Inlet-Engine System.
UNIT III DESIGN OF ROTATING COMPONENTS
Fan and Compressor Aerodynamics – Diffusion factor – Aerofoil geometry – Flow path dimensions – Radial variation – Turbine Aerodynamics – Constant axial velocity – adiabatic – selected Mach number – Mean line stage Design – tage pressure ratio – Airfoil geometry – Radial variation – Turbine cooling – Engine life – Design Examples.
UNIT IV COMBUSTION CHAMBER DESIGN
Combustion system components- Chemical reactor theory – Combustor Stability map-Stirring and mixing-Total pressure loss-Fuels-Ignition-Combustion Systems of Main Burner Design: Air partitioning- Main burner component Design: Diffuser-types of burner-inner and outer casing Design-Fuel- nozzle-Dome and liner-Primary zone- swirler-Secondary holes-Dilution holesTransition duct-Example Design calculation: Design of Afterburners-Design parameters Components-Diffuser-Fuel injection-Ignition-Flame stabilization-Flame spread and after burner length-Example design calculations.
UNIT V EXHAUST NOZZLE DESIGN
Different types of Nozzles – design of nozzles – Jet control methods for reduction of infrared signature on military aircrafts – Simple design problem – One dimensional nozzle flow.
TOTAL: 45 PERIODS
COURSE OUTCOMES:
At the end of this course, students will be able
CO1: To successfully design a gas turbine engine for given requirements.
CO2: To have thorough knowledge with the operational behavior of the major components of gas turbine engines.
CO3: To identify the factors those limit the performance of the components of gas turbine engines.
CO4: To find solutions for the compressor and turbine matching in gas turbine engines.
CO5: To overcome the problems associated with inlet on aircrafts.
REFERENCES:
1. Cumpsty,N, “Jet Propulsion: A Simple Guide to the Aerodynamics and Thermodynamics
Design and Performance of Jet Engines”, Cambridge University Press, 2nd edition, 2003.
2. Mattingly.JD,Heiser,WH and Pratt,DT,“Aircraft Engine Design”, 2nd Edition, AIAA Education Series, 2002.
3. Oates. GC,“Aircraft Propulsion Systems Technology and Design”, AIAA Education Series, 1989.
4. Saravanamuttoo, HIH andRogers,GFC,“Gas Turbine Technology”, Pearson Education Canada, 6th edition, 2008.
5. Treager,IE,“Aircraft Gas Turbine Engine Technology”, 3rd edition, Glencoe McGraw-Hill, Inc.1995.