AE3402 Syllabus - Air Breathing Propulsion - 2021 Regulation Anna University

AE3402 Syllabus - Air Breathing Propulsion - 2021 Regulation Anna University

AE3402	AIR BREATHING PROPULSION	LTPC

3104

COURSE OBJECTIVES:

• To establish fundamental approach and application of jet engine components.
• To learn about the analysis of flow phenomenon and estimation of thrust developed by jet engine.
• To introduce about the application of various equations in Gas Turbine Engines.
• To learn the concepts of jet engine combustion chambers
• To acquire knowledge on compressors and turbines

UNIT I	PRINCIPLES OF AIR BREATHING ENGINES	9+6

Operating principles of piston engines – thermal efficiency calculations – classification of piston engines - illustration of working of gas turbine engines – factors affecting thrust – methods of thrust augmentation – performance parameters of jet engines.

UNIT II	JET ENGINE INTAKES AND EXHAUST NOZZLES	9+6

Ram effect, Internal flow and Stall in subsonic inlets – relation between minimum area ratio and eternal deceleration ratio – diffuser performance – modes of operation - supersonic inlets – starting problem on supersonic inlets – shock swallowing by area variation – real flow through nozzles and nozzle efficiency – losses in nozzles – ejector and variable area nozzles - interaction of nozzle flow with adjacent surfaces – thrust reversal.

UNIT III	JET ENGINE COMBUSTION CHAMBERS	9+6

Chemistry of combustion, Combustion equations, Combustion process, classification of combustion chambers – combustion chamber performance – effect of operating variables on performance – flame stabilization, Cooling process, Materials, Aircraft fuels, HHV, LHV, Orsat apparatus

UNIT IV	JET ENGINE COMPRESSORS	9+6

Euler’s turbo machinery equation, Principle operation of centrifugal compressor, Principle operation of axial flow compressor– Work done and pressure rise – velocity diagrams – degree of reaction – free vortex and constant reaction designs of axial flow compressor – performance parameters axial flow compressors– stage efficiency.

UNIT V	JET ENGINE TURBINES	9+6

Principle of operation of axial flow turbines– limitations of radial flow turbines- Work done and pressure rise – Velocity diagrams – degree of reaction – constant nozzle angle designs – performance parameters of axial flow turbine– turbine blade cooling methods – stage efficiency calculations – basic blade profile design considerations – matching of compressor and turbine

TOTAL: 75 PERIODS

COURSE OUTCOMES: On completion of the course, the student is expected

CO1: To be able to apply control volume and momentum equation to estimate the forces produced by aircraft propulsion systems
CO2: To be able to describe the principal figures of merit for aircraft engine
CO3: To be able to describe the principal design parameters and constraints that set the performance of gas turbine engines.
CO4: To apply ideal and actual cycle analysis to a gas turbine engine to relate thrust and fuel burn to component performance parameters.
CO5: Understanding the workings of multistage compressor or turbine, and to be able to use velocity triangles and the Euler Turbine Equation to estimate the performance of a compressor or turbine stage.

TEXT BOOKS:

1. Hill, P.G. & Peterson, C.R. “Mechanics & Thermodynamics of Propulsion” Pearson education (2009)

REFERENCES:

1. Cohen, H. Rogers, G.F.C. and Saravanamuttoo, H.I.H. “Gas Turbine Theory”, Pearson Education Canada; 6th edition, 2008.
2. Mathur, M.L. and Sharma, R.P., “Gas Turbine, Jet and Rocket Propulsion”, Standard Publishers & Distributors, Delhi, 2nd edition 2014.
3. Oates, G.C., “Aero thermodynamics of Aircraft Engine Components”, AIAA Education Series, New York, 1985.
4. “Rolls Royce Jet Engine”, Rolls Royce; 4th revised edition, 1986