Propulsion I detail syllabus for Aeronautical Engineering (Aero), 2017 regulation is taken from Anna University official website and presented for students of Anna University. The details of the course are: course code (AE8404), Category (PC), Contact Periods/week (5), Teaching hours/week (3), Practical Hours/week (2). The total course credits are given in combined syllabus.
For all other aero 4th sem syllabus for be 2017 regulation anna univ you can visit Aero 4th Sem syllabus for BE 2017 regulation Anna Univ Subjects. The detail syllabus for propulsion i is as follows.”
Course Objective:
- To establish fundamental approach and application of jet engine components. Also analysis of flow phenomenon and estimation of thrust developed by jet engine.
Unit I
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Unit II
Jet Engine Intakes and Exhaust Nozzles
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
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
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Unit V
Jet Engine Turbines
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
Course Outcome:
- To be able to apply control volume and momentum equation to estimate the forces produced by aircraft propulsion systems
- To be able to describe the principal figures of merit for aircraft engine
- To be able to describe the principal design parameters and constraints that set the performance of gas turbine engines.
- To apply ideal and actual cycle analysis to a gas turbine engine to relate thrust and fuel burn to component performance parameters.
- 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:
- Hill, P.G. and Peterson, C.R. Mechanics and Thermodynamics of Propulsion Pearson education (2009)
References:
- Cohen, H. Rogers, G.F.C. and Saravanamuttoo, H.I.H. Gas Turbine Theory, Pearson Education Canada; 6th edition, 2008.
- Mathur, M.L. and Sharma, R.P., Gas Turbine, Jet and Rocket Propulsion, Standard Publishers and Distributors, Delhi, 2nd edition 2014.
- Oates, G.C., Aero thermodynamics of Aircraft Engine Components, AIAA Education Series, New York, 1985.
- Rolls Royce Jet Engine, Rolls Royce; 4th revised edition, 1986.
For detail syllabus of all other subjects of BE Aero, 2017 regulation do visit Aero 4th Sem syllabus for 2017 Regulation.
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