### 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

• 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.

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

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

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