JNTUK B.Tech Aerospace Propulsion – I gives you detail information of Flight Aerospace Propulsion – I R13 syllabus It will be help full to understand you complete curriculum of the year.
Course Objective
The main objective of the subject is to study the fundamentals of gas turbine engines working principles and thrust equation. Subsonic and Supersonic inlets and modes of their evaluation are also considered. It also includes combustion chambers different types of combustion chambers and performance analysis. The compressors and nozzles of gas turbine are studied.
UNIT -I : Fundamentals Of Gas Turbine Engines: Illustration of working of gas turbine engine – The thrust equation – Factors affecting thrust – Effect of pressure, velocity and temperature changes of air entering compressors – Method of thrust augmentation – Characteristics of turboprop, turbojet – Performance characteristics.
UNIT – II : Subsonic Inlets : Internal flow and Stall in Subsonic inlets – Boundary layer separation – Major features of external flow near a subsonic inlet – Relation between minimum area ratio and eternal deceleration ratio – Diffuser performance.
Supersonic Inlets : Supersonic inlets – Starting problem in supersonic inlets – Shock swallowing by area variation- External deceleration –Modes of inlet operation.
UNIT – III : Combustion Chambers And Performance: Classification of combustion chambers – Important factors affecting combustion chamber design – Combustion process– Combustion chamber performance.
UNIT – IV : Performance Sensitivity: Effect of operating variables on performance – Flame tube cooling – Flame stabilization – Use of flame holders –Numerical problems.
UNIT – V : Nozzles: Theory of flow in isentropic nozzles – Convergent nozzles and nozzle choking – Nozzle throat conditions – Nozzle efficiency – Losses in nozzles – Over-expanded and under-expanded nozzles – Ejector and variable area nozzles – Interaction of nozzle flow with adjacent surfaces – Thrust reversal.
UNIT – VI : Centrifugal Compressors: Principle of operation of centrifugal compressors – Work done and pressure rise -Velocity diagrams – Diffuser vane design considerations – Concept of Prewhirl –Rotating stall.
Axial Flow Compressors: Elementary theory of axial flow compressor – Velocity triangles – Degree of reaction – Three dimensional flow – Air angle distribution for free vortex and constant reaction designs – Compressor blade design – Centrifugal and Axial compressor performance characteristics.
TEXT BOOKS
- Mathur M L & Sharma R P; Gas Turbines and Jet & Rocket Propulsion, Standard Publisher, Delhi, 2000.
- Cohen, H. Rogers, G.F.C. and Saravanamuttoo, H.I.H. Gas Turbine Theory, Longman, ELBSEd, 1989.
REFERENCE BOOKS
- Oates G C, AeroThermodyanamics of Aircraft Engine Components, AIAA Edn. Services, NY, 1986.
- Rolls- Royce, Jet Engine, 3rd edition, 1983.
- Ganesan V, Gas Turbines, TMGH Pub Co & Ed, Delhi, 1999.
- Philipa Hill and Carl Peterson, Mechanics and Thermodynamics of Propulsion, Addison Wesley Longman Inc, 1999.
Course Outcomes
At the end of the course the students shall be able to:
- Understand the fundamentals of gas turbine engines working principles and thrust equation.
- Evaluate Subsonic and Supersonic inlets and modes.
- Describe the different types of combustion chambers and performance analysis.
- Emphasize the compressors and nozzles of gas turbine.
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