Counselling Code: 2719
This Laboratory is intended to teach the basics of Aircraft Propulsion, Heat transfer, Combustion and Compressible flow in various components of Gas Turbine to the Pre-final year students of Department of Aeronautical Engineering. Heat transfer studies fulfill the students' understanding about the relation between heat transfer and engine operation and how they are implemented in the engine components. Aerodynamic studies over the blade and nozzle exit helps students' to obtain knowledge in components design. Combustion studies provide good understanding of combustion chamber design and performance. Students will be able to apply them further in their field of study. Shock Tube is the unique facility to study about Shock Wave propagation and Applications of shock wave. Shock Tunnel is the facility to study flow properties in compressible flow over any Aerodynamic Bodies.
