Optimisation of Single Stage Axial Compressor Blade For a Gas Turbine Engine
Budget: £250 – £750 GBP
This project of mine will look at the primary design of a single-stage axial compressor blade and the behaviour of the flow using ANSYS FLUENT. Then we will provide an optimised blade for the primary design where we achieve a much more efficient compressor.
Related categories:
Mechanical Engineering
Aerospace Engineering
Computational Fluid Dynamics
Ansys
Thermodynamics