Computational Modelling and Structural Analysis of Scimitar Shaped Compressor
In this project compressor rotor blade is employed with new design of scimitar shaped rotor blades. Analyzed using FEA software –ANSYS and studied the parameters like stress and failure point occurring in the rotor blade section. The basic requirements of the compressor for aircraft gas turbine application are well known .In generally,they include high air flow capacity per unit frontal area, high efficiency and easily stackable to obtain the required pressure ratio. The fan and compressor of modern aircraft engine must be capable of operation over widely diverse conditions and improving the flow margin between the fan operating range of the compressor ,under many circumstances unstable flow conditions are initiated in the tip region of a fan or compressor thus if stall in the tip region can be delayed ,the weight flow range of the fan or compressor may be increased.