Journal Title : International Journal of Modern Trends in Engineering and Science

Author’s Name : Banupriya P| Ajay Pratap | Sathish Kumar K

Volume 02 Issue 10  Year 2015

ISSN no: 2348-3121

Page no: 5-7

Abstract The design of the axial flow compressor begins with the determination of its overall performance specification obtained from the engine and airplane requirements. In this paper the blade design and analysis of fan and compressor is carried out. By just a handful of design specifications a model can be generated. These specifications can be mass flow, rotational speed, number of stages, pressure ratio etc. The Pressure ratio is also the one parameter that the calculation aims to satisfy. The designing of the fan and compressor blades are carried out using GTRE In-house codes and meshing of blades is done in TURBOGRID, flow analysis is taken place in ANSYS CFX. Single stage fan is designed at rotational speed 18000rpm, mass flow 35kg/s, hub tip diameter 530mm and pressure ratio 1.75 as design specifications and two stage booster compressor is designed at rotational speed 18000rpm, mass flow 8.75kg/s and pressure ratio 1.78 as design specifications. The preliminary 1-D and 2-D calculations were carried out and parameters required for blade profile generation were estimated. 3-D analysis was carried out at design speed and validated with the design parameters.

Keywords— Compressor; Rotor; Stator;Design specification; Performance; Aerodynamic Design 


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