Aerodynamic Design and Analysis of a Transonic Axial Flow Compressor Stage

Aerodynamic design of an axial flow compressor for a gas turbine engine utilized in procedure ventures for power generation and steam production. Engine is designed for 500 KW comprising of design of axial flow compressor, annular combustion chamber and axial flow turbine. The cycle considered for the investigation is regenerative cycle having regenerator viability of 0.78. The axial flow compressor is designed for 33006 RPM dependent on Isentropic Radial Equilibrium technique. This is radially consistent weight proportion design with variable proficiency for rotor. All Isentropic Radial Equilibrium Equations are accessible in graphical structure, which are customized through C-program. It figures the speed vector charts at a few axial areas at driving and trailing edges of the cutting edge. This program likewise gives the rate, deviation, harmony and different geometric parameters. Weight proportion, delta all out weight and temperature, total Mach number, rotational speed and rotor tip cutting edge speed are the contributions to this program. Determined span along cutting edge stature, flow points and occurrence edges from the above program are then utilized in the edge generation. The parameters acquired are then additionally utilized for displaying through bladegen for both stator and rotor. This displayed rotor and stator at that point coincided in turbo-framework and investigated through CFX