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Some concept of Turbomachinery Aerodynamics are Axial Flow Compressors, Axial Turbine Design Considerations, Blade Performance, Engine Performance Significantly, Flows Through Axial Compresso. Main points of this lecture are: Isentropic Efficiency, Axial Flow, Flow Compressor, Compressor, Outlet Angles, Reaction Design, Done Factor, Axial Flow, Mass Flow Rate, Blade Angles
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Air at 1 bar and 288 K enters an axial flow compressor stage with an axial velocity of 150 m/s. There are no inlet guide vanes. The rotor has a tip diameter of 60 cm and a hub diameter of 50 cm and rotates at 100 rps. The air enters the rotor and leaves the stator with no change in velocity or radius. The air is turned through 30 o^ as it passes through the rotor. Determine (a) the blade angles (b) mass flow rate (c) power required and (d) the degree of reaction.
Ans: (a) 49 o, 19 o^ (b) 14.38 kg/s © 300.7 kW (d) 0.
A 50% reaction axial flow compressor has inlet
and outlet blade angles of 45 o^ and 12 o, respectively. The blade speed at the tip of the rotor is 320 m/s. If the inlet total temperature is 300 K, determine the tip relative Mach number.
Ans: 1.