with a velocity of 175 m/s at an angle of 21° to the axial direction (in the direction of engine rotation). The air then enters a row of rotor blades which have hub and tip diameters of 230 mm and 290 mm, respectively, and rotate at 19100 rpm. The air is turned through an angle of 17° towards the axial direction as it passes through the rotor. It may be assumed that: The axial velocity of the air remains constant throughout this compression stage.
Air enters the inlet guide vanes of an axial flow compressor in an axial direction at a pressure of 86.35 kPa and a temperature of 281K. The air exits these guide vanes with a velocity of 175 m/s at an angle of 21° to the axial direction (in the direction of engine rotation). The air then enters a row of rotor blades which have hub and tip diameters of 230 mm and 290 mm, respectively, and rotate at 19100 rpm. The air is turned through an angle of 17° towards the axial direction as it passes through the rotor.
It may be assumed that:
The axial velocity of the air remains constant throughout this compression stage.
The air enters and leaves the blades at the blade angles.
For air, γ = 1.4, Cp = 1.005kJ/kg.K
All blade geometry should be calculated at a mean blade height position.
Determine the rotor blade inlet angle relative to the axial direction.
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