Low-Cost Rotating Experimentation in Compressor Aerodynamics Using Rapid Prototyping

Table 1

Design parameters of the axial compressor stage.

Parameter	= 7200 RPM	= 4382 RPM
Design corrected mass flow (kg/s)	0.511	0.330
Design stagnation pressure rise coefficient	0.414	0.390
Design efficiency	0.894	0.874
Rotor inlet circum. tip speed (m/s)	65.2	41.4
Rotor inlet tip radius (mm)	87.8
Rotor inlet hub-tip ratio	0.488
Rotor tip clearance/stator hub clearance (mm)	0.254/0.254
Number of blades (rotor/stator)	12/13