(Solved): Problem1:An axial compressor rotor has a blade hub to tip radius of ( rh/ rt =0.7) with a mean radiu ...
Problem1:An axial compressor rotor has a blade hub to tip radius of ( rh/ rt =0.7) with a mean radius of 0.29m rotating at 6,900 rpm. The stage is designed for a pressure ratio of 1.4, with a stage efficiencyof 83%. Air enters axially at a total temperature of 300 K. Considering air with Cp = 1 kJ/kg Kand = 1.4, if the axial velocity component of air is 140 m/s Find:a- b- c- d- e- f- Rotor blades design angles at the tip, mean and hub radius, considering free vortex flowat exit of the rotor.Degree of reaction at the tip, mean and the hub.Is the specific work constant across the rotor radius?Stator leading edge angle at tip, mean and hub radius.Find the relative inlet Mach number of air at the tip of the rotor.Identify the required design of the rotor blade at the tip using 4 digit NACA airfoil. Problem1: An axial compressor rotor has a blade hub to tip radius of (
(r_(b))/(r_(t))=0.7) with a mean radius of 0.29 m rotating at
6,900rpm. The stage is designed for a pressure ratio of 1.4 , with a stage efficiency of
83%. Air enters axially at a total temperature of 300 K . Considering air with
Cp=1k(J)/(k)gKand
\gamma =1.4, if the axial velocity component of air is
140(m)/(s)Find: a- Rotor blades design angles at the tip, mean and hub radius, considering free vortex flow at exit of the rotor. b- Degree of reaction at the tip, mean and the hub. c- Is the specific work constant across the rotor radius? d- Stator leading edge angle at tip, mean and hub radius. e- Find the relative inlet Mach number of air at the tip of the rotor. f- Identify the required design of the rotor blade at the tip using 4 digit NACA airfoil.
