(a) the tip radius and corresponding rotor air angles B1 and B2. (b) the mass flow entering the stage. (c) the stage stagnation pressure ratio and power required. (d) the rotor air angles at the root section.

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3.20) The first stage of an axial compressor is designed on free vortex principles, with no inlet guide
vanes. The rotational speed is 6000 rev/min and the stagnation temperature rise is 20 K. The
hub-tip ratio is 0.60, the work-done factor is 0.93 and the isentropic efficiency of the stage is
0.89. Assuming an inlet velocity of 140 m/s, the Mach number relative to the tip is limited to
0.95 and ambient conditions of 1.01 bar and 288 K, calculate:
(a) the tip radius and corresponding rotor air angles B1 and B2. [0.456 m, 63.95° and 56.40°]
(b) the mass flow entering the stage.
[65.5 kg/s]
(c) the stage stagnation pressure ratio and power required.
[1.233, 1317 kW]
(d) the rotor air angles at the root section.
[50.83° and 18.32°]
Transcribed Image Text:3.20) The first stage of an axial compressor is designed on free vortex principles, with no inlet guide vanes. The rotational speed is 6000 rev/min and the stagnation temperature rise is 20 K. The hub-tip ratio is 0.60, the work-done factor is 0.93 and the isentropic efficiency of the stage is 0.89. Assuming an inlet velocity of 140 m/s, the Mach number relative to the tip is limited to 0.95 and ambient conditions of 1.01 bar and 288 K, calculate: (a) the tip radius and corresponding rotor air angles B1 and B2. [0.456 m, 63.95° and 56.40°] (b) the mass flow entering the stage. [65.5 kg/s] (c) the stage stagnation pressure ratio and power required. [1.233, 1317 kW] (d) the rotor air angles at the root section. [50.83° and 18.32°]
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