Aerospace Engineering > GATE 2010 > Compressor Performance
The inlet stagnation temperature for a single stage axial compressor is 300 K and the stage
efficiency is 0.80. Following conditions exist at the mean radius of the rotor blade:
Blade speed =200 m/s
Axial flow velocity =160 m/s
Inlet blade angle β1=44o
Outlet blade angle β2=14o
Cp=1005 I/kgK and γ=1.4
What is the stagnation pressure ratio (<PRS>) for this compressor?
efficiency is 0.80. Following conditions exist at the mean radius of the rotor blade:
Blade speed =200 m/s
Axial flow velocity =160 m/s
Inlet blade angle β1=44o
Outlet blade angle β2=14o
Cp=1005 I/kgK and γ=1.4
What is the stagnation pressure ratio (<PRS>) for this compressor?
Correct : a
Similar Questions
For a single stage subsonic compressor, which of the following statements about the highest possible compressor pressure ratio (CPR) is correct?
The pressure ratio in any one stage of a jet engine compressor is limited by
The maximum operating flow rate through a centrifugal compressor at a given RPM is limited by
Total Unique Visitors
Loading......