Aerospace Engineering > GATE 2011 > Compressor Performance
The pressure ratio in any one stage of a jet engine compressor is limited by
A
entry stagnation temperature in that stage
B
entry Mach number in that stage
C
pressure gradient induced separation in that stage
D
mass flow rate in that stage

Correct : c

Similar Questions

For a single stage subsonic compressor, which of the following statements about the highest possible compressor pressure ratio (CPR) is correct?
#283 MCQ
The maximum operating flow rate through a centrifugal compressor at a given RPM is limited by
#891 MCQ
The inlet stagnation temperature for a single stage axial compressor is 300 K and the stageefficiency is 0.80. Following conditions exist at the mean radius of...
#912 MCQ

Related Topics

No tags found

Unique Visitor Count

Total Unique Visitors

Loading......