I need help with the foloowing problems , i would greatly appreciate the help. A

Question

I need help with the foloowing problems , i would greatly appreciate the help.

A high-pressure axial compressor for a jet engine rotates at 15,000 rpm with an overall stagnation

pressure ratio of 8.5. The mass flow rate of air through the compressor is 16 kg/s1 and the stagnation

conditions at inlet are 200 kPa and 450 K. The polytropic efficiency is 91%.

(a) If the mean radius is 0.24 m and this is constant throughout the compressor, calculate the

total-to-total isentropic efficiency of the compressor and show that, for the stage loading to

be less than 0.4 in all stages, eight stages are required.

(b) The compressor is designed with repeating stages and zero inlet swirl. If the inlet axial Mach

number is 0.52, calculate the mean flow coefficient and sketch the velocity triangles for one

stage. Show that the blade height at exit from the compressor is about 7.8 mm.

Explanation / Answer

http://www.scribd.com/doc/100300544/Turbo-Machinery

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