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Axial flow compressor design

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Compressor Axial design flow

rythmnbls Avatar

Sept 8, 2015 18:32:13 GMT -5 rythmnbls said:

My basic understanding of pitch / chord is, the more the the gasses are deflected the lower the number. Which makes sense when you think about it. More gas deflection requires more blades to ensure/control that deflection. If you look at the 1241.pdf file on this page jetandturbineowners.proboards.com/thread/503/links on page 75 you will see how Howell's approximation for pitch / chord based on gas deflection is calculated. I would recommend you calculate s/c first based on deflection, then deviations.

One question. After correcting the angles b1 and b2 with the incidence and deviation, am i done? Changing these values doesn't mean that angles a1 and a2 also change?

I believe you are done. Again I could be wrong, I've never built a working axial comp ( although I'm tempted to try, senility or a delusional state must be setting in )




Hi Steve,

I read the pdf about the solidity and deviation from Howell and after applying it and comparing it with the calculations i had done before, i notice some big differences.
Below is an example.

For the hub station of a 2nd stage rotor the specifications are these:

using howell's equations i get deviation = 13.01deg and incidence = -5.46deg  b1=50.02deg & b2=20.84deg (i am confused about how he calculates the angle b2  b2=b2'+deviation. Since deviation is positive, he had to subtract it right?)
using the equations i showed you above i get deviation 9.05deg and incidence = -4.15deg   b1=46.86deg & b2=-1.20deg.

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