a single stage centrifugal compressor is to be designed that gives maximum overall static pressure ratio. The following design conditions must be considered:Fluid: air

Inlet stagnation pressure: $100$ kPa

inlet stagnation temperature: $15\backslash$deg C

Specific heat ratio: $1\mathrm{.}4$

Gas constant: $287$ J$/$kg$.$K

Mass flow rate: $3$ kg$/$s

Impeller inlet

Hub$-$to$-$shroud radius ratio between $0\mathrm{.}3$ and $0\mathrm{.}6$

Inlet swirl: $30\backslash$deg

The inlet absolute and relative flow must be subsonic and conditions at inlet must be optimum.

Impeller exit

Tip$-$radius to inlet shroud$-$radius ratio $2$Number of vanes: $7-25$

Vane backsweep angle $0\backslash$deg $-45\backslash$deg

Flow coefficient $0\mathrm{.}3-0\mathrm{.}4$

Impeller efficiency $90\%$

DiffuserType: Vaned

Channel geometry: $2$D

Diffuser efficiency: $85\%$

Neglect clerance between impeller tip and diffuser vanes

The diffuser exit radius should be less than three$-$times the inlet shroud radius.surge free flow must be considered

The following must be determined

RPM

Impeller vane inlet angle

Impeller vane outlet angle

The radii

Axial width at impeller exit

Total$-$to$-$total efficiency

Shaft power

Overall static pressure ratio