The stator blades of a gas turbine are supplied with gas whose stagnation enthalpy h0 And stagnation temperature To vary with radius r. There is cylindrical flow through the stator blades is reversible and adiabatic.
Show that, in the cross-sectional plane at exit from the stator blades
Hence, when the gas can be assumed to be a perfect gas and the stagnation pressure P0 is constant over the annulus, show that
