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most cases, minimize the number of iterations to about five to six, yielding a satisfactory small numerical error. I am setting the hub to shroud width at the trailing edge to be equal to the one at the rotor inlet. This simplifies the analysis since it removes one possible input variable to be specified. Constructing the impeller design, I was using a correlation to determine the inlet total pressure of the impeller, equation (A.22), and consequently the total pressure loss as far as to the impeller tip. In this program I am assuming that this pressure loss arises entirely from the nozzle row passage and that the total pressure at the leading edge of the nozzle blades is equal to stage inlet total pressure. I am also assuming that the turbine is adiabatic and consequently the total temperature is constant and equal to the one at the stage inlet as far as to the impeller tip. Initial guess: ρ6 = p07 T06 R c6m= m ̇ 2πr6 b6 ρ6 (A.93) (A.94) (A.95) (A.96) (A.97) (A.98) Now the exit meridional velocity is known and therefore it is possible to calculate the required throat width. I said that I would be using the sine rule and while that is still true, when the mach number exceeds unity I have chosen to use a different approach in which I am using the conservation of mass flow between the throat and exit. This brings the determination of the throat width down to two equations, shown below. tanα6 = c6m c6θ M6 = c6 T6 γ R o = s6 sinα6 o=s ρ6c6m M6 ≤ 1 M >1 (A.99) (A.100) (A.101) (A.102) c6 = c26m + c26θ T6 = T06 − c26 p6=p06 T ρ6 = p6 6 ρ∗a∗ The density, ρ∗, and velocity, a∗, are the sonic density and speed respectively and they 90 T6 R 2cp Tγ 6 γ−1 06 6PDF Image | A Detailed Analysis of Radial Turbines
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