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account. The procedure is shown below. √ =1− sinβ7 N 0.7 R =1− NrtB7 2πr7 sinβ7 (A.53) (A.54) (A.55) (A.56) (A.57) The default inlet blade angle occur when the incidence angle, i, is equal to the optimum incidence angle, i∗. It is my intent to give the user of the program as much information as possible, and due to that fact the designer will be given values on the following parameters. The outlet blade speed, relative velocity, relative mach number, flow and blade angles and the pitch. At the inlet the relative velocity and the corresponding mach number are given. The throat is a very important component and the blade to blade width at throat is provided. The throat is calculated differently depending on whether the relative mach number, M9,rel, is exceeding unity or not. σ KB7 ∗ c7m cotβ7 c7θ ∗ =σU7−K B7 i7 i7 ◦ − 1 ( U 7 − c ∗7 θ ) K B 7 =β7−90+tan c 7m ◦ −1 (U7 − c7θ)KB7 =β7−90+tan c 7m M9,rel 1 M > 1 ⇒ ⇒ o9 = s9c9m (A.58) w9 o = s ρ9c9m (A.59) 9 9 ρ∗w∗ 9,rel In equation (A.59), ρ∗ and w∗, are the density and relative velocity at sonic conditions. Finally the designer will be given information about the power and efficiency. The parameters just described are not difficult to calculate and the equations are omitted here. Input variable according to the designer If the designer feels that he has got adequate knowledge about how the impeller should be designed or if he would like to vary some of the parameters from the default values it is possible in this program. Naturally the calculation procedure takes a different coarse of action than the one I have used in the previous case. Initially the meridional velocity is calculated using equation (A.35), then the absolute velocity at the tip is followed using equation (A.36). Because the inlet blade angle now is specified, the parameters defined in equations (A.53)-(A.57) can be determined without having to use the iterative procedure. The equations (A.37), (A.38), (A.39), (A.40) and (A.41) can be applied to 80PDF Image | A Detailed Analysis of Radial Turbines
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