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to approximate the proper throat width, I have to determine the flow angle at the trailing edge. I say ”approximate” because there are no existing relationship which correlates the flow angle and the throat precisely, but I have chosen to use the simple sine rule. Baines shows that the sine rule does not determine the flow angle very good, especially not at high mach numbers, [12], however, since this program just aims to find a first and preliminary design it is preferable to use such a simple relation. The tangential velocity at the rotor tip is known from the rotor analysis and the ratio of the nozzle exit radius-to rotor inlet radius, r6/r7, is taken from the input variables. Using the relationship which states that the angular momentum is conserved it is possible to determine the tangential velocity at the trailing edge of the nozzle blades. Figure A.9.: The nozzle airfoil setting angle. Adapted from Aungier [2]. c =c r7 (A.92) 6θ 7θ r6 The flow angle can be determined if the meridional velocity is known. To calculate this velocity a mass balance will be performed. The static density at the trailing is, however, not known and it is therefore necessary to apply an iterative calculation procedure. First an initial guess of the static density is made and then the iteration begins and proceeds until the correct static density is found. I have chosen to take the static density as equal to the total density as an initial guess. This will be a relatively good guess and will, in 89PDF Image | A Detailed Analysis of Radial Turbines
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