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Design of Radial Inflow and Mixed Flow Turbines 1971

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Design of Radial Inflow and Mixed Flow Turbines 1971 ( design-radial-inflow-and-mixed-flow-turbines-1971 )

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Page 4 2. STEADYFLOW(CONSTANTPRESSURE)ANALYSIS (References 1 and 6) Under this heading the most important aspect of the one-dimensional treatment will be discussed, particularly the off-design interspace model as applied to subsonic as well as sonic nozzle exit conditions. This work is taken almost in its entirety from Reference 6. It must be emphasised that the only losses explicitly taken into account are nozzle-rotor interspace irrevsrsibilities and rotor exit losses, ie the& is no recovery of exit KE. Nozzle and rotor passage losses are explicitly excluded, although the treatment can very readily be modified by the inclusion of loss coefficient as discussed in a recent paper by Benson (8). The chief advantage of the method lies in the fact that it gives a closed solution of the off design problem and that no recourse is had to empirical incidence loss or deviation coefficients. Correlation with experimental results is surprisingly good. (a) Unchoked Nozzle (Figures 1, 2 and 3) The thermodynamic model for interspace flow is that of a constant pressure irreversible ('shock') process 22' (Figure 2) with sudden deflection of the nozzle jet leavingvelocity c2 and absolute angle a3 (Figure 3) to conditions ~2' and a2' giving a relative velocity vector wz', B2' in conformity with the rotor inlet geometry. Slip is not allowed for, but could readily be incorporated. The shock' problem is solved by the application of the continuity, enexgy and momentum equations between conditions 2 and 2', the momentumequation giving the so-called 'shock torque' as distinct from the'impeller torque subsequently developed in the rotor itself.

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