Abstract
Actuator disc theory has been further developed to model the influence of density gradients upon the meridional flow through multi-stage turbomachines. The analysis takes advantage of previous solutions for the flow induced by source discs and the analogy between compressible flows and incompressible flows with source distributions. Plane compressible actuator disc theory for cylindrical turbomachines is improved and extended to deal with smeared or axially distributed actuator discs. A further extension is developed to deal with non-cylindrical annuli and applied to a three-stage axial turbine with flared hub and casing. The method provides a first-order design technique for multi-stage axial turbines suitable for PC computations.
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