Abstract
AbstractThe paper describes the basic components of a turbomachinery blade design system in use within Rolls‐Royce. A number of modelling aspects of the advanced computational methods in use and under development are reviewed together with areas for future research and development.A quasi‐3D blade design system which is used for both compressors and turbines is described covering through‐flow and blade‐to‐blade analysis. Various features of blade‐to‐blade analysis are discussed including the use of compatible design and analysis modes and coupled boundary layer analysis capable of handling attached and separated flow; examples are included to show capabilities. Advances being made in the development and application of Reynolds‐averaged Navier–Stokes models are covered showing capabilities with regard to loss and heat transfer prediction.A fully coupled quasi‐3D through‐flow and blade‐to‐blade analysis system is described and results presented to show basic capabilities.The need for 3D flow analysis is discussed and the elements of a 3D blade design system presented showing how this links to the traditional quasi‐3D system. Examples are given showing basic capabilities of the methods available and under development.Finally areas for future development are presented indicating the mathematical and numerical modelling problems to be addressed.
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