The development of advanced computational methods for turbomachinery blade design

The 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.