The application of the method is explored using a transonic test case, NASA rotor 67. From an understanding of the dynamics of the flow in the fan in relation to its pressure loading distributions,simple guidelines can be developed for the inverse method in
order to weaken the shock formation.
The design of transonic multistage axial turbines and compressors of the type used in aero-engines and industrial gas turbines poses difficult and challenging problems to turbomachinery designers. In aero-engines, there is an increasing trend to reduce engine weight, which is only possible by increasing stage loading coefficient and reducing the axial spacing between the stages.
An inverse design methodology is presented for the design of turbomachinery blades using a cell-vertex finite volume time-marching algorithm in transonic viscous flow. In this method the blade shape is designed subject to a specified distribution of pressure loading (the difference in pressure across the blade) and thickness distribution.
The development and application of a three-dimensional inverse design for turbomachinery blades is described in this paper. The method solves for the blade geometry based on the prescribed mass-averaged swirl velocity across the blade span and a fixed tangential blade thickness.