A new compressor and turbine blade design method based on three-dimensional Euler computations with moving boundaries

A new three-dimensional inverse method for the design of compressor and tur bine blades is presented. The method solves the time dependent Euler equati ons in a numerical domain of which some boundaries (the blade walls) are it eratively modified until a prescribed pressure distribution is reached. Each iteration of the procedure starts with a blade modification, based on the transpiration model and the permeable wall concept. After generating a new mesh the dow field is updated by performing one finite volume time iter ation, taking into account the mesh points movement during the time steppin g. The blade modifications and time marching computation converge simultane ously to the required geometry and steady-state flow solution. The method makes use of a high resolution three-dimensional finite volume E uler solver, with an upwind-biased evaluation of the advective fluxes for s harp shock wave capturing and low numerical entropy generation. The wall bo undary conditions respect the hyperbolic character of the time dependent Eu ler equations. Non-reflecting boundary conditions are applied along the inl et and outlet boundaries, to favor convergence and limit errors due to shoc k wave reflection. Applications to turbine and compressor blade design illustrate the capabili ties of the method and demonstrate its industrial applicability.