University of Alberta
Edmonton, Alberta, Canada
With this work we present a new Lagrangian based inverse design technique for constructing turbomachinery blade geometries. This method consists of a 2D flow field integrator, a camberline generator, and a passage-averaged momentum/pressure boundary condition. Incorporated into both the passage-averaged boundary conditions, and the camberline generator itself, is a Lagrangian description that enhances significantly, the global convergence of our inverse design calculations.
By describing a blade geometry as a mean camberline with a specified thickness distribution, we will show how this camberline can be obtained from a Lagrangian analysis of the upper and lower blade surfaces. We will also show how a flow field into a complex-lamellar decomposition and then used to derive the pressure boundary conditions for our inverse design method.
Finally, numerical results will be presented to illustrate the utility of this inverse design technique and verify the convergence acceleration produce by this new Lagrangian approach.