The aerodynamic design method for turbomachine blades reported in part 1 is extended to three dimensions. In this inverse method, the blade pressure loading (i.e., pressure difference between blade upper and lower surfaces) and the blade thickness distributions are prescribed, and the corresponding blade camber surface is sought. The inverse problem is formulated using a pressure-loading boundary condition across the blade surfaces, and modification of the blade geometry is achieved using the flow-tangency conditions along the blade surfaces. The method is demonstrated for the design of axial-flow machines ranging from the subsonic to the supersonic flow regimes.
ASJC Scopus subject areas
- Aerospace Engineering