| 摘要 |
An improved structure and method of manufacturing a structure such as a guide vane (42) for a gas turbine engine (10) includes an improved guide vane (42) having a stress transition section called a fillet (74, 76, 78) that is positioned between an airfoil (50) and a hub (52). The fillet (74, 76, 78) includes a constant radius section (76) and a compound radius portion (78) that is collectively configured to handle the stress loads of the guide vane (42) as well as to provide aerodynamic efficiencies. An improved method of manufacturing an airfoil (50) is provided that employs a single pass manufacturing process whereby a single tool (84) is used to generate a resulting fillet (74, 76, 78) having a constant radius and compound radius portion (74, 76). |
