TURBOMACHINE AIRFOIL TO REDUCE LAMINAR SEPARATION

The invention provides a turbomachine airfoil to reduce laminar separation. A method of controlling a transition from a laminar flow to a turbulent flow for an airfoil of a turbomachine includes forming an airfoil. The airfoil defines a span extending between a root and a tip and a chord extending between a leading edge and a trailing edge. The airfoil includes a suction side surface and a pressure side surface, opposite the suction side surface, each extending between the leading edge, the trailing edge, the root, and the tip. The method also includes finishing a majority of the suction and pressure side surfaces in order to form a finished surface. The finished surface defines a first roughness. The method additionally includes leaving at least a portion of the suction side surface and/or pressure side surface unfinished in order to form an unfinished surface. Furthermore, the unfinished surface defines a second roughness greater than the first roughness. 本发明涉及用以减少层状分离的涡轮机翼型件，具体而言一种针对涡轮机的翼型件而控制从层状流到湍急流的过渡的方