GAS TURBINE ENGINE AIRFOIL WITH LARGE THICKNESS PROPERTIES

摘要

An airfoil (78) for a gas turbine engine includes an airfoil with pressure and suction sides (94,96) that are joined at leading and trailing edges (82,84). The airfoil (78) extends a span from a support (76) to an end (80) in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil (78) at the support (76) and at the end (80). The leading and trailing edges (82,84) are spaced apart from one another an axial chord (b x ) in an axial direction (X). A cross-section of the airfoil (78) at a span location has a diameter (d max ) tangent to the pressure and suction sides. The diameter (d max ) corresponds to the largest circle fitting within the cross-section. A ratio of the diameter (d max to the axial chord (b x ) is at least 0.4 between 50% and 95% span location.