GAS TURBINE ENGINE TURBINE BLADE WITH COOLED TIP

摘要

An airfoil (78; 178; 278) for a gas turbine engine (20) includes pressure and suction walls (86, 88) that are spaced apart from one another and joined at leading and trailing edges (82, 84) to provide an airfoil (78; 178; 278) that has an exterior surface that extends in a radial direction (R) to a tip (80; 180; 280). A film cooling hole (94) is provided in the tip (80; 180; 280) and extends at an angle relative to the radial direction (R). The film cooling hole (94) includes a diffuser (98).