| 摘要 |
A gas turbine engine component includes a wall (102) having a pressure side (103), a suction side (101), a leading edge (105), a trailing edge (107), an outer surface (108) and an inner surface (110). The inner surface (110) is positioned within the outer surface and defines a core (109). The inner surface has a first protrusion (104b) with a first face and a first concavity (124b). The wall defines a first angled cooling hole (106b) from the first face to the suction side of the outer surface, wherein the axis of the cooling hole forms an angle with the outer surface, and the outlet is configured as a diffuser. |
