| 摘要 |
A vane (110) for a gas turbine engine includes an airfoil (202) having a leading edge (214), a pressure surface (304), a trailing edge (216) and a suction surface (302), and a cooling air channel (340). The suction surface (302) is formed by an exterior surface of a first wall portion (306) and an exterior surface of a second wall portion (308) The first wall portion (306) spans a length of the suction surface (302) between the second wall portion (308) and the trailing edge (216). The cooling air channel (340) is defined, at least in part, by an interior surface of the first wall portion (306), the first wall portion (306) exhibiting a thickness (T 1 ) that is thinner than a thickness (T 2 ) exhibited by the second wall portion (308). |
