| 摘要 |
An airfoil (302) of a gas turbine engine having a hollow body defining at least one airfoil cavity (304) therein, the hollow body defining an inner diameter and an outer diameter and a baffle (320) positioned within the at least one airfoil cavity (304) and extending over less than an entire length between the inner diameter and the outer diameter, the baffle (320) configured to reduce the cross-sectional area within the at least one airfoil cavity (304). The at least one airfoil cavity (304) includes a first portion (326) having a length that is defined by an open cavity having a full cross-sectional area and a second portion (328) having a length that is defined by a reduced cross-sectional area, the second portion (328) being the length of the baffle (320) within the at least one airfoil cavity (304). |
