| 摘要 |
PROBLEM TO BE SOLVED: To provide a technique concerning the field of turbomachines, particularly cooling of a ring sector 1 of a turbine 8 of a turbomachine 9. SOLUTION: The ring sector 1 of the turbine comprises a wall body 11 bounding an aerodynamic flowpath 5 in which gases flow from an upstream region 52 to a downstream region 53, and a multiperforated plate 2 situated on the opposite side of the flowpath 5 with respect to the wall 11, the plate comprising bottoms 21, 121, 221, 321 and side walls 22 and 23. The distance between the wall 11 of the ring sector 1 and the bottoms 21, 121, 221, 321 of the plate 2 defines a gap which is progressive in an axial direction from the upstream region 52 toward the downstream region 53. The value of the gap situated at the upstream region 52 is below the value of the gap situated at the downstream region 53. COPYRIGHT: (C)2008,JPO&INPIT |
