| 摘要 |
The invention relates to a nozzle sector (22) for a turbine engine. The nozzle sector comprises a radially outer platform (24), a radially inner platform (26), a first end blade (81), a second end blade (84) and at least one first central blade (82, 83) between the end blades (81, 84) in a circumferential direction of the platforms (Z-Z). The blades (81, 82, 83, 84) extend radially between the platforms (24, 26) in the direction of the span (X-X) of said blades. The sector (22) includes means (44, 46) for cooling the blades, configured to cool each of the blades (81, 82, 83, 84) by circulating cooling air over same. The cooling means (44, 46) are configured to cool the one or more central blades (82, 83) more than at least one of the end blades (81, 84). |
