| 摘要 |
A vane assembly (21) for an axial flow turbine engine provides a plurality of nozzles (22) arranged symmetrically around a turbine axis formed by an inner hub (26), an outer casing (27) and vanes (23) intermediate pairs of adjacent nozzles. The nozzles have a cross-section normal to the turbine axis that changes smoothly with the position of the cross-section along the turbine axis from a first shape having a minimum radius of curvature of a first value that is no less than a limit L, providing the cross-section with no highly curved corners, to a second shape having a minimum radius of curvature of a second value less than the first value, providing corners. This allows the secondary flow structure to be designed to improve aerodynamic loss and cooling performance. |
