| 摘要 |
<p>A gas turbine stator (1) for aircraft engines has a blade array (lb) with a plurality of blades constituted by a series of first blades (5a) and a series of second blades (5b) with different geometries; the array is formed by a plurality of sectors, each having an inner portion (3), an outer portion (4), at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator (1).</p> |
