| 摘要 |
A turbine nozzle assembly for a gas turbine engine, including: a plurality of segments (34) joined together to form an outer band; a plurality of segments (36) joined together to form an inner band; at least one airfoil (32) positioned between the outer and inner bands; a leaf seal (54) attached to each inner band segment (36) by at least one pin member (58); and, a leaf seal attached to each outer band segment (34) by at least one pin member. Each of the inner band segments (36) includes a protrusion (74) extending from a surface (68) thereof so as to provide balanced support to the corresponding leaf seal (54) in conjunction with the pin members (58). Each of the inner band segments (36) further includes a first portion (56) having a flange (75) extending therefrom, a second portion (66) opposite the first portion (56), a first end (62), and a second end opposite the first end (62), wherein the surface (68) extends between the first and second ends and the first and second portions (56,66). <IMAGE>
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