| 摘要 |
Nozzles (102) and nozzle assemblies (100) for gas turbine engines (16) are provided. A nozzle (102) includes an airfoil (110) having an exterior surface defining a pressure side (112) and a suction side (114) extending between a leading edge (116) and a trailing edge (118), an outer band (130) disposed radially outward of the airfoil (110), the outer band (130) including a radially outwardly-facing end surface (132), and an inner band (120) disposed radially inward of the airfoil (110), the inner band (120) including a radially inwardly-facing end surface (121). The nozzle (102) further includes a flange (200) extending radially from one of the radially outwardly-facing end surface (132) or the radially inwardly-facing end surface (121). The flange (200) is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies (250) stacked together and generally having an L-shape in a circumferential cross-sectional view. |
