| 摘要 |
A gas turbine engine apparatus includes a turbine nozzle 20 including first and second vanes 36,38 joined to outer and inner bands. The vanes 36,38 include outboard sides 50,52 defining outboard flow passages 60 containing axial split-lines 44 in the bands, and opposite inboard sides 52,50 defining an inboard flow passage 58 without an axial split-line. The two vanes 36,38 include different cooling arrangements for differently cooling the inboard and outboard vane sides 50,52. The outboard sides may be cooled to a greater extent than the inboard sides to withstand hot streaks produced by fuel injectors 30. The differences in cooling may be achieved by varying the configuration of film cooling holes or impingement cooling holes and/or the thicknesses of thermal barrier coatings. |
