| 摘要 |
PROBLEM TO BE SOLVED: To provide an improved turbine nozzle having inner band cooling in a configuration supporting an interstage honeycomb seal. SOLUTION: A turbine nozzle 30 includes hollow nozzle vanes 36 mounted between outer and inner bands 38 and 40. The inner band 40 includes an integral skirt around the perimeter thereof. A backing sheet 62 of a honeycomb seal 60 is mounted to the skirt to define a cavity 46 therein. The inner band includes supply apertures 42 for providing cooling air into the cavity, and the skirt includes forward and aft purge holes 48 and 50 for discharging the cooling air therefrom. During operation, the air channeled through the cavity cools the backside of the inner band and is then discharged through the purge holes. COPYRIGHT: (C)2004,JPO
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