| 摘要 |
<p>A gas turbine nozzle segment (10) has outer and inner bands (12, 14) and a vane (16) therebetween. Each band includes a nozzle wall (18), a side wall (40), a cover (20) and an impingement plate (22) between the cover and the nozzle wall defining two cavities (24, 26) on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures (30) of the impingement plate to cool the nozzle wall. The side wall (40) of the band and inturned flange (42) define with the nozzle wall an undercut region (44). The impingement plate has a turned flange (52) welded to the inturned flange (42). A backing plate (60) overlies the turned flange and aligned apertures (62) are formed through the backing plate and turned flange to direct and focus cooling flow onto the side wall of the nozzle segment. <IMAGE></p> |
