Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling

Patent · Tue Jan 01 00:00:00 EST 2002

OSTI ID:874574

Burdgick, Steven Sebastian ^[1]

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1. Schenectady, NY

A gas turbine nozzle segment has outer and inner bands and a vane extending therebetween. Each band has a side wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band has an inturned flange defining with the nozzle wall an undercut region. The outer surface of the side wall is provided with a step prior to welding the cover to the side wall. A thermal barrier coating is applied in the step and, after the cover is welded to the side wall, the side wall is finally machined to a controlled thickness removing all, some or none of the coating.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• DOE Contract Number: FC21-95MC31176
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): US 6418618
• OSTI ID: 874574
• Country of Publication: United States
• Language: English

Related Subjects

method
controlling
wall
thickness
turbine
nozzle
segment
improved
cooling
gas
outer
inner
bands
vane
extending
therebetween
band
cover
impingement
plate
defining
cavities
opposite
steam
supplied
cavity
flow
apertures
cool
inturned
flange
undercut
region
surface
provided
step
prior
welding
thermal
barrier
coating
applied
welded
finally
machined
controlled
removing
gas turbine
turbine nozzle
nozzle segment
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