Turbine stator vane segment having internal cooling circuits

Patent · Wed Jan 01 00:00:00 EST 2003

OSTI ID:875032

Jones, Raymond Joseph ^[1]; Burns, James Lee ^[2]; Bojappa, Parvangada Ganapathy ^[3]; Jones, Schotsch Margaret ^[4]

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1. Oxford, MA
2. Schenectady, NY
3. Simpsonville, SC
4. Greer, SC

A turbine stator vane includes outer and inner walls each having outer and inner chambers and a vane extending between the outer and inner walls. The vane includes first, second, third, fourth and fifth cavities for flowing a cooling medium. The cooling medium enters the outer chamber of the outer wall, flows through an impingement plate for impingement cooling of the outer band wall defining in part the hot gas path and through openings in the first, second and fourth cavities for flow radially inwardly, cooling the vane. The spent cooling medium flows into the inner wall and inner chamber for flow through an impingement plate radially outwardly to cool the inner wall. The spent cooling medium flows through the third cavity for egress from the turbine vane segment from the outer wall. The first, second or third cavities contain inserts having impingement openings for impingement cooling of the vane walls. The fifth cavity provides air cooling for the trailing edge.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• DOE Contract Number: FC21-95MC31176
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): US 6517312
• OSTI ID: 875032
• Country of Publication: United States
• Language: English

Related Subjects

turbine
stator
vane
segment
internal
cooling
circuits
outer
inner
walls
chambers
extending
third
fourth
fifth
cavities
flowing
medium
enters
chamber
wall
flows
impingement
plate
band
defining
hot
gas
path
openings
flow
radially
inwardly
spent
outwardly
cool
cavity
egress
contain
inserts
provides
air
trailing
edge
hot gas
cooling circuit
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