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Film cooling for a closed loop cooled airfoil

Patent ·
OSTI ID:874986
 [1];  [2];  [2]
  1. Schenectady, NY
  2. Simpsonville, SC
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Turbine stator vane segments have radially inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. At least one film cooling hole is defined through a wall of at least one of the cavities for flow communication between an interior of the cavity and an exterior of the vane. The film cooling hole(s) are defined adjacent a potential low LCF life region, so that cooling medium that bleeds out through the film cooling hole(s) reduces a thermal gradient in a vicinity thereof, thereby the increase the LCF life of that region.

Research Organization:
General Electric Company (Schenectady, NY)
DOE Contract Number:
FC21-95MC31176
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
US 6506013
OSTI ID:
874986
Country of Publication:
United States
Language:
English

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Related Subjects

/415/416/
adjacent
airfoil
bleeds
cavities
cavity
closed
communication
compartmentalized
cooled
cooled air
cooling
defined
extending
exterior
film
flow
flowing
flows
gradient
hole
holes
impingement
increase
inner
inserts
interior
lcf
life
loop
medium
outer
passes
plate
plates
plenum
potential
radially
radially inner
reduces
region
return
segments
spent
stator
steam
steam flow
surface
surfaces
therebetween
thermal
turbine
upper
upper surface
vane
vanes
vanes extend
vicinity
wall
walls