Skip to main content
OSTI.GOVU.S. Department of Energy Office of Scientific and Technical Information
U.S. Department of Energy
Office of Scientific and Technical Information
 

Nozzle cavity impingement/area reduction insert

Patent ·
OSTI ID:874818
 [1];  [1];  [2]
  1. Simpsonville, SC
  2. East Thetford, VT
+ Show Author Affiliations
A turbine vane segment is provided that has inner and outer walls spaced from one another, a vane extending between the inner and outer walls and having leading and trailing edges and pressure and suction sides, the vane including discrete leading edge, intermediate, aft and trailing edge cavities between the leading and trailing edges and extending lengthwise of the vane for flowing a cooling medium; and an insert sleeve within at least one of the cavities and spaced from interior wall surfaces thereof. The insert sleeve has an inlet for flowing the cooling medium into the insert sleeve and has impingement holes defined in first and second walls thereof that respectively face the pressure and suction sides of the vane. The impingement holes of at least one of those first and second walls are defined along substantially only a first, upstream portion thereof, whereby the cooling flow is predominantly impingement cooling along a first region of the insert wall corresponding to the first, upstream portion and the cooling flow is predominantly convective cooling along a second region corresponding to a second, downstream portion of the at least one wall of the insert sleeve.
Research Organization:
General Electric Company (Schenectady, NY)
DOE Contract Number:
FC21-95MC31176
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
US 6468031
OSTI ID:
874818
Country of Publication:
United States
Language:
English

References (2)

Advances in Steam Path Technology journal April 1996
Development Requirements for an Advanced Gas Turbine System journal October 1995

Similar Records

Cooling circuit for steam and air-cooled turbine nozzle stage
Patent · Mon Dec 31 23:00:00 EST 2001 · OSTI ID:874517
Film cooling for a closed loop cooled airfoil
Patent · Tue Dec 31 23:00:00 EST 2002 · OSTI ID:874986
Turbine stator vane segment having internal cooling circuits
Patent · Tue Dec 31 23:00:00 EST 2002 · OSTI ID:875032

Related Subjects

/415/416/
cavities
cavity
convective
cooling
cooling medium
defined
discrete
downstream
edge
edges
extending
flow
flowing
holes
impingement
impingementarea
including
inlet
inner
insert
interior
intermediate
leading
lengthwise
medium
nozzle
outer
portion
predominantly
pressure
provided
reduction
region
segment
sleeve
spaced
substantially
suction
surfaces
trailing
turbine
turbine vane
upstream
vane
wall
walls