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
 

Turbine blade cooling

Patent ·
OSTI ID:872390
 [1];  [2]
  1. Schenectady, NY
  2. Niskayuna, NY
+ Show Author Affiliations
A turbine rotor blade comprises a shank portion, a tip portion and an airfoil. The airfoil has a pressure side wall and a suction side wall that are interconnected by a plurality of partition sidewalls, defining an internal cooling passageway within the airfoil. The internal cooling passageway includes at least one radial outflow passageway to direct a cooling medium flow from the shank portion towards the tip portion and at least one radial inflow passageway to direct a cooling medium flow from the tip portion towards the shank portion. A number of mixing ribs are disposed on the partition sidewalls within the radial outflow passageways so as to enhance the thermal mixing of the cooling medium flow, thereby producing improved heat transfer over a broad range of the Buoyancy number.
Research Organization:
GENERAL ELECTRIC CO
DOE Contract Number:
AC21-93MC30244
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
US 5924843
Application Number:
08/861045
OSTI ID:
872390
Country of Publication:
United States
Language:
English

References (2)

Heat Transfer in Rotating Serpentine Passages With Smooth Walls
  • Wagner, J. H.; Johnson, B. V.; Kopper, F. C.
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition, Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration https://doi.org/10.1115/90-GT-331
conference March 2015
Heat Transfer in Rotating Serpentine Passages With Trips Skewed to the Flow
  • Johnson, B. V.; Wagner, J. H.; Steuber, G. D.
  • ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration https://doi.org/10.1115/92-GT-191
conference March 2015

Similar Records

Turbine blade cooling
Patent · Fri Dec 31 23:00:00 EST 1999 · OSTI ID:873303
Turbine blade cooling
Patent · Tue Jul 20 00:00:00 EDT 1999 · OSTI ID:6446019
Internal cooling circuit for gas turbine bucket
Patent · Tue Oct 25 00:00:00 EDT 2005 · OSTI ID:1175532

Related Subjects

/415/416/
airfoil
blade
blade comprises
blade cooling
broad
broad range
buoyancy
comprises
cooling
cooling medium
defining
direct
disposed
enhance
flow
flow passage
flow passageways
heat
heat transfer
improved
improved heat
inflow
interconnected
internal
internal cooling
medium
medium flow
mixing
outflow
partition
partition sidewalls
passageway
passageways
plurality
portion
pressure
producing
producing improved
radial
range
ribs
rotor
rotor blade
shank
shank portion
sidewalls
suction
thermal
tip
tip portion
towards
transfer
turbine
turbine blade
turbine rotor
wall