Turbine blade cooling

Patent · Sat Jan 01 00:00:00 EST 2000

OSTI ID:873303

Staub, Fred Wolf ^[1]; Willett, Fred Thomas ^[2]

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1. Schenectady, NY
2. Niskayuna, NY

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., Boston, MA (United States)
• DOE Contract Number: AC21-93MC30244
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): US 6132174
• OSTI ID: 873303
• Country of Publication: United States
• Language: English

Related Subjects

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