Turbine blade cooling

Patent · Tue Jul 20 04:00:00 EDT 1999

OSTI ID:6446019

Staub, F W; Willett, F T

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. 13 figs.

• Sponsoring Organization: DOE; USDOE, Washington, DC (United States)
• DOE Contract Number: AC21-93MC30244
• Assignee: General Electric Co., Schenectady, NY (United States)
• Patent Number(s): A; US 5924843
• Application Number: PPN: US 8-861045
• OSTI ID: 6446019
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AUGMENTATION
COOLING
ENERGY TRANSFER
HEAT TRANSFER
TURBINE BLADES