Turbine blade cooling
Abstract
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.
- Inventors:
- Issue Date:
- Sponsoring Org.:
- USDOE; USDOE, Washington, DC (United States)
- OSTI Identifier:
- 6446019
- Patent Number(s):
- 5924843
- Application Number:
- PPN: US 8-861045
- Assignee:
- General Electric Co., Schenectady, NY (United States)
- DOE Contract Number:
- AC21-93MC30244
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 21 May 1997
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; AUGMENTATION; COOLING; HEAT TRANSFER; TURBINE BLADES; ENERGY TRANSFER; 330103* - Internal Combustion Engines- Turbine
Citation Formats
Staub, F W, and Willett, F T. Turbine blade cooling. United States: N. p., 1999.
Web.
Staub, F W, & Willett, F T. Turbine blade cooling. United States.
Staub, F W, and Willett, F T. Tue .
"Turbine blade cooling". United States.
@article{osti_6446019,
title = {Turbine blade cooling},
author = {Staub, F W and Willett, F T},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1999},
month = {7}
}