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.
- Inventors:
-
- Schenectady, NY
- Niskayuna, NY
- Issue Date:
- Research Org.:
- General Electric Co., Boston, MA (United States)
- OSTI Identifier:
- 872390
- Patent Number(s):
- 5924843
- Application Number:
- 08/861045
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- DOE Contract Number:
- AC21-93MC30244
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 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; /415/416/
Citation Formats
Staub, Fred Wolf, and Willett, Fred Thomas. Turbine blade cooling. United States: N. p., 1999.
Web.
Staub, Fred Wolf, & Willett, Fred Thomas. Turbine blade cooling. United States.
Staub, Fred Wolf, and Willett, Fred Thomas. Tue .
"Turbine blade cooling". United States. https://www.osti.gov/servlets/purl/872390.
@article{osti_872390,
title = {Turbine blade cooling},
author = {Staub, Fred Wolf and Willett, Fred Thomas},
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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1999},
month = {7}
}
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Works referenced in this record:
Heat Transfer in Rotating Serpentine Passages With Smooth Walls
conference, March 2015
- 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
Heat Transfer in Rotating Serpentine Passages With Trips Skewed to the Flow
conference, March 2015
- 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