Cooling system for the trailing edges of turbine bucket airfoils
AssigneeGeneral Electric Company
InventorsAriel Caesar Prepena Jacala, Gary M. Itzel, Joshua R. Kornau, Azadali A. Ladhani
Life of this patent
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Abstract
The cooling system includes a plurality of generally radially extending passages within the airfoil for convectively cooling the airfoil. A predetermined number of the passages exit through the airfoil tip. One or more of the remaining passages exit into a plenum adjacent the trailing edge and airfoil tip region of the airfoil and flow radially inwardly along one or more passageways adjacent the trailing edge region. The passageways exit in openings along the pressure side of the airfoil. In this manner, the trailing edge region is convectively cooled as well as film cooled by the film of air exiting the holes.
Claims17
A cooling system for a turbine bucket comprising:
- an airfoil, a base and a platform interfaced between the airfoil and base;
- said airfoil having a plurality of passages extending generally radially therealong for communication with a supply of cooling medium at radial inner ends thereof and convectively cooling the airfoil as the cooling medium flows generally radially outwardly along the passages toward a tip of the airfoil;
- a predetermined number of said passages having exit openings adjacent said airfoil tip for flowing spent cooling medium into a hot gas path of the turbine;
- at least one remaining passage of said plurality of passages being in communication adjacent the tip of the airfoil with a cooling passageway extending generally inwardly along a trailing edge region of the airfoil for convectively cooling the trailing edge region,
- said passageway terminating in an exit hole along one side and intermediate the length of the airfoil for film cooling the trailing edge along said one airfoil side.
A method of cooling a trailing edge region of an airfoil forming part of a turbine bucket having a base and a platform interfaced between the airfoil and base comprising the steps of:
- providing said airfoil with a plurality of passages extending generally radially therealong toward a tip of the airfoil;
- flowing a cooling medium generally radially outwardly along said passages toward the airfoil tip for convectively cooling the airfoil;
- providing exit openings adjacent said airfoil tip for a predetermined number of said passages enabling flow of spent cooling medium into a hot gas path of the turbine;
- communicating the cooling medium at a location adjacent the tip of the airfoil from at least one of remaining passages of said plurality of passages with a cooling passageway extending generally radially inwardly along a trailing edge region of the airfoil for convectively cooling the trailing edge region;
- and
- terminating the passageway in an exit hole along one side of the airfoil intermediate the length of the airfoil for film cooling the trailing edge along said one airfoil side.
Dependencies are inferred from the claim text.