Cooled airfoil tip corner
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Gary E. Wheat, Barry T. Malone, Nicholas C. Palmer, Robert C. Simmons
Life of this patent
Estimating the term…
Abstract
A gas turbine engine airfoil includes a tip corner disposed at the juncture of the airfoil tip and trailing edge, and a cooling hole extends therethrough in direct flow communication with an internal cooling passage thereof. A cross-hole extends perpendicularly into the tip corner and into the cooling hole for discharging from the airfoil a portion of cooling air channeled into the cooling hole. The airfoil tip corner is therefore cooled by the air channeled through the cross-hole received from the intersecting cooling hole.
Claims8
A gas turbine engine airfoil comprising:
- first and second opposite sides joined together at spaced apart leading and trailing edges and extending from a root to a tip;
- an internal cooling passage for channeling cooling air therethrough;
- and
- a tip corner disposed at a juncture of said airfoil tip and said airfoil trailing edge, and having a plurality of cooling holes extending therethrough in direct flow communication with said cooling passage for discharging said cooling air from said airfoil, and further having a cross-hole extending perpendicularly into said corner and into at least one of said cooling holes for discharging from said airfoil a portion of said cooling air channeled into said at least one cooling hole.
A gas turbine engine airfoil comprising:
- first and second opposite sides joined together at spaced apart leading and trailing edges and extending from a root to a tip;
- an internal cooling passage for channeling cooling air therethrough;
- a tip corner disposed at a juncture of said airfoil tip and said airfoil trailing edge, said tip corner including a radial leg extending along said airfoil trailing edge at said airfoil tip, and a tip leg extending along said airfoil tip at said airfoil trailing edge and generally perpendicular to said radial leg;
- a first cooling hole extending through said radial leg perpendicularly to said trailing edge in direct flow communication with said cooling passage for discharging said cooling air from said airfoil, and a first cross hole extending through said tip corner to said first cooling hole and perpendicularly to said airfoil tip for discharging from said airfoil a portion of said cooling air channeled into first cooling hole;
- and
- a second cooling hole extending through said tip leg perpendicularly to said airfoil tip in direct flow communication with said cooling passage for discharging said cooling air from said airfoil, and a second cross hole extending through said tip corner to said second cooling hole and perpendicularly to said airfoil trailing edge for discharging from said airfoil a portion of said cooling air channeled into second cooling hole.
Dependencies are inferred from the claim text.