Internally cooled gas turbine airfoil and method
AssigneePratt & Whitney Canada Corp.
InventorMichael Papple
Life of this patent
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Abstract
An internally cooled airfoil for a gas turbine engine, wherein a plurality of elongated cooling fins are provided inside the concave sidewall.
Claims20
An internally cooled airfoil for a gas turbine engine, the airfoil having at least one internal cooling passageway generally positioned between opposite concave and convex sidewalls, and a trailing edge outlet, the airfoil comprising:
- a crossover located in the passageway and being adjacent to the trailing edge outlet, the crossover comprising a plurality of crossover holes;
- and
- a plurality of elongated cooling fins provided inside the concave sidewall between the crossover and the trailing edge outlet.
An airfoil for use in a gas turbine engine, the airfoil comprising a convex side, a concave side and a trailing edge at a rearmost portion of the airfoil, the airfoil having at least one internal cooling passageway, the airfoil comprising a plurality of internal cooling fins located inside the passageway and extending from the concave side upstream the trailing edge.
A method of enhancing the cooling an airfoil of a gas turbine engine, the airfoil comprising at least one internal cooling passageway generally positioned between a concave sidewall and a convex sidewall, and a trailing edge outlet, the method comprising:
- providing a crossover located in the passageway and adjacent to the trailing edge outlet, the crossover comprising a plurality of crossover holes;
- providing a plurality of elongated cooling fins inside the concave sidewall between the crossover and the trailing edge outlet;
- and
- circulating an airflow inside the passageway, the airflow running through the crossover holes and then over the fins before exiting at the trailing edge outlet.
Dependencies are inferred from the claim text.