Cooled airfoil component
AssigneePratt & Whitney Canada Corp.
InventorsSri Sreekanth, Michael Papple
Life of this patent
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Abstract
A gas turbine engine airfoil component having an airfoil body with a core cavity, an end opening in communication with the core cavity, and a wall having a plurality of cooling holes defined therein, each cooling hole being oriented such that the respective hole axis extends out of the core cavity through the end opening.
Claims13
An airfoil component for a gas turbine engine, the airfoil component comprising an airfoil body defining a leading edge and a trailing edge, the body having opposed first and second walls interconnected at the leading and trailing edges to define a core cavity therebetween, the body also having an end opening defined therein in communication with the core cavity and bordered by the walls, at least the first wall having a plurality of radially extending rows of non parallel cooling holes defined therein with a respective hole axis being defined for each of the cooling holes, the cooling holes of the first wall being oriented such that all of the hole axes extend within the core cavity and through the end opening without intersecting the second wall.
An airfoil assembly for a gas turbine engine, the assembly comprising:
- an annular inner platform;
- an annular outer platform extending outwardly of and concentric with the inner platform to define an annular gas path therebetween;
- and
- a plurality of airfoils extending between the inner and outer platforms, each airfoil having an airfoil body defining a core cavity therein, the body and one of the inner and outer platforms including aligned openings defined therein in communication with the core cavity, the body including a suction side wall having a plurality of rows of non parallel cooling holes defined therethrough in communication with the core cavity with the rows being defined along a direction extending between the inner and outer platforms, all of the cooling holes of said plurality of rows each defining a respective hole axis oriented such as to extend across the core cavity and through the aligned openings without intersecting the airfoil body.
Dependencies are inferred from the claim text.