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.
Claims16
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 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 one of the walls having a plurality of cooling holes defined therein with a respective hole axis being defined for each of the cooling holes, each cooling hole being oriented such that the respective hole axis extends out of the core cavity through the end opening.
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 cooling holes defined therethrough in communication with the core cavity, each cooling hole defining a respective hole axis oriented such as to extend across the core cavity and through the aligned openings without intersecting the airfoil body.
A method of manufacturing a cooled airfoil component for a gas turbine engine, the method including:
- forming an airfoil body defining a core cavity therein and an end opening in communication with the core cavity;
- passing a tool through the end opening and across the core cavity to machine an inner surface of a wall of the airfoil body;
- and
- forming at least one cooling hole through the wall from the inner surface thereof along a longitudinal axis of the tool.
Dependencies are inferred from the claim text.