COOLED TURBINE COMPONENT WITH ALTERNATELY ORIENTATED FILM COOLING HOLE ROWS AND FABRICATION METHOD

A cooled component (62) for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis (A) of the gas turbine engine. The internal ribs are disposed within an internal cavity (110) defining cooling air passages within the cooled component (62)....

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Bibliographische Detailangaben
Hauptverfasser:	SALZILLO, Jr., Richard M, DeGRAY, Jeffrey J, BOEKE, Mark A, LoRICCO, Nicholas M
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A cooled component (62) for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis (A) of the gas turbine engine. The internal ribs are disposed within an internal cavity (110) defining cooling air passages within the cooled component (62). A plurality of cooling holes (84, 85) are arranged in rows (80) with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes (84, 85) includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes (84, 85) is disposed on a side opposite the internal rib relative to a corresponding internal opening.