SEGREGATED COOLING AIR PASSAGES FOR TURBINE VANE

An airfoil for a gas turbine engine includes a cavity (84) including an internal surface (92) of an outer wall (90). A baffle (88) is disposed within the cavity (84) and spaced apart from the internal surface (92). A partition (94) is disposed between the baffle (88) and the internal surface (92) to...

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Bibliographische Detailangaben
1. Verfasser:	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:	An airfoil for a gas turbine engine includes a cavity (84) including an internal surface (92) of an outer wall (90). A baffle (88) is disposed within the cavity (84) and spaced apart from the internal surface (92). A partition (94) is disposed between the baffle (88) and the internal surface (92) to divide a space between the baffle (88) and the internal surface (92) into at least a first passage (110) and a second passage (112).