TWO PORTION COOLING PASSAGE FOR AIRFOIL

A turbine airfoil includes a body having an airfoil wall, and a coolant chamber within the body. A plurality of cooling passages are within the airfoil wall, each cooling passage includes: a first portion extending from a first point on an exterior surface of the airfoil wall to the coolant chamber,...

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Bibliographische Detailangaben
Hauptverfasser:	Gregg, Jason Ray, Brzek, Brian Gene, Rathay, Nicholas William
Format:	Patent
Sprache:	eng
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 turbine airfoil includes a body having an airfoil wall, and a coolant chamber within the body. A plurality of cooling passages are within the airfoil wall, each cooling passage includes: a first portion extending from a first point on an exterior surface of the airfoil wall to the coolant chamber, and a second portion extending from a second point on the exterior surface of the airfoil wall distal from the first point to intersect a mid-portion of the first portion. A cap element closes the first portion at the first point but leaving the second portion open. Each cooling passage has a single inlet in fluid communication with the coolant chamber and a single outlet at the second point of the second portion.