TWO PORTION COOLING PASSAGE FOR AIRFOIL

A turbine airfoil 150, 176, 200 includes a body 210 having an airfoil wall, and a coolant chamber 216 within the body 210. A plurality of cooling passages 204 are within the airfoil wall, each cooling passage 204 includes: a first portion 218 extending from a first point 220 on an exterior surface 2...

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Bibliographische Detailangaben
Hauptverfasser:	GREGG, Jason Ray, BRZEK, Brian Gene, RATHAY, Nicholas William
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 turbine airfoil 150, 176, 200 includes a body 210 having an airfoil wall, and a coolant chamber 216 within the body 210. A plurality of cooling passages 204 are within the airfoil wall, each cooling passage 204 includes: a first portion 218 extending from a first point 220 on an exterior surface 222 of the airfoil wall to the coolant chamber 216, and a second portion 230 extending from a second point 232 on the exterior surface 222 of the airfoil wall distal from the first point 220 to intersect a mid-portion 234 of the first portion 218. A cap element 250 closes the first portion 218 at the first point 220 but leaving the second portion 230 open. Each cooling passage 204 has a single inlet 252 in fluid communication with the coolant chamber 216 and a single outlet 254 at the second point 232 of the second portion 230.