Leading edge cooling of airfoils

The leading edge of the turbine airfoil (12) of a turbine blade (10) for a gas turbine engine is cooled by utilizing helix shaped holes (40) that are rectangular in cross-section and curved to produce film holes egressing at low angles adjacent the outer surface of the leading edge. The helix holes...

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Bibliographische Detailangaben
Hauptverfasser:	AUXIER, THOMAS A, HALL, KENNETH B
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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:	The leading edge of the turbine airfoil (12) of a turbine blade (10) for a gas turbine engine is cooled by utilizing helix shaped holes (40) that are rectangular in cross-section and curved to produce film holes egressing at low angles adjacent the outer surface of the leading edge. The helix holes (40) extend from the root (14) to the tip (16) of the blade and are parallelly and longitudinally spaced.