GAS TURBINE ENGINE AIRFOIL IMPINGEMENT COOLING

A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges join...

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Bibliographische Detailangaben
Hauptverfasser:	ZELESKY, Mark F, DEVORE, Matthew A, MONGILLO, JR., Dominic J, GAUTSCHI, Steven Bruce, FISK, Benjamin T, PROPHETER-HINCKLEY, Tracy A
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL FOUNDRY MOULDING 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 PERFORMING OPERATIONS POWDER METALLURGY STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall.