COMPONENTS FOR GAS TURBINE ENGINES

Airfoil assemblies (400; 500) for gas turbine engines (20) are described. The airfoil assemblies include an airfoil body (401; 501; 654) having a leading edge (662), a trailing edge (664), a pressure side (666), and a suction side (668), the airfoil body extending in a radial direction between a fir...

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Bibliographische Detailangaben
Hauptverfasser:	GENERALE, Adam P, MONGILLO, Dominic J., Jr
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:	Airfoil assemblies (400; 500) for gas turbine engines (20) are described. The airfoil assemblies include an airfoil body (401; 501; 654) having a leading edge (662), a trailing edge (664), a pressure side (666), and a suction side (668), the airfoil body extending in a radial direction between a first end (782) and a second end (784), wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body (401; 501; 654), the airfoil body (401; 501; 654) formed from a high-temperature-material material and a metallic insert member (402; 502; 652; 780; 896) installed within the internal cavity. One or more radially extending ribs (406; 506; 676; 786a, 788a, 790a; 892, 894) are arranged on an exterior surface of the metallic insert member (402; 502; 652; 780; 896) and defining one or more radially extending passages (408; 508; 674; 786b, 788b, 790b) between the exterior surface of the metallic insert member (402; 502; 652; 780; 896) and the interior surface of the airfoil body (401; 501; 654).