Hollow airfoil construction using cover subassembly

A component for a gas turbine engine includes an airfoil having a plurality of channels with a main body extending between a leading edge and a trailing edge. The main body forms a portion of one side of the airfoil and the entirety of an opposing side of the airfoil. A cover is secured to the main...

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Bibliographische Detailangaben
1. Verfasser:	Pickens, John T
Format:	Patent
Sprache:	eng
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:	A component for a gas turbine engine includes an airfoil having a plurality of channels with a main body extending between a leading edge and a trailing edge. The main body forms a portion of one side of the airfoil and the entirety of an opposing side of the airfoil. A cover is secured to the main body about a perimeter by a weld. The cover extends across a majority of the one side of the airfoil. A plurality of ribs extends from the cover in a direction toward the main body to define the channels. The ribs are secured to an inner surface of the main body by an adhesive. A gas turbine engine and a method are also disclosed.