US 11,852,035 B2
Multi-cover gas turbine engine component
Daniel A. Bales, Avon, CT (US); Michael DuPont, Berlin, CT (US); and Eric W. Malmborg, Amston, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Jan. 28, 2022, as Appl. No. 17/587,027.
Application 17/587,027 is a division of application No. 16/404,774, filed on May 7, 2019, granted, now 11,236,619.
Prior Publication US 2022/0145763 A1, May 12, 2022
Int. Cl. F01D 5/18 (2006.01); B23K 101/00 (2006.01)
CPC F01D 5/184 (2013.01) [F01D 5/187 (2013.01); B23K 2101/001 (2018.08); F05D 2220/36 (2013.01); F05D 2240/30 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An airfoil for a gas turbine engine comprising:
an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction;
wherein the airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region; and
a plurality of cover skins welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets, the plurality of cover skins formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recessed region, wherein the plurality of cover skins includes a peripheral cover skin and one or more localized cover skins, the peripheral cover skin comprising the perimeter of the common cover such that the peripheral cover skin surrounds the one or more localized cover skins in an installed position.