US 12,371,997 B2
Cooling arrangement for gas turbine engine component
Emma J. Place, New Hartford, CT (US); Christopher J. Peters, Los Lunas, NM (US); Jeffrey J. DeGray, Somers, CT (US); Dominic J. Mongillo, West Hartford, CT (US); Timothy J. Jennings, New Britain, CT (US); Raymond Surace, Newington, CT (US); and Jeremy B. Fredette, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on May 7, 2024, as Appl. No. 18/656,892.
Application 18/656,892 is a division of application No. 17/856,042, filed on Jul. 1, 2022, granted, now 12,006,836.
Claims priority of provisional application 63/217,788, filed on Jul. 2, 2021.
Prior Publication US 2024/0287907 A1, Aug. 29, 2024
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/18 (2013.01) [F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2260/20 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A casting core assembly for a gas turbine engine component comprising:
a skin core corresponding to a first cooling passage of an airfoil, the first cooling passage including a first section and a tip flag section joined at a first bend, the tip flag section dimensioned to extend from the first bend to a trailing edge of the airfoil, the skin core including a first portion corresponding to the first section and a tip flag portion corresponding to the tip flag section, and the tip flag portion including a row of protrusions corresponding to a first row of exit slots along the trailing edge of the airfoil; and
a serpentine core corresponding to a serpentine cooling passage;
wherein the skin core includes at least one arcuate slot corresponding to at least one turning vane of the airfoil, and the skin core includes a plurality of branched sections corresponding to a plurality of branched paths along the first section, the plurality of branched sections bounding the at least one arcuate slot such that the plurality of branched sections join along the tip flag portion; and
wherein the skin core and the serpentine core are arranged in spaced relationship such that the first cooling passage and the serpentine cooling passage are opposite sides along an internal wall of the airfoil relative to a thickness direction.