US 11,913,358 B2
Forming lined cooling aperture(s) in a turbine engine component
Brian Craig, Palm Beach Gardens, FL (US); James M. Koonankeil, Marlborough, CT (US); Brian T. Hazel, Avon, CT (US); Paul E. Denney, Northborough, MA (US); and Dominic J. Mongillo, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Mar. 13, 2023, as Appl. No. 18/120,843.
Application 18/120,843 is a division of application No. 17/401,906, filed on Aug. 13, 2021, granted, now 11,603,769.
Prior Publication US 2023/0212951 A1, Jul. 6, 2023
Int. Cl. B23K 26/386 (2014.01); F01D 5/18 (2006.01); F01D 9/04 (2006.01); B23K 26/382 (2014.01); C23C 4/01 (2016.01); C23C 14/02 (2006.01); C23C 14/16 (2006.01); C23C 16/02 (2006.01); C23C 16/06 (2006.01); F01D 25/12 (2006.01); F01D 9/02 (2006.01)
CPC F01D 9/041 (2013.01) [B23K 26/386 (2013.01); B23K 26/389 (2015.10); C23C 4/01 (2016.01); C23C 14/024 (2013.01); C23C 14/028 (2013.01); C23C 14/16 (2013.01); C23C 16/0263 (2013.01); C23C 16/0281 (2013.01); C23C 16/06 (2013.01); F01D 5/186 (2013.01); F01D 9/02 (2013.01); F01D 25/12 (2013.01); B23P 2700/00 (2013.01); F05D 2220/32 (2013.01); F05D 2230/10 (2013.01); F05D 2230/31 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01); F05D 2260/20 (2013.01); F05D 2260/202 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A component for a turbine engine, comprising:
a substrate comprising metal;
an external coating over the metal substrate, the external coating comprising ceramic;
a plurality of cooling apertures, a first of the plurality of cooling apertures including a meter section and a diffuser section, the meter section formed in the substrate, and the diffuser section formed in the substrate and the external coating; and
an internal coating at least partially lining the first of the plurality of cooling apertures within the substrate;
wherein the component is configured as an airfoil or a flowpath wall for the turbine engine.