US 11,898,465 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 Aug. 13, 2021, as Appl. No. 17/401,914.
Prior Publication US 2023/0052105 A1, Feb. 16, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/28 (2006.01); F01D 5/00 (2006.01); F01D 5/18 (2006.01); B23K 26/382 (2014.01); C23C 4/073 (2016.01); C23C 4/11 (2016.01); B23K 101/00 (2006.01); B23H 9/10 (2006.01); B23H 9/14 (2006.01); B23P 9/00 (2006.01); B23P 15/02 (2006.01); C23C 4/06 (2016.01); C23C 4/12 (2016.01); C23C 4/16 (2016.01)
CPC F01D 5/288 (2013.01) [F01D 5/005 (2013.01); F01D 5/186 (2013.01); F01D 5/284 (2013.01); B23H 9/10 (2013.01); B23H 9/14 (2013.01); B23K 26/389 (2015.10); B23K 2101/001 (2018.08); B23P 9/00 (2013.01); B23P 15/02 (2013.01); B23P 2700/06 (2013.01); C23C 4/06 (2013.01); C23C 4/073 (2016.01); C23C 4/11 (2016.01); C23C 4/12 (2013.01); C23C 4/16 (2013.01); F05D 2230/11 (2013.01); F05D 2230/90 (2013.01); F05D 2260/202 (2013.01); F05D 2300/2112 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A manufacturing method, comprising:
providing a preform component for a turbine engine, the preform component comprising a substrate;
forming a preform meter section and a preform diffuser section in the substrate;
applying an internal coating to at least the preform meter section to provide a meter section of a cooling aperture; and
applying external coating material over the substrate, the applying of the external coating material forming an external coating over the substrate, and the applying of the external coating building up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.