US 12,359,620 B2
Cooling features for a component of a gas turbine engine
Billie R. Maldonado, Seattle, WA (US); Thurman C. Dabbs, Dover, NH (US); James R. Plante, East Waterboro, ME (US); Paul M. Lutjen, Kennebunkport, ME (US); Dmitriy A. Romanov, Portland, ME (US); Morely S. Sherman, Portsmouth, NH (US); Nolan Frederic Quinn, Troy, NY (US); Mary E. M. Hiller, Wells, ME (US); Jon Moore, Charlottesville, VA (US); and John R. Paulus, Afton, VA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Oct. 13, 2023, as Appl. No. 18/379,958.
Claims priority of provisional application 63/415,802, filed on Oct. 13, 2022.
Prior Publication US 2024/0125272 A1, Apr. 18, 2024
Int. Cl. F01D 5/18 (2006.01); F01D 25/12 (2006.01); F02C 7/18 (2006.01)
CPC F02C 7/18 (2013.01) [F01D 5/187 (2013.01); F01D 25/12 (2013.01); F05D 2250/70 (2013.01); F05D 2260/232 (2013.01)] 21 Claims
OG exemplary drawing
 
1. A component for a gas turbine engine, comprising:
at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity;
a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features comprising:
a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity each of the plurality of airfoil shaped features includes a base portion that extends upwardly away from the surface and the base portion also extends horizontally with respect to the surface such that a tail portion is formed, the tail portion creates an undercut portion located underneath the tail portion and a first portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises an upstream end of the first portion of the plurality of airfoil shaped features and a second portion of the plurality of airfoil shaped features are oriented such that the tail portion comprises a downstream end of the second portion of the plurality of airfoil shaped features.