US 12,435,640 B2
Gas turbine engine vane outer diameter platform integrated with blade outer air seal
James T. Roach, Vernon, CT (US); Jonas Banhos, West Hartford, CT (US); and Russell Kim, Temecula, CA (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 2, 2023, as Appl. No. 18/500,671.
Prior Publication US 2025/0146421 A1, May 8, 2025
Int. Cl. F01D 11/08 (2006.01); F01D 5/18 (2006.01); F01D 5/28 (2006.01); F01D 9/06 (2006.01); F01D 11/00 (2006.01)
CPC F01D 11/08 (2013.01) [F01D 5/187 (2013.01); F01D 5/188 (2013.01); F01D 5/282 (2013.01); F01D 5/284 (2013.01); F01D 9/065 (2013.01); F01D 11/001 (2013.01); F05D 2240/81 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/6034 (2013.01)] 4 Claims
OG exemplary drawing
 
1. A combined gas turbine engine vane and blade outer air seal assembly comprising:
a vane having an airfoil extending from a leading edge to a trailing edge, and having an outer platform, the outer platform having a cooling channel that extends into the airfoil to receive cooling air;
the outer platform extending to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine;
at least a portion of said vane and said blade outer air seal formed of ceramic matrix composite materials;
wherein there are cooling air passages within said outer platform and said blade outer air seal and connected into the cooling channel such that the cooling air can be communicated from the cooling channel into said blade outer air seal; and
wherein the cooling air passages extend to a radially outwardly extending portion and then into outlets extending in an axially aft direction.