US 12,215,604 B1
Cooling nozzle vanes of a turbine engine
Lawrence A. Binek, Glastonbury, CT (US); Paul M. Lutjen, Kennebunkport, ME (US); and Jose R. Paulino, Jupiter, FL (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Dec. 22, 2023, as Appl. No. 18/394,810.
Int. Cl. F01D 9/02 (2006.01); F23R 3/54 (2006.01); F01D 5/18 (2006.01); F01D 9/06 (2006.01)
CPC F01D 9/02 (2013.01) [F23R 3/54 (2013.01); F01D 5/187 (2013.01); F01D 9/065 (2013.01); F23R 2900/03044 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An assembly for a turbine engine, comprising:
a nozzle structure including a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis, the plurality of nozzle vanes extending radially between and connected to the first platform and the second platform; and
a combustor wall comprising a plurality of apertures, an upstream portion of the combustor wall radially between and bordering a plenum and a combustion chamber, a downstream portion of the combustor wall radially between and bordering the plenum and a gap, the downstream portion of the combustor wall axially overlapping the nozzle structure with the gap formed by and extending between the combustor wall and the first platform, and the plurality of apertures extending through the downstream portion of the combustor wall and aligned with the plurality of nozzle vanes.