US 12,359,615 B1
Separating airflows within a turbine engine
Michael G. McCaffrey, Windsor, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Dec. 29, 2023, as Appl. No. 18/400,368.
Int. Cl. F23R 3/04 (2006.01); F02C 7/05 (2006.01)
CPC F02C 7/05 (2013.01) [F23R 3/04 (2013.01); F05D 2260/607 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An assembly for a turbine engine, comprising:
an engine core extending axially along an axis, the engine core including a compressor section, a combustor, a diffuser structure, a diffuser plenum and a plurality of separators;
the combustor arranged within the diffuser plenum, and the combustor including a combustion chamber and a combustor wall between the combustion chamber and the diffuser plenum;
the diffuser structure including a plurality of diffuser passages, and each of the plurality of diffuser passages fluidly coupling the compressor section to a respective one of the plurality of separators; and
each of the of the plurality of separators including a first outlet into the diffuser plenum and a second outlet into the combustion chamber, the plurality of separators comprising a first separator, and the first separator arranged in the diffuser plenum radially outboard of the combustor.