US 12,454,911 B2
Bleeding core air from a turbine engine core flowpath
Michael G. McCaffrey, Windsor, CT (US); and Mark F. Zelesky, Bolton, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Dec. 29, 2023, as Appl. No. 18/400,329.
Prior Publication US 2025/0215827 A1, Jul. 3, 2025
Int. Cl. F01D 25/12 (2006.01); F01D 17/10 (2006.01); F02C 7/18 (2006.01)
CPC F02C 7/18 (2013.01) [F01D 17/105 (2013.01); F01D 25/12 (2013.01); F05D 2220/323 (2013.01); F05D 2260/232 (2013.01); F05D 2260/606 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An assembly for a turbine engine, comprising:
an engine core configured to drive rotation of a propulsor rotor, the engine core including a first compressor section, a second compressor section, a flowpath, a bleed port, an inner passage and an outer passage;
the first compressor section and the second compressor section arranged axially along an axis;
the flowpath extending longitudinally through the first compressor section and the second compressor section;
the bleed port fluidly coupling the flowpath to the inner passage and the outer passage in parallel, and the bleed port located longitudinally along the flowpath between the first compressor section and the second compressor section;
the inner passage arranged radially between the flowpath and the outer passage; and
a trajectory of the bleed port extending radially inward as the bleed port extends longitudinally from the flowpath to an inlet into the inner passage and an inlet into the outer passage;
wherein at least one of
a trajectory of the outer passage extends radially outward as the outer passage extends longitudinally away from the bleed port; or
a trajectory of the outer passage extends radially inward and then extends radially outward as the outer passage extends longitudinally out from the bleed port.