US 12,292,006 B2
Aircraft propulsion system with multi-direction bleed valve
Jui-Lin Chang, Glastonbury, CT (US); and Paul R. Hanrahan, Sedona, AZ (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Aug. 14, 2023, as Appl. No. 18/233,615.
Claims priority of provisional application 63/397,548, filed on Aug. 12, 2022.
Prior Publication US 2024/0052790 A1, Feb. 15, 2024
Int. Cl. F02C 9/18 (2006.01); F02C 3/04 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 3/04 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An assembly for an aircraft propulsion system, comprising:
an engine core including a compressor section, a combustor section, a turbine section and a core flowpath extending sequentially through the compressor section, the combustor section and the turbine section;
a bypass duct comprising a bypass flowpath outside of the engine core; and
a bleed circuit including a bleed passage and a flow regulator;
the bleed circuit configured to direct bypass gas through the bleed passage from the bypass flowpath into the core flowpath when the flow regulator is in an open position;
the bleed circuit configured to cutoff gas flow through the bleed passage between the bypass flowpath and the core flowpath when the flow regulator is in a closed position; and
the bleed circuit configured to direct core gas through the bleed passage from the core flowpath into the bypass flowpath when the flow regulator is in a second open position.