US 12,404,812 B1
Open rotor aircraft propulsion system with bypass flowpath
Andrew E. Breault, Bolton, CT (US); Jeffrey T. Morton, Manchester, CT (US); and Jon E. Sobanski, Glastonbury, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Mar. 4, 2024, as Appl. No. 18/594,936.
Int. Cl. F02C 7/36 (2006.01); B64D 35/00 (2006.01); F02C 9/18 (2006.01)
CPC F02C 7/36 (2013.01) [B64D 35/00 (2013.01); F02C 9/18 (2013.01); F05D 2220/323 (2013.01); F05D 2260/40311 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft, comprising:
an open propulsor rotor; and
a turbine engine including a fan section, an engine core, a first geartrain, a second geartrain, a core flowpath and a bypass flowpath;
the fan section comprising a fan rotor;
the engine core including a first rotating assembly, a low pressure compressor section, a high pressure compressor section, a combustor section, a high pressure turbine section and a low pressure turbine section, the low pressure compressor section is located axially between the first geartrain and the high pressure compressor section along the axis, and the first rotating assembly rotatable about an axis and configured to drive rotation of the open propulsor rotor and the fan rotor through the first geartrain;
the first geartrain located axially between the engine core and the open propulsor rotor, the first rotating assembly configured to drive the rotation of the fan rotor through the first geartrain and independent of the second geartrain;
the second geartrain located axially between the fan rotor and the open propulsor rotor;
the core flowpath extending through the low pressure compressor section, the high pressure compressor section, the combustor section, the high pressure turbine section and the low pressure turbine section from an inlet into the core flowpath to an exhaust from the core flowpath, and the inlet into the core flowpath next to and downstream of the fan section; and
the bypass flowpath extending outside of and along the engine core from an inlet into the bypass flowpath to an exhaust from the bypass flowpath, the exhaust from the bypass flowpath disposed radially outboard of and circumscribing the exhaust from the core flowpath, and the inlet into the bypass flowpath next to and downstream of the fan section.