Open rotor aircraft propulsion system with bypass flowpath
US12397924B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 2, 2024 |
| Grant date | Aug 26, 2025 |
| Priority date | — |
| Expiry date | Feb 2, 2044 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D33/02
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The turbine engine includes a core flowpath, a bypass flowpath, a fan section and an engine core. The engine core includes a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The inlet is next to and downstream of the fan section. The bypass flowpath extends outside of and along the engine core from an inlet into the bypass flowpath to an exhaust from the bypass flowpath. The inlet is next to and downstream of the fan section. The engine core is arranged axially between the fan section and the open propulsor rotor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.