Open rotor aircraft propulsion system with bypass flowpath
US12404812B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 4, 2024 |
| Grant date | Sep 2, 2025 |
| Priority date | — |
| Expiry date | Mar 4, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/40311
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine. The turbine engine includes a fan section, an engine core, a first geartrain, a core flowpath and a bypass flowpath. The fan section includes a fan rotor. The engine core includes 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 first rotating assembly drives rotation of the open propulsor rotor and the fan rotor through the first geartrain. The core flowpath extends 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. The bypass flowpath extends outside of and along the engine core.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.