Fueldraulic heat management system
US12359619B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 25, 2024 |
| Grant date | Jul 15, 2025 |
| Priority date | — |
| Expiry date | Jun 25, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/64
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine for an aircraft includes an engine core with a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor. The engine includes a fan upstream of the engine core driven by the core shaft. The engine includes a nacelle surrounding the fan and engine core and defining a bypass duct located radially outside of the engine core, where the bypass ratio of the mass flow rate through the bypass duct to the mass flow rate through the core at cruise conditions, is at least 4. The engine includes an engine heat management system and an actuator configured to actuate at least one valve within that system. The engine includes a fuel supply system to supply fuel to fueldraulically drive the actuator. The actuator is configured to actuate said valve to enable non-binary position adjustment between an open and closed valve positions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.