Power system for aircraft parallel hybrid gas turbine electric propulsion system
US11371430B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 1, 2016 |
| Grant date | Jun 28, 2022 |
| Priority date | — |
| Expiry date | Mar 25, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/85
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.