Aircraft load shedding system including supplementary power sources for assuring DC and device for cutting off power to the alternators of a turbine engine during acceleration
US9988158B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 22, 2014 |
| Grant date | Jun 5, 2018 |
| Priority date | — |
| Expiry date | Aug 9, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldElectrical machinery, apparatus, energy
- WIPO sectorElectrical engineering
Abstract
A DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, includes at least one electrical energy storage capacity, at least one generator driven mechanically by a rotation shaft of the turbine engine and electrical connections between the electrical energy storage capacity, the generator and the aircraft equipment for powering the above-mentioned equipment with DC current, also including at least one alternative for supplying DC current to the equipment, which are autonomous in relation to any mechanical driving by a rotation shaft of the turbine engine, and a device that can cut-off power to the generator(s) and simultaneously activate the alternative current supply. The power cut-off device for triggering power cut-off and activating the alternative current supply is controlled by a control or operating parameter of the turbine engine. The alternative current supply is preferably formed by one or more supercapacitors.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.