Gas turbine engine fuel control method
US6584762B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 27, 2002 |
| Grant date | Jul 1, 2003 |
| Priority date | — |
| Expiry date | Nov 27, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/54
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydraulic pump to provide pressurized fluid for exhaust nozzle actuation. An augmentor fuel bypass arrangement is provided to enable the augmentor fuel pump to provide pressurized fuel to the main fuel pressurizing valve and to components operated by the main fuel system in the event of failure of the main fuel pump. The augmentor fuel pump pressure and output flow are controlled as a function of thrust augmentation demand and main fuel system operation. The system provides redundancy by enabling either the main fuel system or the augmentor fuel system to maintain engine operation if one of the fuel systems fails or provides inadequate fuel flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.