Distributed aircraft engine fuel system
US8666632B2 · kind B2 · utility
15Cited by
8References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 20, 2011 |
| Grant date | Mar 4, 2014 |
| Priority date | — |
| Expiry date | Jan 26, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/31
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.