| 摘要 |
The strainer (30) has an interior space (46) partially delimited by a filtering structure (38) through which fuel is circulated from the interior space towards the outside of the strainer. Heating systems are electrically powered, where the heating systems comprise heating resistors. Bottom (44) of the strainer is formed opposite to an inlet (34) in a principal flow direction of the fuel through the inlet, where the bottom of the strainer is covered by a thermally insulated coating. The heating systems are mounted on the bottom of the strainer. Independent claims are also included for the following: (1) a turboshaft engine for an aircraft comprising fuel injection system (2) a method for controlling a fuel injection system for a turboshaft engine of aircraft. |
