| 发明名称 |
IGNITION DEVICE FOR AN AIRCRAFT ENGINE |
| 摘要 |
A device for igniting an aircraft engine, comprising at least two spark plugs, the device comprising a power supply, a first path for supplying a first spark plug with power and a second path for supplying a second spark plug with power, said paths being connected to the power supply by distribution means of the power supply which are controlled by a FADEC-type control system, wherein said distribution means comprise a first circuit that is configured to alternately supply said first path or said second path with power, and a second circuit for simultaneously supplying said first and second paths with power, the device being configured to use either the first circuit or the second circuit during start-up. |
| 申请公布号 |
US2016222887(A1) |
申请公布日期 |
2016.08.04 |
| 申请号 |
US201414917812 |
申请日期 |
2014.09.16 |
| 申请人 |
TURBOMECA |
发明人 |
Bourgeois Nicolas;Grenier Benoît;Guichemerre Nicolas |
| 分类号 |
F02C7/266;F02P15/00;F02P15/08 |
主分类号 |
F02C7/266 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. Device for igniting an aircraft engine, comprising: at least two spark plugs, a power supply, a first path for supplying a first spark plug with power and a second path for supplying a second spark plug with power, said paths being connected to the power supply by a distributor of the power supply, wherein said distributor comprises a first circuit that is configured to alternately supply said first path or said second path with power, and a second circuit for simultaneously supplying said first and second paths with power, wherein the device is configured to use either the first circuit or the second circuit during start-up. |
| 地址 |
Bordes FR |
