曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Ejector Pump Operation
Ejector pumps operate on the same principle as the venturi tube, and have no moving parts. The high-pressure stream of fuel at the ejector’s motive flow nozzle induces a large volume of fuel to flow into the intake of the ejector. The fuel then enters the feed lines and flows under pressure.
FUEL SYSTEM Description Vol. 2 12.10.7
Oct 05/06
Main Ejector and Ejector Operation
Figure 12.10.6
FUEL SYSTEM Description Vol. 2 12.10.8
Oct 05/06
Main Ejector Pump
There are two main ejector pumps (left and right), located on top of their respective collector tanks. They receive pressurized fuel from their on-side engine’s motive flow supply, and deliver an uninterrupted fuel supply from the collector tank to the respective engine. In addition, the main ejector provides the motive flow fuel supply to the on-side transfer ejector pump. Main ejector motive flow fuel is prevented from feeding the cross-side engine by a one-way check valve.
Scavenge Ejector Pump
The left and right scavenge ejector pumps are located at the lowest inboard point in each main (wing) tank. The scavenge ejectors’ motive flow is created by the high-pressure fuel output of the engine-driven pumps. The scavenge ejectors transfer fuel from the main tanks to the collector tanks.
Transfer Ejector Pump
The left and right transfer ejector pumps are located at the lowest point of the center auxiliary tank. Their motive flow supply is derived from their on-side main ejector pump output. The transfer ejectors continuously transfer fuel to the main tanks, maintaining them filled to 93% capacity. A float valve, located in the forward area of each main tank, prevents this transfer until main tank fuel quantity is at or below 93% capacity.
Engine Fuel Shutoff Valves
One electrically controlled engine fuel shutoff valve (“firewall” SOV) is installed on each engine fuel feed line, ahead of the engine-driven pump. When activated by pushing the L (R) ENG FIRE PUSH switch/light on the pilot’s or copilot’s glareshield, the SOV will close, stopping the flow of fuel to the engine, and the BOTTLE ARMED PUSH TO DISCH switch/lights will illuminate. Successful closing of the engine fuel shutoff valve is indicated by a L (R) ENG SOV CLOSED advisory EICAS message. If the valve fails to close, a L (R) ENG SOV caution EICAS message is displayed.
The engine fuel shutoff valves are powered by the DC emergency bus. For additional information, see Chapter 9, Fire Protection.
Fuel Filter
The engine-driven pumps are each equipped with a fuel filter. The filters are mounted adjacent to the oil tank within the engine nacelle, and are monitored for contamination by an impending bypass switch. An indication of impending bypass (filter clogged) is the L (R) FUEL FILTER caution EICAS message.
中国公务机网 www.gongwuji.com
公务机翻译 www.aviation.cn
本文链接地址：庞巴迪挑战者605公务机机组操作手册 CL605-燃油系统 FUEL SYSTEM(5)
| 
