发明名称 Dual nozzle single pump fuel injection system
摘要 A fuel-injection system for a stratified charge hybrid internal combustion engine including a main combustion chamber and prechamber, fuel injectors in both the main chamber and the prechamber which open at higher and lower pressure levels respectively to sequentially inject fuel into the prechamber and main chamber. The system also includes a timed-spark ignition means in the prechamber and an engine-driven and timed fuel injection pump having a variable output capacity which varies with the power level requirements, the injection pump being supplied by a low pressure charge pump. The injection system further includes a shuttle valve with a shuttle spool positioned therein defining a prechamber supply chamber on one side thereof and a spool activation chamber on the opposite side; the initial charge from the injection pump actuates the spool means from its first to its second position valving closed charging pressure into the prechamber supply chamber with further displacement of the spool supplying the charge for the prechamber injector until the spool means reaches a stop whereupon the fuel pressure from the injection pump rises to the opening pressure level of the main injector, flowing through the spool actuation chamber to the main injector and an electrical ignition trigger means positioned in the shuttle valve which fires the ignition means as the spool means moves from its first position.
申请公布号 US5090378(A) 申请公布日期 1992.02.25
申请号 US19910661832 申请日期 1991.02.22
申请人 THE CESSNA AIRCRAFT COMPANY 发明人 GONZALEZ, CESAR
分类号 F02B1/04;F02B19/10;F02M45/06;F02M59/08;F02M59/32;F02M63/02 主分类号 F02B1/04
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