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    • 6. 发明公开
    • SHOCKWAVE INJECTOR NOZZLE
    • STOSSWELLENEINSPRITZDÜSE
    • EP1295028A4
    • 2006-12-13
    • EP01947032
    • 2001-06-29
    • ORBITAL ENG PTY
    • MURDOCH PETER JOHN
    • B05B1/30B05B7/00B05B7/04F02M61/06F02M61/08F02M61/18F02M67/12
    • F02M61/06B05B1/3073B05B7/00F02M61/08F02M61/1873F02M67/12F23D11/005F23D11/12F23D11/34
    • A system for assisting in the atomisation of liquid particles conveyed in a gas stream flowing along a flow path having a rigid boundary, said system involving the creation of one or more shock waves in the gas stream. In a preferred embodiment, the system comprises a fuel injection nozzle (10) comprising a fluid flow passage (43) terminating at a discharge orifice (15) and incorporating a delivery port (33) defined between a valve seat (31) and a valve member (23) movable with respect to the valve seat for opening and closing the delivery port. Fuel is delivered along the fluid flow passage (43) into a combustion chamber through the discharge orifice (15) upon opening of the delivery port (33). The valve member (23) devines an inner boundary surface (47) of the flow passage (43) and the valve seat (31) defines at least part of an outer boundary surface (45) of the flow passage (43). The inner and outer boundary surfaces (47, 45) are configured to generate one or more shock waves in an air-fuel mixture flowing at supersonic speed therebetween.
    • 一种用于辅助雾化在沿具有刚性边界的流动路径流动的气流中输送的液体颗粒的系统,所述系统涉及在气流中产生一个或多个冲击波。 在优选实施例中,该系统包括燃料喷嘴(10),该燃料喷嘴包括终止于排放孔口(15)并且包括限定在阀座(31)和阀门之间的输送端口(33)的流体流动通道(43) 构件(23)可相对于阀座移动以打开和关闭输出口。 当输送口(33)打开时,燃料沿流体流动通道(43)通过排放孔(15)输送到燃烧室中。 阀构件23分隔流道43的内边界表面47并且阀座31限定流道43的外边界表面45的至少一部分。 内部和外部边界表面(47,45)被配置为在其间以超音速流动的空气 - 燃料混合物中产生一个或多个冲击波。