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    • 131. 发明公开
    • Fuel filter with cold start circuit
    • Brennstoffilter和Kaltstartkreislauf
    • EP0887542A2
    • 1998-12-30
    • EP98111469.7
    • 1998-06-22
    • STANADYNE AUTOMOTIVE CORP.
    • Janik, Leon P.Williams, Michael J.Atwood, Richard E.
    • F02M37/00
    • F02D33/006F02M37/0035F02M37/0052F02M37/221F02M2037/225F02M2037/226
    • A fuel circuit (10) for a fuel system (12) including a fuel tank (14), a fuel injection system, and a fuel filter assembly (18). Excess fuel flow is recirculated from the fuel injection pump (16) to the base of the fuel filter (18). The base includes an internal recirculated fuel passageway which is in fluid communication with the fuel injection pump (16) and the fuel tank (14), an internal fuel inlet plenum that is in fluid communication with the fuel tank (14), and an internal fuel outlet passageway which is in fluid communication with the fuel injection system. An opening provides fluid communication between the recirculated fuel passageway and the fuel inlet plenum. A thermal flow control valve (62) is positioned in the recirculated fuel passageway to open the opening when the recirculated fuel temperature is below a predetermined temperature and to close the opening when the recirculated fuel temperature is above the predetermined temperature. For pressurized fuel systems, a constant vent passageway (70) provides fluid communication between the fuel outlet passageway and the recircuiated fuel passageway to vent air from the fitter assembly (18).
    • 一种用于燃料系统(12)的燃料回路(10),包括燃料箱(14),燃料喷射系统和燃料过滤器组件(18)。 过多的燃料流从燃料喷射泵(16)再循环到燃料过滤器(18)的底部。 底座包括与燃料喷射泵(16)和燃料箱(14)流体连通的内部再循环燃料通道,与燃料箱(14)流体连通的内部燃料入口增压室 燃料出口通道,其与燃料喷射系统流体连通。 开口提供再循环燃料通道和燃料入口通风室之间的流体连通。 当再循环燃料温度低于预定温度时,热流控制阀(62)定位在再循环燃料通道中以打开开口,并且当再循环燃料温度高于预定温度时关闭开口。 对于加压燃料系统,恒定的排气通道(70)在燃料出口通道和再循环燃料通道之间提供流体连通,以便从装配工组件(18)排出空气。
    • 136. 发明公开
    • Fuel blending system, method and apparatus
    • 用于燃料混合系统,方法和装置
    • EP0733796A2
    • 1996-09-25
    • EP95308887.9
    • 1995-12-07
    • The Cessna Aircraft Company
    • Gonzalez, Cesar
    • F02M37/00B67D5/56
    • F02D33/006F02D19/0628F02D19/0649F02D19/0665F02D19/0676F02D19/0684F02D19/0694F02D19/081F02D19/082F02M37/0052F02M37/0064F02M37/0088F02M37/20Y02T10/36
    • The invention relates to an on-board and in-line fuel blending system of two reference fuels (A, B) of known octane ratings for an aircraft or land vehicle piston engine. First and second fuel tanks (12, 14) are provided for the respective test fuels (A, B), each associated with a constant pressure pump (18, 20) and discharge line (22, 24) for supplying a constant pressure of both fuels (A, B). An adjustable blending valve (16) is provided, having two entry ports connected one to each of the discharge lines of the respective pumps. The blending valve includes a spool (36) which, as it moves, increases the portion of one reference fuel and decreases the portion of the other fuel, to vary the octane rating of the blended-flow from an exit port of the blending valve (16). A first flow meter (32) is located in the discharge line (22) of the constant pressure pump (18), and a second flow meter (34) is located in the exit line (44) for blended fuel flowing from the blending valve (16). A float-controlled needle valve (46) is positioned in the line (44) which limits the blended fuel flow to that which the engine is burning. Processing means (86, 90) senses the flow from both flow meters (32, 34) and computes the percent of each test fuel (A, B) in the blend, and also the octane rating of the blended stream.
      Based on appropriate calibration blending curves, the system will provide instantaneous indications of both lean and rich performance ratings of the fuel. Instantaneous lean and rich performance ratings of the blended fuel streams may be recorded concurrently with engine parameters and ambient test data, and with combustion knock severity numbers derived from an associated detonation indication system.