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    Fuel injection systems for internal combustion engines
    73.
    发明公开
    Fuel injection systems for internal combustion engines 失效
    KraftstoffeinspritzsystemenfürBrennkraftmaschinen。

    公开(公告)号：EP0499741A1

    公开(公告)日：1992-08-26

    申请号：EP91310147.3

    申请日：1991-11-04

    Applicant: The Cessna Aircraft Company

    Inventor： Gonzalez, Cesar

    IPC: F02B19/10 ,  F02M59/32 ,  F02M45/02

    CPC classification number: F02M59/32 ,  F02B1/04 ,  F02B19/108 ,  F02B19/1085 ,  F02M45/06 ,  F02M59/08 ,  F02M63/02 ,  Y02T10/125

    Abstract: A fuel injection system for a stratified charge hybrid internal combustion engine includes a main combustion chamber and a precombustion chamber, and fuel injectors (56, 54) in both the main chamber and the precombustion chamber which open at higher and lower pressure levels respectively to sequentially inject fuel into the precombustion chamber and main chamber. The system also includes a timed-spark ignition trigger (58) in the precombustion chamber, and an engine-driven and timed fuel injection pump (12) having a variable output capacity which varies with the engine power level requirements, the injection pump (12) being supplied by a low pressure charge pump (26). The injection system further includes a shuttle valve (30) with a shuttle spool (36) positioned therein defining a precombustion chamber supply chamber (40) on one side thereof and a spool activation chamber (38) on the opposite side.
    An initial charge from the injection pump (12) displaces the spool (36) from its first (right-hand) to its second (left-hand) position. The initial part of this displacement valves-off the supply of fuel into the supply chamber (40), and further displacement causes the spool (36) to supply a charge of fuel to the prechamber injector (54) until the spool reaches its second position defined by a stop (61). Thereafter, the fuel pressure from the injection pump (12) acting in the spool actuation chamber (38) rises to the opening pressure level of the main injector (56), and fuel flows through the spool actuation chamber to the main injector. The trigger (58) positioned in the shuttle valve fires the ignition means as the spool moves from its first position.

    Abstract translation: 用于分层电荷混合内燃机的燃料喷射系统包括主燃烧室和预燃室，以及主室和预燃室中的燃料喷射器（56,54），其分别在较高和较低压力水平下分别打开 将燃料喷入预燃室和主室。 该系统还包括在预燃室中的定时火花点火触发器（58）和具有根据发动机功率水平要求而变化的可变输出能力的发动机驱动和定时燃料喷射泵（12），喷射泵（12 ）由低压电荷泵（26）供应。 注射系统还包括梭阀（30），其具有位于其中的梭阀芯（36），其在其一侧限定预燃室供应室（40）和在相对侧上的阀芯活塞室（38）。 来自注射泵（12）的初始充电将阀芯（36）从其第一（右侧）位置移动到其第二（左侧）位置。 该位移的初始部分阀 - 将供应燃料供应到供应室（40）中，并且进一步的位移导致阀芯（36）向前室喷射器（54）供应燃料，直到阀芯到达其第二位置 由停止（61）限定。 此后，作用在阀芯致动室38中的来自喷射泵12的燃料压力上升到主喷射器56的打开压力水平，燃料通过阀芯致动腔流入主喷射器。 当阀芯从其第一位置移动时，定位在梭阀中的触发器（58）启动点火装置。

    Internal combustion engine detonation indication system
    74.
    发明公开
    Internal combustion engine detonation indication system 失效
    用于内燃机的爆震指示系统

    公开(公告)号：EP0715160A3

    公开(公告)日：1997-01-29

    申请号：EP95308572.7

    申请日：1995-11-29

    Applicant: The Cessna Aircraft Company

    Inventor： Gonzalez, Cesar ,  Cheek, James

    IPC: G01L23/22

    CPC classification number: G01L23/225 ,  G01L23/222

    Abstract: The invention relates to a detonation indication system for an internal combustion piston engine of an aircraft, which senses detonation by means of a sensor comprising a piezoelectric force transducer (12) installed under a the spark plug of each cylinder of the engine. The transducer produces an on-going combustion pressure-induced charge signal which is converted into a voltage signal by a charge converter (14). A comparator gating circuit (16) removes, from the voltage signal, signal components, associated with intake and exhaust strokes, which occur below a predetermined combustion pressure. A high-pass frequency filter (18) then removes signal components associated with low frequency changes in combustion pressure. The output from the filter (18) is applied to an RMS-to-direct current converter (20) which converts the output into a direct current voltage proportional to the RMS value of the filter output. The output from the converter (20) is applied to peak and hold circuitry (22) which holds the peak value of the converter output corresponding to the most severe detonation event which occurs during an adjustable reset time period. A digital display (24) is provided which receives signals from the circuit (22) corresponding to the peak values occurring during successive reset periods and provides a numerical read-out indicative of the severity of the associated detonation events.

    Fuel blending system, method and apparatus
    75.
    发明公开
    Fuel blending system, method and apparatus 失效
    用于燃料混合系统，方法和装置

    公开(公告)号：EP0733796A2

    公开(公告)日：1996-09-25

    申请号：EP95308887.9

    申请日：1995-12-07

    Applicant: The Cessna Aircraft Company

    Inventor： Gonzalez, Cesar

    IPC: F02M37/00 ,  B67D5/56

    CPC classification number: F02D33/006 ,  F02D19/0628 ,  F02D19/0649 ,  F02D19/0665 ,  F02D19/0676 ,  F02D19/0684 ,  F02D19/0694 ,  F02D19/081 ,  F02D19/082 ,  F02M37/0052 ,  F02M37/0064 ,  F02M37/0088 ,  F02M37/20 ,  Y02T10/36

    Abstract: 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.

    Controllable pitch aircraft propeller
    79.
    发明公开
    Controllable pitch aircraft propeller 失效
    可调螺旋桨叶片的角度。

    公开(公告)号：EP0200337A2

    公开(公告)日：1986-11-05

    申请号：EP86302082.2

    申请日：1986-03-20

    Applicant: The Cessna Aircraft Company

    Inventor： Voisard, Walter Bryan

    IPC: B64C11/38

    CPC classification number: B64C11/38

    Abstract: A variable pitch propeller has blades (36), the position of which, at relatively low pitch angles is controlled by a beta valve through a lever (23) and a feedback collar (25), the position of the collar being controlled by a plurality of beta feedback rods (55). There is one rod (55) for each blade of the propeller, and the movement of the rods (55) is controlled by a blade yoke (50) which has arms (52) partially encircling the rods (55). A lost motion connection in the form of a sleeve (60) is carried on each of the rods (55) and is movable against a retraction spring (62) by the arms (52). A movable stop mechanism (75) engages the feedback rods (55) at a particular low blade angle position and temporarily interrupts the movement of the feedback rods (55) while the sleeves (60) move to a seated position against the retraction spring (62), and thereafter the movement of the rods (55) is again picked up, accompanied by movement of the stop mechanism (75) against a spring (80). The lost motion connection represented by the sleeve (60) permits movement of the blades under control of the beta feedback valve without accompanying movement of the feedback rod which causes a shifting of the blades to a still lower pitch position, thereafter followed by reclosing of the feedback valve with continued movement of the rods (55).

    Fuel blending system, method and apparatus
    80.
    发明公开
    Fuel blending system, method and apparatus 失效
    Anlage，Verfahren und Vorrichtung zum Mischen von Brennstoffen

    公开(公告)号：EP0733796A3

    公开(公告)日：1997-01-29

    申请号：EP95308887.9

    申请日：1995-12-07

    Applicant: The Cessna Aircraft Company

    Inventor： Gonzalez, Cesar

    IPC: F02M37/00 ,  B67D5/56

    CPC classification number: F02D33/006 ,  F02D19/0628 ,  F02D19/0649 ,  F02D19/0665 ,  F02D19/0676 ,  F02D19/0684 ,  F02D19/0694 ,  F02D19/081 ,  F02D19/082 ,  F02M37/0052 ,  F02M37/0064 ,  F02M37/0088 ,  F02M37/20 ,  Y02T10/36

    Abstract: 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.

    Abstract translation: 该系统包括一个带有两个入口和一个出口的可调混合阀。 每个输入口连接到相应燃料泵的排放管线。 混合阀包括阀芯装置，当其移动时，当其降低另一燃料的一部分以改变来自出口的混合流的辛烷值时，随着其移动，增加一个参考燃料的部分。 浮动控制针阀定位在混合燃料流动路径中，其将混合燃料流量限制到发动机燃烧的燃料流量。 感测来自所包括的流量计的流量的一体化处理装置，以计算混合流中每种测试燃料A和B的百分比和辛烷值。

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