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    TURBOFAN ENGINE OPERATION CONTROL
    2.
    发明公开
    TURBOFAN ENGINE OPERATION CONTROL 审中-公开
    涡轮增压发动机运行控制

    公开(公告)号：EP3141730A1

    公开(公告)日：2017-03-15

    申请号：EP16186992.0

    申请日：2006-10-12

    申请人： United Technologies Corporation

    发明人： The designation of the inventor has not yet been filed

    IPC分类号： F02K1/12 ,  F02K1/16 ,  F02K3/075

    CPC分类号： F02K1/16 ,  F02K1/1207 ,  F02K3/075 ,  F05D2220/327

    摘要： A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.

    摘要翻译： 提供涡扇发动机（10），其包括线轴（14）。 阀芯（14）支撑涡轮机（18）并容纳在核心机舱（12）内。 风扇（20）联接到阀芯（14）并且包括目标可操作性线。 目标可操作性线提供期望的燃料消耗，发动机性能和/或风扇可操作性裕度。 风扇机舱（34）围绕风扇（20）和核心机舱（12）以提供具有喷嘴出口区域（40）的旁路流动路径（39）。 控制器（50）被编程以命令流量控制装置（41）改变喷嘴出口区域（40）。 响应于作为空速和节气门位置的函数的发动机操作条件，喷嘴出口区域（40）的变化实现目标可操作性线。 喷嘴出口区域（40）的变化被用于通过操纵风扇压力比将操作线朝向风扇失速或颤动边界移动。

    Turbofan engine with variable bypass nozzle exit area and method of operation
    4.
    发明公开
    Turbofan engine with variable bypass nozzle exit area and method of operation 有权
    带有可变旁路喷嘴出口区域的涡轮风扇发动机和操作方法

    公开(公告)号：EP2426342A2

    公开(公告)日：2012-03-07

    申请号：EP11186123.3

    申请日：2006-10-12

    申请人： United Technologies Corporation

    发明人： Winter, Michael

    IPC分类号： F02K1/30 ,  F02K3/06

    CPC分类号： F02K1/30 ,  F02C6/08 ,  F02C7/36 ,  F02K1/16 ,  F02K3/06 ,  F05D2260/4031

    摘要： A turbofan engine includes core and fan nacelles that provide a bypass flow path having a nozzle exit area. The bypass flow path carries a bypass flow to be expelled from the nozzle exit area. A turbofan is arranged within the fan nacelle and upstream from the core nacelle for generating the bypass flow. A flow control device includes a surface in the bypass flow path including an aperture. The flow device is adapted to introduce a fluid into the bypass flow path for altering a boundary layer of the bypass flow that effectively changes the nozzle exit area. In one example, bleed air is introduced through the aperture. In another example, pulses of fluid from a Helmholz resonator flow through the aperture. By decreasing the boundary layer, the nozzle exit area is effectively increased. By increasing the boundary layer, the nozzle exit area is effectively decreased.

    摘要翻译： 涡轮风扇发动机包括提供具有喷嘴出口区域的旁路流动路径的核心和风扇机舱。 旁路流路承载旁路流从喷嘴出口区域排出。 涡轮风扇布置在风扇机舱内并且在核心机舱的上游用于产生旁路流。 流量控制装置包括在旁路流路中的包括孔的表面。 流动装置适于将流体引入旁路流动路径中以改变旁路流动的边界层，其有效地改变喷嘴出口区域。 在一个例子中，引气通过孔引入。 在另一个例子中，来自亥姆霍兹共振器的流体脉冲流过该孔。 通过减小边界层，喷嘴出口面积有效地增加。 通过增加边界层，喷嘴出口面积有效地减小。

    TURBOFAN ENGINE OPERATION CONTROL
    6.
    发明公开
    TURBOFAN ENGINE OPERATION CONTROL 审中-公开
    控制涡扇发动机运​​行

    公开(公告)号：EP2074314A1

    公开(公告)日：2009-07-01

    申请号：EP06851137.7

    申请日：2006-10-12

    申请人： United Technologies Corporation

    发明人： MCVEY, William J.

    IPC分类号： F02K1/12 ,  F02K1/16 ,  F02K3/075

    CPC分类号： F02K1/16 ,  F02K1/1207 ,  F02K3/075 ,  F05D2220/327

    摘要： A turbofan engine (10) is provided that includes a spool (14). The spool (14) supports a turbine (18) and is housed within a core nacelle (12). A fan (20) is coupled to the spool (14) and includes a target operability line. The target operability line provides desired fuel consumption, engine performance, and/or fan operability margin. A fan nacelle (34) surrounds the fan (20) and core nacelle (12) to provide a bypass flow path (39) having a nozzle exit area (40). A controller (50) is programmed to command a flow control device (41) for changing the nozzle exit area (40). The change in nozzle exit area (40) achieves the target operability line in response to an engine operating condition that is a function of airspeed and throttle position. A change in the nozzle exit area (40) is used to move the operating line toward a fan stall or flutter boundary by manipulating the fan pressure ratio.

    GAS TURBINE WITH MOVEABLE EXHAUST PLUG
    7.
    发明公开
    GAS TURBINE WITH MOVEABLE EXHAUST PLUG 审中-公开

    公开(公告)号：EP3412902A1

    公开(公告)日：2018-12-12

    申请号：EP18177104.9

    申请日：2018-06-11

    申请人： United Technologies Corporation

    发明人： BENT, Andre L. ,  ZYSMAN, Steven H. ,  SAWYERS-ABBOTT, Nigel David

    IPC分类号： F02K1/08 ,  F02K1/16 ,  F02K1/72

    CPC分类号： F02K1/70 ,  F02C3/04 ,  F02K1/08 ,  F02K1/16 ,  F02K1/72 ,  F02K3/06 ,  F05D2260/57 ,  F05D2270/62 ,  F05D2270/65

    摘要： An exhaust section (78) of a gas turbine engine includes an exhaust plug (58), and an exhaust nozzle (60) radially offset from the exhaust plug defining an exhaust pathway (80) between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser (68) to divert a fan airflow (70) from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.