Poppet valve with sloped purge holes and method for reducing a pressure force therein
    2.
    发明授权
    Poppet valve with sloped purge holes and method for reducing a pressure force therein 有权
    具有倾斜吹扫孔的提升阀和减小其中的压力的​​方法

    公开(公告)号:US08453670B2

    公开(公告)日:2013-06-04

    申请号:US12183133

    申请日:2008-07-31

    IPC分类号: F16K17/34

    摘要: A poppet valve is disclosed that includes a valve body, a poppet guide disposed inside the valve body so as to form a flow passage from an inlet to an outlet of the valve, a poppet shutter disposed inside the poppet guide, and a biasing member to bias the poppet shutter away from the poppet guide toward an inside surface of the flow inlet so as to block the flow passage. The poppet valve further includes at least one discharge hole placing an inner chamber of the poppet guide in flow communication with a region of low static pressure of the flow passage. A method for reducing a closing pressure force acting on a poppet shutter of a poppet valve is also disclosed.

    摘要翻译: 提供了一种提升阀,其包括阀体,设置在阀体内的提升阀引导件,以形成从阀门的入口到出口的流动通道,设置在提升引导件内的提升阀,以及偏置构件 将提升阀从提升阀引导件朝向流入口的内表面偏压以阻止流动通道。 提升阀还包括至少一个排出孔,其将提升阀导向件的内部腔室与流动通道的低静态压力区域流动连通。 还公开了一种减小作用在提升阀的提升阀上的关闭压力的方法。

    POPPET VALVE WITH SLOPED PURGE HOLES AND METHOD FOR REDUCING A PRESSURE FORCE THEREIN
    4.
    发明申请
    POPPET VALVE WITH SLOPED PURGE HOLES AND METHOD FOR REDUCING A PRESSURE FORCE THEREIN 有权
    带倾斜孔的阀门和减压阀的方法

    公开(公告)号:US20100025601A1

    公开(公告)日:2010-02-04

    申请号:US12183133

    申请日:2008-07-31

    IPC分类号: F16K31/122

    摘要: A poppet valve is disclosed that includes a valve body, a poppet guide disposed inside the valve body so as to form a flow passage from an inlet to an outlet of the valve, a poppet shutter disposed inside the poppet guide, and a biasing member to bias the poppet shutter away from the poppet guide toward an inside surface of the flow inlet so as to block the flow passage. The poppet valve further includes at least one discharge hole placing an inner chamber of the poppet guide in flow communication with a region of low static pressure of the flow passage. A method for reducing a closing pressure force acting on a poppet shutter of a poppet valve is also disclosed.

    摘要翻译: 提供了一种提升阀,其包括阀体,设置在阀体内的提升阀引导件,以形成从阀门的入口到出口的流动通道,设置在提升引导件内的提升阀,以及偏置构件 将提升阀从提升阀引导件朝向流入口的内表面偏压以阻止流动通道。 提升阀还包括至少一个排出孔,其将提升阀导向件的内部腔室与流动通道的低静态压力区域流动连通。 还公开了一种减小作用在提升阀的提升阀上的关闭压力的方法。

    High efficiency rotor for the second phase of a gas turbine
    5.
    发明授权
    High efficiency rotor for the second phase of a gas turbine 失效
    用于燃气轮机第二阶段的高效转子

    公开(公告)号:US07390171B2

    公开(公告)日:2008-06-24

    申请号:US11100611

    申请日:2005-04-07

    申请人: Stefano Francini

    发明人: Stefano Francini

    IPC分类号: F01D5/14

    摘要: A rotor for the second phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y,Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat single ranges from 54.9° to 57.9°.

    摘要翻译: 用于低压涡轮机的第二相的转子具有一系列叶片,每个叶片各自由笛卡尔参考系(X,Y,Z)中的点的离散组合的坐标定义,其中轴线(Z)是径向 轴与涡轮机的中心轴线相交。 通过在轮廓本身与位于与中心轴线的距离(Z)处的平面(X,Y)之间的一系列闭合的交叉曲线来识别每个叶片的轮廓。 每个叶片具有平均喉角,其平均喉角由叶片中部高度处的平均喉部长度与在平均喉部点的半径处评估的圆周间距之间的比率的余弦弧确定; 平均喉咙单一范围为54.9°至57.9°。

    High efficiency stator for the second phase of a gas turbine
    6.
    发明授权
    High efficiency stator for the second phase of a gas turbine 失效
    用于燃气轮机第二相的高效率定子

    公开(公告)号:US07390165B2

    公开(公告)日:2008-06-24

    申请号:US11100625

    申请日:2005-04-07

    申请人: Stefano Francini

    发明人: Stefano Francini

    IPC分类号: F01D9/04

    CPC分类号: F01D9/041 Y10S416/02

    摘要: A stator for the second phase of a low-pressure turbine has a series of blades each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. Each blade has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 57.8° to 60.8°.

    摘要翻译: 用于低压涡轮机的第二相的定子具有由笛卡尔参考系(X,Y,Z)中的点的离散组合的坐标限定的一系列叶片,其中轴线(Z)是径向 轴与涡轮机的中心轴线相交。 通过在轮廓本身与位于与中心轴线的距离(Z)处的平面(X,Y)之间的一系列闭合的交叉曲线来识别每个叶片的轮廓。 每个叶片具有平均喉角,其平均喉角由叶片中部高度处的平均喉部长度与在平均喉部点的半径处评估的圆周间距之间的比率的余弦弧确定; 平均喉角范围为57.8°至60.8°。

    High efficiency stator for the second phase of a gas turbine
    7.
    发明申请
    High efficiency stator for the second phase of a gas turbine 失效
    用于燃气轮机第二相的高效率定子

    公开(公告)号:US20050247045A1

    公开(公告)日:2005-11-10

    申请号:US11100625

    申请日:2005-04-07

    申请人: Stefano Francini

    发明人: Stefano Francini

    CPC分类号: F01D9/041 Y10S416/02

    摘要: Stator for the second phase of a low-pressure turbine having a series of blades (1) each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X,Y,Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade (1) is identified by means of a series of closed intersection curves (20) between the profile itself and planes (X,Y) lying at distances (Z) from the central axis. Each blade (1) has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 57.8° to 60.8°.

    摘要翻译: 具有由笛卡尔参考系(X,Y,Z)中的点的组合的坐标定义的一系列叶片(1)的低压涡轮机的第二阶段的定子,其中轴线(Z)是 与涡轮机的中心轴线相交的径向轴线。 每个叶片(1)的轮廓通过在轮廓本身与位于距离中心轴线的距离(Z))的平面(X,Y)之间的一系列闭合交叉曲线(20)来识别。 每个叶片(1)具有平均喉部角度,该平均喉部角度由叶片中部高度处的平均喉部长度与在平均喉部点的半径处估计的圆周间距之间的比率的余弦弧确定; 平均喉角范围为57.8°至60.8°。

    High efficiency rotor for the second phase of a gas turbine
    8.
    发明申请
    High efficiency rotor for the second phase of a gas turbine 失效
    用于燃气轮机第二阶段的高效转子

    公开(公告)号:US20050247044A1

    公开(公告)日:2005-11-10

    申请号:US11100611

    申请日:2005-04-07

    申请人: Stefano Francini

    发明人: Stefano Francini

    摘要: Rotor for the second phase of a low-pressure turbine having a series of blades (1) each defined by coordinates of a discreet combination of points, in a Cartesian reference system (X,Y,Z), wherein the axis (Z) is a radial axis intersecting the central axis of the turbine. The profile of each blade (1) is identified by means of a series of closed intersection curves (20) between the profile itself and planes (X,Y) lying at distances (Z) from the central axis. Each blade (1) has an average throat angle defined by the cosine arc of the ratio between the average throat length at mid-height of the blade and the circumferential pitch evaluated at the radius of the average throat point; the average throat angle ranges from 54.9° to 57.9°.

    摘要翻译: 用于第二相的转子,其具有在笛卡尔参考系(X,Y,Z)中各自由点的组合的坐标定义的一系列叶片(1)的第二相,其中轴(Z)为 与涡轮机的中心轴线相交的径向轴线。 每个叶片(1)的轮廓通过在轮廓本身与位于距离中心轴线的距离(Z))的平面(X,Y)之间的一系列闭合交叉曲线(20)来识别。 每个叶片(1)具有平均喉部角度,该平均喉部角度由叶片中部高度处的平均喉部长度与在平均喉部点的半径处估计的圆周间距之间的比率的余弦弧确定; 平均咽喉角度范围为54.9°至57.9°。