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9 条记录 (耗时 0.025 秒)

    Methods and systems for controlling gas turbine clearance
    1.
    发明授权
    Methods and systems for controlling gas turbine clearance 有权
    控制燃气轮机间隙的方法和系统

    公开(公告)号：US08038382B2

    公开(公告)日：2011-10-18

    申请号：US12775566

    申请日：2010-05-07

    申请人： Tagir Nigmatulin ,  Jonathan Carl Thatcher ,  Jesse Edwin Trout ,  Roger Clayton Walker

    发明人： Tagir Nigmatulin ,  Jonathan Carl Thatcher ,  Jesse Edwin Trout ,  Roger Clayton Walker

    IPC分类号： F01B25/00 ,  F01D19/02 ,  F01D25/10

    CPC分类号： F01D11/20 ,  F01D11/24 ,  F05D2260/80 ,  F05D2270/303

    摘要： Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.

    摘要翻译： 提供了用于控制燃气轮机间隙的系统和方法。 可以确定燃气轮机的轴的温度，并且可以基于轴的温度来确定涡轮机的内涡轮壳体的期望温度。 内涡轮壳体的期望温度可以与涡轮机间隙相关联，在那里可以点燃燃气涡轮机。 可以通过控制在内涡轮机壳体内循环的气体的温度来改变内涡轮机壳体的温度，并且可以确定内涡轮机壳体的温度超过所需温度。 在确定内涡轮壳体的温度超过所需温度之后，可以点燃燃气轮机。

    Methods and Systems for Controlling Gas Turbine Clearance
    2.
    发明申请
    Methods and Systems for Controlling Gas Turbine Clearance 有权
    控制燃气轮机间隙的方法与系统

    公开(公告)号：US20100218506A1

    公开(公告)日：2010-09-02

    申请号：US12775566

    申请日：2010-05-07

    申请人： Tagir Nigmatulin ,  Jonathan Carl Thatcher ,  Jesse Edwin Trout ,  Roger Clayton Walker

    发明人： Tagir Nigmatulin ,  Jonathan Carl Thatcher ,  Jesse Edwin Trout ,  Roger Clayton Walker

    IPC分类号： F02C1/00

    CPC分类号： F01D11/20 ,  F01D11/24 ,  F05D2260/80 ,  F05D2270/303

    摘要： Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.

    摘要翻译： 提供了用于控制燃气轮机间隙的系统和方法。 可以确定燃气轮机的轴的温度，并且可以基于轴的温度来确定涡轮机的内涡轮壳体的期望温度。 内涡轮壳体的期望温度可以与涡轮机间隙相关联，在那里可以点燃燃气涡轮机。 可以通过控制在内涡轮机壳体内循环的气体的温度来改变内涡轮机壳体的温度，并且可以确定内涡轮机壳体的温度超过所需温度。 在确定内涡轮壳体的温度超过所需温度之后，可以点燃燃气轮机。

    Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles
    5.
    发明申请
    Angel wing seals for turbine blades and methods for selecting stator, rotor and wing seal profiles 失效
    用于涡轮叶片的天使翼形密封件和用于选择定子，转子和翼形密封型材的方法

    公开(公告)号：US20070224035A1

    公开(公告)日：2007-09-27

    申请号：US11229096

    申请日：2005-09-16

    申请人： Tagir Nigmatulin

    发明人： Tagir Nigmatulin

    IPC分类号： F04D29/08

    CPC分类号： F01D11/02 ,  F01D5/20 ,  F05D2250/70 ,  Y02T50/67

    摘要： Angel wing seals for turbines are described. In one aspect, an angel wing seal between a rotor blade and nozzle in a turbine inhibits ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces. The seal includes, in an example embodiment, a seal body extending from a shank of the blade and generally toward the nozzle. The seal body has at least one concave surface.

    摘要翻译： 描述了涡轮机的天使翼密封件。 在一个方面，转子叶片和涡轮喷嘴之间的天使翼密封件抑制了从通过涡轮机的热气流中吸入热气体到涡轮机叶轮空间。 在示例性实施例中，密封件包括从叶片的柄部延伸并且大致朝向喷嘴延伸的密封体。 密封体具有至少一个凹面。

    RESILIENT SEAL ON TRAILING EDGE OF TURBINE INNER SHROUD AND METHOD FOR SHROUD POST IMPINGEMENT CAVITY SEALING
    7.
    发明申请
    RESILIENT SEAL ON TRAILING EDGE OF TURBINE INNER SHROUD AND METHOD FOR SHROUD POST IMPINGEMENT CAVITY SEALING 有权
    风力涡轮机内部风力发动机的密封和风速冲击密封的方法

    公开(公告)号：US20070237624A1

    公开(公告)日：2007-10-11

    申请号：US11226393

    申请日：2005-09-15

    申请人： Tagir Nigmatulin

    发明人： Tagir Nigmatulin

    IPC分类号： F03B11/00

    CPC分类号： F02C7/28 ,  F01D11/005 ,  F01D11/08 ,  F05D2240/11

    摘要： A sealing arrangement for the post impingement cavity of a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine energy efficiency. The stator shroud segment includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds, each having a leading edge hook and a trailing edge hook. The leading and trailing hooks of each of the inner shrouds are respectively engaged with the leading and trailing edge grooves of the outer shroud so as to connect the inner shroud to the outer shroud. The resilient shaped seal is located at a trailing edge of the respectively engaged inner and outer shrouds at an interface of the inner shroud and the outer shroud. In an example embodiment, a sealing groove is defined in the outer shroud for receiving the aft resilient seal.

    摘要翻译： 提供了一种用于定子护罩段的后冲击腔的密封装置，其包括用于减少空气泄漏并提高涡轮能量效率的弹性密封件。 定子护罩区段包括具有前缘槽和后缘槽的外护罩; 以及多个内护罩，每个内护罩具有前缘钩和后缘钩。 每个内护罩的引导钩和尾钩分别与外护罩的前缘和后缘槽啮合，以将内护罩连接到外护罩上。 弹性形状的密封件位于内护罩和外护罩的界面处的分别接合的内护罩和外护罩的后缘。 在一个示例性实施例中，密封槽限定在外护罩中用于接收后弹性密封。

    Turbine shroud cooling hole diffusers and related method
    9.
    发明授权
    Turbine shroud cooling hole diffusers and related method 有权
    涡轮罩冷却孔扩散器及相关方法

    公开(公告)号：US06554566B1

    公开(公告)日：2003-04-29

    申请号：US09983996

    申请日：2001-10-26

    申请人： Tagir Nigmatulin

    发明人： Tagir Nigmatulin

    IPC分类号： F01D1108

    CPC分类号： F01D11/08 ,  F01D25/12 ,  F05D2260/20

    摘要： An inner shroud assembly for a turbine comprising a plurality of part-annular segments combining to form an inner, annular shroud adapted to surround rotating components of a turbine, each segment having a pair of end faces that are juxtaposed similar end faces on adjacent segments with gaps therebetween; at least one convection cooling hole in the segment, opening along at least one of the pair of end faces. The cooling hole opens specifically into a diffuser recess formed in one of the pair of end faces for diffusing the flow of cooling air into the gap.

    摘要翻译： 一种用于涡轮机的内护罩组件，包括多个部分环形段，其结合以形成适于围绕涡轮机的旋转部件的内部环形护罩，每个段具有一对端面，其在相邻段上并置相似的端面， 间隙; 所述段中的至少一个对流冷却孔沿着所述一对端面中的至少一个开口。 冷却孔特别地形成在一对端面中的一个中形成的扩散器凹部，用于将冷却空气流扩散到间隙中。