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    Gas turbine bucket wall thickness control
    3.
    发明授权
    Gas turbine bucket wall thickness control 有权
    燃气轮机壁厚控制

    公开(公告)号：US06464462B2

    公开(公告)日：2002-10-15

    申请号：US09923915

    申请日：2001-08-08

    申请人： Dimitrios Stathopoulos ,  Liming Xu ,  Doyle C. Lewis

    发明人： Dimitrios Stathopoulos ,  Liming Xu ,  Doyle C. Lewis

    IPC分类号： B63H114

    CPC分类号： B22C9/103 ,  Y10T29/49341

    摘要： A core for use in casting a turbine bucket including serpentine cooling passages is divided into two pieces including a leading edge core section and a trailing edge core section. Wall thicknesses at the leading edge and the trailing edge of the turbine bucket can be controlled independent of each other by separately positioning the leading edge core section and the trailing edge core section in the casting die. The controlled leading and trailing edge thicknesses can thus be optimized for efficient cooling, resulting in more efficient turbine operation.

    摘要翻译： 用于铸造包括蛇形冷却通道的涡轮机桶的芯体被分成两部分，其包括前缘芯部分和后缘芯部分。 通过将前缘芯部分和后缘芯部分分别定位在铸模中，可以独立于彼此控制涡轮机叶片的前缘和后缘处的壁厚。 因此，受控的前缘和后缘厚度可以被优化以实现有效的冷却，从而导致更有效的涡轮机操作。

    Gas turbine bucket cooling circuit and related process
    4.
    发明授权
    Gas turbine bucket cooling circuit and related process 有权
    燃气轮机桶冷却回路及相关工艺

    公开(公告)号：US06390774B1

    公开(公告)日：2002-05-21

    申请号：US09496715

    申请日：2000-02-02

    申请人： Doyle C. Lewis ,  Kevin Joseph Barb

    发明人： Doyle C. Lewis ,  Kevin Joseph Barb

    IPC分类号： F01D508

    CPC分类号： F01D5/187 ,  B22C9/10 ,  B22C21/14 ,  F05D2240/81 ,  F05D2260/205 ,  F05D2260/2322

    摘要： A turbine bucket includes an airfoil portion having leading and trailing edges; at least one radially extending cooling passage within the airfoil portion, the airfoil portion joined to a platform at a radially inner end of the airfoil portion; a dovetail mounting portion enclosing a cooling medium supply passage; and, a crossover passage in fluid communication with the cooling medium supply passage and with at least one radially extending cooling passage, the crossover passage having a portion extending along and substantially parallel to an underside surface of the platform.

    摘要翻译： 涡轮机桶包括具有前缘和后缘的翼型部分; 在所述翼型部分内的至少一个径向延伸的冷却通道，所述翼型部分在所述翼型部分的径向内端处连接到平台; 封闭冷却介质供给通道的燕尾形安装部; 以及与所述冷却介质供应通道流体连通并且具有至少一个径向延伸的冷却通道的交叉通道，所述交叉通道具有沿所述平台的下表面延伸并且基本上平行于所述平台的下表面。

    Methods and apparatus for cooling gas turbine rotor blades
    8.
    发明授权
    Methods and apparatus for cooling gas turbine rotor blades 有权
    用于冷却燃气轮机转子叶片的方法和装置

    公开(公告)号：US07513738B2

    公开(公告)日：2009-04-07

    申请号：US11355213

    申请日：2006-02-15

    申请人： Gary Michael Itzel ,  Ariel Caesar Prepena Jacala ,  Doyle C. Lewis ,  Calvin Levy Sims

    发明人： Gary Michael Itzel ,  Ariel Caesar Prepena Jacala ,  Doyle C. Lewis ,  Calvin Levy Sims

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/205

    摘要： Methods and apparatus for cooling rotor blades of a gas turbine are provided. The turbine blade has an airfoil connected to the platform and a dovetail extending from the platform. A main cooling circuit extends through the dovetail and into the airfoil. The main cooling circuit includes an exit for main cooling flow from the airfoil to exit out through the dovetail. In one aspect, the method includes the steps of extracting a portion of the coolant flowing through the main cooling circuit into a platform cooling circuit. After cooling a portion of the platform, the platform cooling flow splits with one portion of the flow rejoining the main cooling circuit and is used to cool the airfoil. The rest of the platform cooling flow continues to cool the platform and then returns to the main cooling circuit to flow through the exit.

    摘要翻译： 提供了一种用于冷却燃气轮机的转子叶片的方法和装置。 涡轮叶片具有连接到平台的翼型件和从平台延伸的燕尾榫。 主冷却回路延伸穿过燕尾榫并进入翼型。 主冷却回路包括用于从翼型件主冷却流出的出口，通过燕尾出口。 一方面，该方法包括以下步骤：将流经主冷却回路的冷却剂的一部分提取到平台冷却回路中。 在冷却平台的一部分之后，平台冷却流将与流入主冷却回路的一部分流分开并用于冷却翼型。 平台冷却流程的其余部分继续冷却平台，然后返回到主冷却回路以流过出口。