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    TURBINE AIRFOIL CASTING METHOD
    2.
    发明申请
    TURBINE AIRFOIL CASTING METHOD 审中-公开
    涡轮机气流铸造方法

    公开(公告)号：US20090165988A1

    公开(公告)日：2009-07-02

    申请号：US11968022

    申请日：2007-12-31

    申请人： Todd Jay Rockstroh ,  Sudhir K. Tewari ,  Joseph Giancarlo Sabato ,  Donald Brett Desander ,  David Henry Abbott ,  Mark Douglas Gledhill

    发明人： Todd Jay Rockstroh ,  Sudhir K. Tewari ,  Joseph Giancarlo Sabato ,  Donald Brett Desander ,  David Henry Abbott ,  Mark Douglas Gledhill

    IPC分类号： B22D27/02 ,  B22D23/00

    CPC分类号： F01D5/187 ,  B22C9/04 ,  B22C9/10 ,  F05D2230/211 ,  F05D2260/202 ,  F05D2260/2212

    摘要： A method for making a turbine airfoil includes: (a) providing a mold having: (i) a core; (ii) an outer shell surrounding the core such that the core and the outer shell cooperatively define a cavity in the shape of an airfoil having at least one outer wall; and (iii) a core support extending from the core to the outer shell through a portion of the cavity that defines the at least one sidewall; (b) introducing molten metal alloy into the cavity and surrounding the core support; (c) solidifying the alloy to form an airfoil casting having at least one outer wall which has at least one core support opening passing therethrough; (d) removing the mold so as to expose the airfoil; and (e) sealing the at least one core support opening in the airfoil with a metal alloy metallurgically bonded to the at least one outer wall.

    摘要翻译： 一种用于制造涡轮机翼型的方法包括：（a）提供具有：（i）芯体的模具; （ii）围绕所述芯的外壳，使得所述芯和所述外壳协调地限定具有至少一个外壁的翼型形状的空腔; 和（iii）从所述芯延伸到所述外壳的芯支撑体，所述芯支撑件限定所述至少一个侧壁的所述空腔的一部分; （b）将熔融金属合金引入空腔并围绕核心支撑件; （c）固化合金以形成具有至少一个外壁的翼型铸件，所述至少一个外壁具有穿过其中的至少一个芯支撑开口; （d）去除模具以暴露翼型件; 和（e）用金属合金密封所述翼型件中的所述至少一个芯支撑开口，所述金属合金与所述至少一个外壁冶金结合。

    Hybrid impingement cooled airfoil
    5.
    发明授权
    Hybrid impingement cooled airfoil 有权
    混合冲击冷却翼型

    公开(公告)号：US08172504B2

    公开(公告)日：2012-05-08

    申请号：US12055101

    申请日：2008-03-25

    申请人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    发明人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.

    摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。

    Method and apparatus for turbine blade contoured platform
    6.
    发明授权
    Method and apparatus for turbine blade contoured platform 有权
    涡轮叶片轮廓平台的方法和装置

    公开(公告)号：US06558121B2

    公开(公告)日：2003-05-06

    申请号：US09942299

    申请日：2001-08-29

    申请人： Gaoqiu Zhu ,  Mark Douglas Gledhill ,  Douglas Bryan Ballantyne

    发明人： Gaoqiu Zhu ,  Mark Douglas Gledhill ,  Douglas Bryan Ballantyne

    IPC分类号： F01D514

    CPC分类号： F01D5/143 ,  Y10T29/49336

    摘要： A turbine blade assembly for a gas turbine engine that includes a turbine platform including contoured edges. The turbine blade assembly includes a platform, a turbine airfoil extending radially outward from the platform, a shank that extends radially inward from the platform, and a dovetail extending from the shank. The platform includes a leading edge and a trailing edge separated by a pressure edge and an opposite suction edge, the pressure edge including a plurality of arcs extending between the leading edge and the trailing edge, the suction edge including a plurality of arcs extending between the leading and trailing edges.

    摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片组件，其包括具有轮廓边缘的涡轮平台。 涡轮叶片组件包括平台，从平台径向向外延伸的涡轮机翼型件，从该平台径向向内延伸的柄部以及从该柄部延伸的燕尾榫。 平台包括由压力边缘和相对的吸力边缘分开的前缘和后缘，压力边缘包括在前缘和后缘之间延伸的多个弧，吸力边缘包括在 前缘和后缘。

    HYBRID IMPINGEMENT COOLED AIRFOIL
    8.
    发明申请
    HYBRID IMPINGEMENT COOLED AIRFOIL 有权
    混合气体冷却空气

    公开(公告)号：US20090245999A1

    公开(公告)日：2009-10-01

    申请号：US12055101

    申请日：2008-03-25

    申请人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    发明人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

    摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.

    摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。