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    Turbine airfoil components containing ceramic-based materials and processes therefor
    6.
    发明公开
    Turbine airfoil components containing ceramic-based materials and processes therefor 审中-公开
    包含陶瓷基材料的涡轮机叶片部件及其工艺

    公开(公告)号：EP2469045A3

    公开(公告)日：2018-01-17

    申请号：EP11193396.6

    申请日：2011-12-14

    申请人： General Electric Company

    发明人： Darkins jr., Toby George ,  Heyward, John Peter ,  Estill, Eric Alan ,  Jamison, Joshua Brian ,  Deines, James Herbert ,  Marusko, Mark Willard ,  Hawkins, James Thomas

    IPC分类号： F01D25/28 ,  F01D5/30 ,  F01D9/04 ,  F01D5/14 ,  F01D5/28

    CPC分类号： F01D5/284 ,  F01D5/147 ,  F01D5/3084 ,  F05D2300/6033 ,  Y02T50/672

    摘要： Hybrid turbine airfoil components (30,100) containing a ceramic material, in which detailed features of the components (30,100) are formed of materials other than ceramic materials. The components (30,100) include a first component (44,102) formed of a ceramic-based material and a second component (46,104) formed of a metallic material. The first component (44,102) comprises an airfoil portion (38,102) and a nub (48,106), and the second component (46,104) is separately formed and attached to the first component (44,102) by casting the metallic material around the nub (48,106) of the first component (44,102). The second component (46,104) includes a platform portion (36,104) between the airfoil portion (38,102) and the nub (48,106) of the first component (44,102) and a dovetail portion (32,106) on the nub (48,106) of the first component (44,102). Each of the platform and dovetail portions (36,104;32,106) has at least one off-axis geometric feature (34,36,42,104) that results in the second component (46,104) having a more complex geometry than the first component (44,102).

    摘要翻译： 包含陶瓷材料的混合涡轮机叶片部件（30,100），其中部件（30,100）的详细特征由陶瓷材料以外的材料形成。 部件（30,100）包括由陶瓷基材料形成的第一部件（44,102）和由金属材料形成的第二部件（46,104）。 第一部件（44,102）包括翼型部分（38,102）和凸块（48,106），并且第二部件（46,104）分别形成并且通​​过围绕凸起（48,106）铸造金属材料而附接到第一部件（44,102） 的第一部件（44,102）。 第二部件（46,104）包括位于第一部件（44,102）的翼型部分（38,102）和凸起（48,106）之间的平台部分（36,104）以及第一部件（44,102）的凸起（48,106）上的燕尾部分（32,106） （44102）。 每个平台和燕尾部分（36,104; 32,106）具有至少一个离轴几何特征（34,36,42,104），其导致第二部件（46,104）具有比第一部件（44,102）更复杂的几何形状。

    Cap for ceramic blade tip shroud
    7.
    发明公开
    Cap for ceramic blade tip shroud 审中-公开
    陶瓷刀片护罩盖

    公开(公告)号：EP2551459A3

    公开(公告)日：2017-07-26

    申请号：EP12178383.1

    申请日：2012-07-27

    申请人： General Electric Company

    发明人： Heyward, John Peter ,  Abbott, Michael George ,  Danowski, Michael Joseph ,  Kleinow, Chad Daniel ,  Mook, Joshua Tyler

    IPC分类号： F01D5/20 ,  F01D5/22 ,  F01D11/12

    CPC分类号： F01D5/225 ,  F01D5/28 ,  F01D11/08 ,  F01D11/127

    摘要： A ceramic shroud assembly (99) includes a tip shroud (88) having an outer platform (86) supporting at least one seal tooth (91), a shroud cap (96) less brittle than the outer platform (86) and including a shroud cap base (98) on the outer platform (86), and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces (152, 153) located at clockwise and counter-clockwise distal ends (124, 126) respectively of the base. A rotor (34) assembly may include a circumferential row (38) of turbine blades (70) made of a ceramic material and extending radially outwardly from a disk (73) of a turbine rotor (34). The turbine blades (70) include airfoils (72) having the airfoil tip shrouds (88) and the shroud caps (96) at blade tips (77). The clockwise and counter-clockwise contact surfaces (152, 153) of circumferentially adjacent ones (71) of the shroud caps (96) contact each other. The shroud (88) and the platform (86) may be made of a ceramic or ceramic matrix composite material and the shroud cap (96) may be made of a metallic material.

    摘要翻译： 陶瓷护罩组件（99）包括具有支撑至少一个密封齿（91）的外平台（86），比外平台（86）更脆弱并且包括护罩的护罩帽（96）的护罩（88） 在所述外部平台（86）上的盖帽基座（98），以及分别位于所述基座的顺时针和逆时针远端（124,126）处的顺时针和逆时针面对的顺时针和逆时针接触表面（152,153） 。 转子（34）组件可以包括由陶瓷材料制成并且从涡轮转子（34）的盘（73）径向向外延伸的涡轮叶片（70）的周向排（38）。 涡轮机叶片（70）包括在翼尖（77）处具有翼型件顶部护罩（88）和护罩帽（96）的翼型件（72）。 圆周相邻的罩盖（96）的顺时针和逆时针接触表面（152,153）彼此接触。 护罩（88）和平台（86）可以由陶瓷或陶瓷基质复合材料制成，护罩盖（96）可以由金属材料制成。

    V-shaped blade tip shroud and method of fabricating same
    8.
    发明公开
    V-shaped blade tip shroud and method of fabricating same 审中-公开
    V-förmigesSchaufelspitzendeckband unddiesbezüglichesHerstellungsverfahren

    公开(公告)号：EP1734227A1

    公开(公告)日：2006-12-20

    申请号：EP06252964.9

    申请日：2006-06-08

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Heyward, John Peter ,  Bobie, Francis ,  Beverley, Michael

    IPC分类号： F01D5/20 ,  F01D5/22 ,  F01D11/08

    CPC分类号： C22C14/00 ,  F01D5/225 ,  F05D2220/3215 ,  F05D2230/12 ,  F05D2230/21 ,  F05D2240/80 ,  F05D2250/19 ,  F05D2250/29 ,  F05D2250/70 ,  Y02T50/671

    摘要： A turbine blade and a method of fabricating the same. The method for fabricating a turbine blade includes casting at least one turbine blade that includes a blade tip shroud (112) and at least one seal tooth (114) coupled to the blade tip shroud, and removing at least a portion (116) of the turbine blade such that a radially outer surface (118) of the blade tip shroud has at least two substantially flat surfaces. Preferably, the blade tip shroud (112) has a substantially V-shaped cross-sectional profile (120).

    摘要翻译： 涡轮叶片及其制造方法。 用于制造涡轮叶片的方法包括铸造至少一个涡轮机叶片，其包括叶片梢罩（112）和耦合到叶片梢罩的至少一个密封齿（114），并且移除至少一个 涡轮叶片，使得叶片梢罩的径向外表面（118）具有至少两个基本平坦的表面。 优选地，叶片尖端护罩（112）具有基本上V形的横截面轮廓（120）。

    Blade for a gas turbine engine and method for manufacturing such blade
    9.
    发明公开
    Blade for a gas turbine engine and method for manufacturing such blade 审中-公开
    刀片用于制造这种叶片的燃气涡轮发动机和方法

    公开(公告)号：EP1365108A3

    公开(公告)日：2004-10-06

    申请号：EP03253238.4

    申请日：2003-05-23

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Heyward, John Peter ,  Norris, Timonthy Lane ,  Wustman, Roger Dale ,  Flecker, III, Carl Anthony ,  Heffron, Todd Stephen

    IPC分类号： F01D5/30 ,  F01D5/18 ,  F01D5/28 ,  F01D5/08

    CPC分类号： F01D5/081 ,  F01D5/087 ,  F01D5/147 ,  F01D5/187 ,  F05D2240/81

    摘要： A method enables a gas turbine engine blade (42) to be manufactured to include an airfoil, a platform (52), a shank (54), and a dovetail (56). The platform extends between the airfoil and the shank, the shank extends between the dovetail and the platform, and the dovetail includes at least one tang (84,86) for securing the blade within the engine. The method comprises defining a cooling cavity (102) in the blade that extends through the airfoil, the platform, the shank, and the dovetail, such that a portion of the cavity defined within the dovetail includes a root passage portion having a first width (D R ), and a transition portion (122) extending between the root passage and the portion (114) of the cavity defined within the shank, and wherein the portion of the cavity defined within the shank has a second width (D S ) that is larger than the root passage first width + portion of the inner surface of the cooling cavity (102) is coated with a layer of an oxidation resistant environmental coating.