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14 条记录 (耗时 0.011 秒)

    Composite blading member and method for making
    1.
    发明公开
    Composite blading member and method for making 有权
    Schaufel aus Verbundmaterial und Verfahren zur Herstellung

    公开(公告)号：EP1801354A2

    公开(公告)日：2007-06-27

    申请号：EP06126911.4

    申请日：2006-12-21

    申请人： General Electric Company

    发明人： Marusko, Mark Willard ,  Subramanian, Suresh

    IPC分类号： F01D5/28 ,  F01D5/30 ,  F01D9/02

    CPC分类号： F01D5/282 ,  F05D2230/23 ,  F05D2300/2261 ,  F05D2300/603 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： A composite blading member (10) includes an airfoil (12) and a base (20) of composite material layers (40) and a platform (38) of composite material layers (40) interfused with the airfoil (12) and base (20). The platform (38) comprises a platform shelf (42) and a plurality of spaced-apart platform supports (44,46) integral with the platform shelf (42) and interfused with surfaces (26,28) of the base. Such blading member (10) was made by providing a partially cured airfoil-base preform (36) and a platform perform (38), including an airfoil shaped opening (43) therethrough and preforms of the platform supports (44,46). The airfoil-base preform (36) was inserted through the airfoil shaped opening (43) whereby cooperating surfaces of the platform perform (38) and airfoil-based preform (36) were in juxtaposition. The performs (36,38) were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms (36,38) under conditions to substantially fully cure the structures.

    摘要翻译： 复合叶片构件（10）包括翼型件（12）和复合材料层（40）的基部（20）和与翼型件（12）和基座（20）接合的复合材料层（40）的平台（38） ）。 平台（38）包括平台架（42）和与平台架（42）成一体并与底座的表面（26,28）连接的多个间隔开的平台支撑件（44,46）。 通过提供部分固化的翼型坯预制件（36）和平台执行（38）制造这种叶片构件（10），其包括穿过其中的翼型开口（43）和平台支撑件（44,46）的预制件。 翼型坯预制件（36）插入通过翼型开口（43），由此平台的配合表面（38）和基于翼型的预型件（36）并置。 表演（36,38）被加热以部分地将他们一起治愈。 然后在与预成型件（36,38）的材料相容的粘合剂的基础上与基本完全固化结构的条件相接合。

    Turbine rotor blade assembly and method of assembling same
    2.
    发明公开
    Turbine rotor blade assembly and method of assembling same 审中-公开
    Turbinenrotorblattanordnung und Montageverfahrendafür

    公开(公告)号：EP2570600A2

    公开(公告)日：2013-03-20

    申请号：EP12182828.9

    申请日：2012-09-03

    申请人： General Electric Company

    发明人： Paige II, Anthony Reid ,  Verrilli, Michael James ,  Jamison, Joshua Brian ,  Noe, Mark Eugene ,  Izon, Paul ,  Marusko, Mark Willard

    IPC分类号： F01D5/26 ,  F01D5/28

    CPC分类号： F01D5/284 ,  F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  F01D11/08 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T29/49321

    摘要： A rotor blade assembly (100) for a rotor (30) of a gas turbine engine (10) having an axis of rotation (8) includes a shank portion (106) formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion (104) formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions (128) of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus (120). At least a portion of the damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus (120) extending toward a circumferentially adjacent rotor blade assembly (100).

    摘要翻译： 用于具有旋转轴线（8）的燃气涡轮发动机（10）的转子（30）的转子叶片组件（100）包括由陶瓷基体复合材料（CMC）材料形成的柄部分（106）。 转子叶片组件还包括由与柄部分基本相似的CMC材料形成的平台部分（104）。 平台部分联接到柄部分。 平台部分和柄部分配合以至少部分地限定转子叶片组件的两个相对侧部分（128）。 相对的侧部分相对于旋转轴线成角度地分离。 转子叶片组件还包括阻尼器保持装置（120）。 阻尼器保持装置的至少一部分联接到柄部。 阻尼器保持装置包括朝向周向相邻的转子叶片组件（100）延伸的至少一个倾斜的支架装置（120）。

    Composite blading member and method for making
    3.
    发明公开
    Composite blading member and method for making 有权
    叶片由复合材料制成并且制造方法的

    公开(公告)号：EP1801354A3

    公开(公告)日：2011-01-05

    申请号：EP06126911.4

    申请日：2006-12-21

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Marusko, Mark Willard ,  Subramanian, Suresh

    IPC分类号： F01D5/28 ,  F01D5/30 ,  F01D9/02

    CPC分类号： F01D5/282 ,  F05D2230/23 ,  F05D2300/2261 ,  F05D2300/603 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： A composite blading member (10) includes an airfoil (12) and a base (20) of composite material layers (40) and a platform (38) of composite material layers (40) interfused with the airfoil (12) and base (20). The platform (38) comprises a platform shelf (42) and a plurality of spaced-apart platform supports (44,46) integral with the platform shelf (42) and interfused with surfaces (26,28) of the base. Such blading member (10) was made by providing a partially cured airfoil-base preform (36) and a platform perform (38), including an airfoil shaped opening (43) therethrough and preforms of the platform supports (44,46). The airfoil-base preform (36) was inserted through the airfoil shaped opening (43) whereby cooperating surfaces of the platform perform (38) and airfoil-based preform (36) were in juxtaposition. The performs (36,38) were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms (36,38) under conditions to substantially fully cure the structures.

    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。

    Chordal mounting arrangement for low-ductility turbine shroud
    8.
    发明公开
    Chordal mounting arrangement for low-ductility turbine shroud 有权
    MontageanordnungfürTurbinendeckband mit geringer Dehnbarkeit

    公开(公告)号：EP2540994A1

    公开(公告)日：2013-01-02

    申请号：EP12174123.5

    申请日：2012-06-28

    申请人： General Electric Company

    发明人： Albers, Joseph Charles ,  Marusko, Mark Willard

    IPC分类号： F01D25/24 ,  F01D9/04

    CPC分类号： F01D25/246 ,  F05D2240/11 ,  F05D2250/75 ,  F05D2300/6033

    摘要： A shroud apparatus for a gas turbine engine includes: a shroud segment (18) comprising low-ductility material and having a cross-sectional shape defined by opposed forward (24) and aft (26) walls, and opposed inner (20) and outer (22) walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface (32), wherein the shroud segment (18) includes: a radially-inward facing chordal forward mounting surface (36); and a radially-inward facing chordal aft mounting surface (40); and an annular case (48) surrounding the shroud segment (18), the case including: a radially-outward facing chordal forward bearing surface (58) which engages the forward mounting surface (36); and a radially-outward facing chordal aft bearing surface (68) which engages the aft mounting surface (40) of the shroud segment.

    摘要翻译： 用于燃气涡轮发动机的护罩装置包括：护罩段（18），其包括低延展性材料并且具有由相对的前（24）和后（26）壁限定的横截面形状，以及相对的内（20）和外 （22）壁，所述壁在相对的第一和第二端面之间延伸，其中所述内壁限定弓形的内部流动路径表面（32），其中所述护罩区段（18）包括：径向向内的向前的向前安装表面（36） ）; 和径向向内的弦尾安装表面（40）; 以及围绕所述护罩段（18）的环形壳体（48），所述壳体包括：接合所述前安装表面（36）的径向向外的向前的向前支承表面（58）; 以及与所述护罩段的后部安装表面（40）接合的径向向外的向后的支承表面（68）。