中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

19 records (took 0.03 seconds)

    Striated turbomachine blade
    3.
    发明公开
    Striated turbomachine blade 有权
    Turbomaschinenschaufel mit Riefen

    公开(公告)号：EP0924380A2

    公开(公告)日：1999-06-23

    申请号：EP98308625.7

    申请日：1998-10-21

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Panovsky, Josef ,  Stevenson, Joseph Timothy

    IPC: F01D5/16

    CPC classification number: F01D5/147 ,  F01D5/16 ,  F05D2240/80 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

    Abstract: A fan blade (10) includes a metal airfoil (14) having first and second opposite sides (16,18) extending longitudinally between a root (20) and a tip (22), and laterally between a leading edge (24) and a trailing edge (26). The airfoil further includes a plurality of fine striations (36) spaced laterally apart between the leading and trailing edges in the airfoil first side, and extending longitudinally between the root and the tip. A viscoelastic filler (38) is bonded in the striations for damping torsional vibrations of the airfoil.

    Abstract translation: 风扇叶片（10）包括金属翼型件（14），其具有在根部（20）和尖端（22）之间纵向延伸的第一和第二相对侧（16,18），并且横向在前缘（24）和 后缘（26）。 翼型件还包括在翼型件第一侧的前缘和后缘之间横向间隔开并且在根部和尖端之间纵向延伸的多个细条纹（36）。 粘弹性填料（38）粘合在用于阻尼翼型的扭转振动的条纹中。

    High modulus, impact resistant foams for structural components
    5.
    发明公开
    High modulus, impact resistant foams for structural components 审中-公开
    SchlagzäheSchaumstoffe mit hohemElastizitätsmodulfürBauteile

    公开(公告)号：EP1447208A2

    公开(公告)日：2004-08-18

    申请号：EP04250741.8

    申请日：2004-02-11

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Lin, Wendy Wen-Ling ,  Finn, Scott Roger ,  Flanagan, Kevin Warner ,  Stevenson, Joseph Timothy ,  Carnahan, James Claude

    IPC: B29C70/74 ,  B29D31/00 ,  B29C70/66 ,  B29L31/08

    CPC classification number: F01D5/147 ,  C08G18/10 ,  C08G2101/00 ,  C08J9/32 ,  C08J2203/22 ,  C08J2375/04 ,  F01D5/28 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T428/2985 ,  C08G18/3814

    Abstract: The present invention provides tough, high modulus, low density thermoset polyurethane compositions which are useful in general as, for example, cast structural materials and in a preferred embodiment can be cured directly onto an aircraft engine fan blade (10), thereby providing a lighter blade, without concomitant loss in structural integrity or blade performance due to, for example, resistance to foreign object impacts and fuel efficiency. In a preferred embodiment, the composition is comprised of bis-amine compounds reacted with isocyanate-functional polyether polymers in the presence of hollow polymeric microspheres. The thermoset polymer compositions are formed by casting into a mold which is formed by a cavity (12) within the metallic or composite fan blade or guide vane in the form of a pocket and a removable caul sheet (16). After the elastomeric polyurethane foam is injected through at least one injector port (18) into the mold, the foam is cured.

    Abstract translation: 本发明提供了韧性，高模量，低密度的热固性聚氨酯组合物，其通常可用于例如铸造结构材料，并且在优选实施方案中可直接固化到飞机发动机风扇叶片（10）上，从而提供更轻 叶片，由于例如抵抗异物冲击和燃料效率而没有结构完整性或叶片性能的同时损失。 在优选的实施方案中，组合物由在中空聚合物微球存在下与异氰酸酯官能的聚醚聚合物反应的双 - 胺化合物组成。 热固性聚合物组合物通过浇铸到由金属或复合风扇叶片或引导叶片内的空腔（12）形成的模具形成，其形式为口袋和可移除的污垢片（16）。 在通过至少一个注射器端口（18）将弹性体聚氨酯泡沫注入到模具中之后，泡沫体被固化。

    Fan disk configuration
    9.
    发明公开
    Fan disk configuration 有权
    疤痕磁盘配置用于风扇转子

    公开(公告)号：EP1209320A3

    公开(公告)日：2003-10-15

    申请号：EP01309912.2

    申请日：2001-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Bolt, Janine Elizabeth ,  Rhoda, James Edwin ,  Stevenson, Joseph Timothy

    IPC: F01D5/02 ,  F01D21/04 ,  F01D5/30

    CPC classification number: F01D5/326 ,  F01D5/06 ,  F01D11/008 ,  F01D21/045 ,  F05D2250/141 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine rotor disk (16) has a number of annular hubs (64) circumscribed about a centerline and each of the hubs is connected to a disk rim by a web (68). A plurality of circumferentially spaced apart dovetail slots are disposed through the rim (62), extending circumferentially between disk posts (50), extending axially from a forward end (65) to an aft end (67) of the rim, and extending radially inwardly from a disk outer surface (63) of the rim. Circumferentially extending annular burst slots (70) extend radially through the rim (62) into the dovetail slots between each adjacent pair (72) of the webs (68). In the exemplary embodiment of the invention illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang (69) is located radially outwardly on each of the disk posts (50) and a chamfer (39) is on a radially outer corner (45) of the each of the disk posts (50) on a portion of the overhangs (69). A plurality of post holes extending axially aftwardly into the rim (62) wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts (50).

    Fan disk configuration
    10.
    发明公开
    Fan disk configuration 有权
    NarbenscheibenkonfigurationfüreinenBläserrotor

    公开(公告)号：EP1209320A2

    公开(公告)日：2002-05-29

    申请号：EP01309912.2

    申请日：2001-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Forrester, James Michael ,  Bolt, Janine Elizabeth ,  Rhoda, James Edwin ,  Stevenson, Joseph Timothy

    IPC: F01D5/02 ,  F01D21/04

    CPC classification number: F01D5/326 ,  F01D5/06 ,  F01D11/008 ,  F01D21/045 ,  F05D2250/141 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine rotor disk (16) has a number of annular hubs (64) circumscribed about a centerline and each of the hubs is connected to a disk rim by a web (68). A plurality of circumferentially spaced apart dovetail slots are disposed through the rim (62), extending circumferentially between disk posts (50), extending axially from a forward end (65) to an aft end (67) of the rim, and extending radially inwardly from a disk outer surface (63) of the rim. Circumferentially extending annular burst slots (70) extend radially through the rim (62) into the dovetail slots between each adjacent pair (72) of the webs (68). In the exemplary embodiment of the invention illustrated herein, the dovetail slots are circular arc dovetail slots. An axially forwardly extending overhang (69) is located radially outwardly on each of the disk posts (50) and a chamfer (39) is on a radially outer corner (45) of the each of the disk posts (50) on a portion of the overhangs (69). A plurality of post holes extending axially aftwardly into the rim (62) wherein each of the post hole extends axially aftwardly into a corresponding one of the disk posts (50).

    Abstract translation: 燃气涡轮发动机转子盘（16）具有围绕中心线限定的多个环形轮毂（64），并且每个轮毂通过腹板（68）连接到盘形边缘。 多个沿周向间隔开的燕尾槽设置成穿过边缘（62），沿圆周方向延伸，在圆柱（50）之间沿轴向从边缘的前端（65）延伸到后端（67），并且径向向内延伸 从轮辋的盘外表面（63）。 圆周延伸的环形突出槽（70）径向延伸穿过边缘（62）进入腹板（68）的每个相邻对（72）之间的燕尾槽。 在本文所示的本发明的示例性实施例中，燕尾槽是圆弧燕尾槽。 轴向向前延伸的突出部分（69）位于每个盘柱（50）的径向外侧，倒角（39）位于每个盘柱（50）的径向外角（45）上， 悬垂（69）。 多个沿轴向向后延伸到边缘（62）中的柱孔，其中每个柱孔轴向向后延伸到相应的一个盘柱（50）中。

Patent Agency Ranking