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    HYBRID BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME
    2.
    发明申请
    HYBRID BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME 有权
    混合式涡轮转子及其制造方法

    公开(公告)号：US20170022827A1

    公开(公告)日：2017-01-26

    申请号：US14806933

    申请日：2015-07-23

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： David R. Waldman ,  Don Mittendorf ,  Mark C. Morris ,  Michael Vinup

    IPC: F01D5/30 ,  B23K20/12 ,  B23K20/22 ,  B23K20/02 ,  B23K20/14 ,  B23K20/08 ,  B23K9/167 ,  B23K9/23 ,  B23K5/14 ,  B23K5/00 ,  B23K10/02 ,  B23K15/00 ,  B23K26/32 ,  B23K26/21 ,  F01D5/02

    CPC classification number: F01D5/3061 ,  B23K20/1205 ,  B23K20/16 ,  B23K2101/001 ,  F01D5/082 ,  F01D5/34 ,  F01D11/006 ,  F05D2230/239 ,  F05D2300/606 ,  F05D2300/607 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery; providing a plurality of turbine blades, each of which comprising an airfoil portion and a shank portion, the shank portion having a base surface; metallurgically bonding a compliant alloy material layer to either or both of the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks; and linear friction welding the plurality of blades to the turbine disk so as to form a bond plane between the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks, the compliant alloy material layer being disposed at the bond plane.

    Abstract translation: 提供混合式涡轮转子及其制造方法。 一种混合式混合涡轮机转子的制造方法，包括以下步骤：提供涡轮盘，该涡轮盘具有边缘部分，该边缘部分包括周向连续材料的活边缘和在涡轮盘的外周中的多个带状轮缘切口， 限定外周的附接表面; 提供多个涡轮叶片，每个涡轮叶片包括翼型部分和柄部分，所述柄部分具有基部表面; 将柔性合金材料层冶金结合到涡轮盘的凸起刀片附件表面中的一个或两个以及刀片柄的基座表面; 并且将所述多个叶片线性摩擦焊接到所述涡轮盘，以便在所述涡轮盘的所述凸起的叶片附接表面与所述叶片柄的基底表面之间形成接合平面，所述柔性合金材料层设置在所述接合平面处。

    Turbine engines with ceramic vanes and methods for manufacturing the same
    3.
    发明授权
    Turbine engines with ceramic vanes and methods for manufacturing the same 有权

    公开(公告)号：US10605086B2

    公开(公告)日：2020-03-31

    申请号：US13681675

    申请日：2012-11-20

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： George E. Zurmehly ,  Milton Ortiz ,  Kin Poon ,  Michael Vinup ,  Ardeshir Riahi

    IPC: F01D5/12 ,  F01D5/14 ,  F01D5/28

    Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.

    TURBINE ENGINES WITH CERAMIC VANES AND METHODS FOR MANUFACTURING THE SAME
    5.
    发明申请
    TURBINE ENGINES WITH CERAMIC VANES AND METHODS FOR MANUFACTURING THE SAME 审中-公开
    具有陶瓷风扇的涡轮发动机及其制造方法

    公开(公告)号：US20140161623A1

    公开(公告)日：2014-06-12

    申请号：US13681675

    申请日：2012-11-20

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： George E. Zurmehly ,  Milton Ortiz ,  Kin Poon ,  Michael Vinup ,  Ardeshir Riahi

    IPC: F01D5/12

    CPC classification number: F01D5/12 ,  F01D5/147 ,  F01D5/284 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49316

    Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.

    Abstract translation: 叶片组件包括构造成接受其间的压缩气体流动的第一和第二环形金属环。 第一和第二环形圈各自包括切口部分。 该组件还包括一个陶瓷基体复合叶片，其被构造成具有钝的圆形鼻部和扁平和渐缩的尾部的翼型件。 叶片的第一径向端刚性地设置在第一环形环上，并且叶片的第二径向端部可滑动地设置在第二环形环的切口部分内，使得叶片被第一和第二环形圈包围。 叶片包括径向延伸穿过的中空的通孔部分。 此外，组件包括设置在叶片的中空部分内并穿过叶片的中空部分并穿过第一环形圈的切口部分的金属细长构件。

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