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13 条记录 (耗时 0.023 秒)

    TRAILING EDGE MACHINING OF A WORKPIECE
    4.
    发明申请
    TRAILING EDGE MACHINING OF A WORKPIECE 有权
    工作的边缘加工

    公开(公告)号：US20100252533A1

    公开(公告)日：2010-10-07

    申请号：US12417714

    申请日：2009-04-03

    申请人： Carl W. Mercier ,  Daniel E. Quinn ,  David J. Hiskes ,  Paul M. Pellet ,  Michael L. Miller

    发明人： Carl W. Mercier ,  Daniel E. Quinn ,  David J. Hiskes ,  Paul M. Pellet ,  Michael L. Miller

    IPC分类号： B23H1/04 ,  B23H1/00

    CPC分类号： B23H9/10 ,  B23H11/003 ,  B23Q3/063 ,  B24B19/14 ,  B24B41/06

    摘要： A method of securing an workpiece for machining the trailing edge. The workpiece has a platform from which extends an airfoil, the airfoil including a leading edge and a trailing edge, and a pressure side and a suction side. A fixture with at least one locating datum that relates to the platform and at least one locating datum that relates to the leading edge is provided. The fixture does not contact the trailing edge of the workpiece. The workpiece is positioned so that the platform is against the related locating datum and the leading edge is against the related locating datum. The workpiece is secured within the fixture, and the trailing edge of the workpiece is machined.

    摘要翻译： 一种固定用于加工后缘的工件的方法。 工件具有一个平台，从该平台延伸翼型件，该翼型件包括前缘和后缘，以及压力侧和吸力侧。 提供具有至少一个与平台相关的定位基准的固定装置和至少一个与前缘相关的定位基准。 夹具不接触工件的后缘。 工件被定位成使得平台抵靠相关的定位基准，并且前缘抵靠相关的定位基准。 工件被固定在固定装置内，并且加工工件的后缘。

    Method for repairing a turbine vane
    6.
    发明授权
    Method for repairing a turbine vane 有权
    修理涡轮叶片的方法

    公开(公告)号：US06685431B2

    公开(公告)日：2004-02-03

    申请号：US10002419

    申请日：2001-10-24

    申请人： David J. Hiskes

    发明人： David J. Hiskes

    IPC分类号： F01D904

    CPC分类号： B23P6/005 ,  F01D5/005 ,  Y10T29/49318 ,  Y10T29/49323

    摘要： The present invention relates to a method for repairing a vane used in a gas turbine engine. The method broadly comprises the steps of providing a vane to be repaired, which vane has a first platform, a first buttress, a second platform, a second buttress, and an airfoil extending between the first and second platforms, removing the first platform, the first buttress, and the airfoil from the vane in their entirety and removing part of the second platform and the second buttress leaving a machined vane portion, providing a replacement detail having at least a replacement first platform, a replacement first buttress and a replacement airfoil, positioning the replacement detail relative to the machined vane portion, and forming a joint between the machined vane portion and the replacement detail.

    摘要翻译： 本发明涉及一种用于修理燃气涡轮发动机中使用的叶片的方法。 该方法广泛地包括提供待修理的叶片的步骤，该叶片具有第一平台，第一支撑件，第二平台，第二支撑件和在第一和第二平台之间延伸的翼型件，移除第一平台， 第一支撑件和来自叶片的翼型件整体移除，并且移除第二平台的一部分和离开加工叶片部分的第二支撑件，提供具有至少替换的第一平台，替换第一支撑件和替换翼型​​件的替换细节， 将替换细节相对于加工的叶片部分定位，以及在加工的叶片部分和替换细节之间形成接头。

    Split vane repair
    7.
    发明申请
    Split vane repair 有权
    拆分叶片修复

    公开(公告)号：US20080289179A1

    公开(公告)日：2008-11-27

    申请号：US11805136

    申请日：2007-05-22

    申请人： Paul M. Pellet ,  David J. Hiskes

    发明人： Paul M. Pellet ,  David J. Hiskes

    IPC分类号： B23P6/00

    CPC分类号： F01D5/005 ,  B23P6/002 ,  F01D9/044 ,  F01D25/285 ,  F05D2230/64 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49321 ,  Y10T29/49336 ,  Y10T29/49337

    摘要： A method of repairing a vane cluster for a gas turbine engine includes attaching a first registration block to a salvageable airfoil segment of the vane cluster, machining a face of the first registration block relative to datum surfaces of the vane cluster, removing a damaged airfoil segment from the vane cluster, adding new material to the salvageable airfoil segment, joining a replacement airfoil segment having a second registration block to the salvageable airfoil segment to replace the damaged airfoil segment, removing the first registration block, and removing the second registration block. The respective first and second registration blocks of the salvageable airfoil segment and the replacement airfoil segment are aligned in a configuration substantially identical to a configuration of the vane cluster prior to undergoing repair.

    摘要翻译： 一种维修燃气涡轮发动机的叶片簇的方法包括将第一对准块附接到叶片组的可抢救的翼型段，相对于叶片簇的基准面加工第一对准块的面，去除损坏的翼型段 从叶片组中将新材料添加到可救修的翼型段，将具有第二对准块的替换翼型段连接到可补救的翼型段，以替换损坏的翼型段，移除第一登记块，并且移除第二登记块。 可补救的翼型段和替换翼型​​段的相应的第一和第二对准块在进行修理之前与叶片簇的构造基本相同的构型对准。

    End cap for a rotor shaft of a rotary machine
    8.
    发明授权
    End cap for a rotor shaft of a rotary machine 失效
    旋转机械的转子轴端盖

    公开(公告)号：US4424004A

    公开(公告)日：1984-01-03

    申请号：US319861

    申请日：1981-11-09

    申请人： David J. Hiskes

    发明人： David J. Hiskes

    IPC分类号： F01D5/06 ,  F01D5/08 ,  F01D11/00

    CPC分类号： F01D5/06 ,  F01D11/00 ,  F01D5/08 ,  Y02T50/676

    摘要： A hollow rotor shaft 34 having a bore 36 sealed by an end cap 40 is disclosed. The end cap abuttingly engages a first side 42 and second side 44 on the shaft which extend radially inwardly into the bore of the shaft. The sides face in opposite directions and are oriented in a generally axial direction. The end cap includes at least one dog 48, a cover 46 pressed tightly against the first side by the rotatable dog and a lock means such as the bolt 50. The dogs are rotatable to a first position during insertion and rotatable to a second position during assembly by the lock means which extends through the cover to permit assembly and disassembly of the end cap from the exterior of the rotor shaft. In one embodiment a gasket 72 is trapped between the side of the shaft and the cover by the side of the shaft and the cover.

    摘要翻译： 公开了具有由端盖40密封的孔36的空心转子轴34。 端盖与轴上的第一侧42和第二侧44接合，径向向内延伸到轴的孔中。 这些侧面朝向相反方向并且在大致轴向方向上定向。 端盖包括至少一个狗48，通过可旋转的狗紧紧地压靠第一侧的盖46和诸如螺栓50的锁定装置。在插入期间，狗可以旋转到第一位置并且可旋转到第二位置 通过延伸穿过盖子的锁定装置组装，以允许端盖从转子轴的外部组装和拆卸。 在一个实施例中，垫圈72被轴和盖的侧面捕获在轴的侧面和盖之间。

    Method repair of turbine blade tip
    9.
    发明授权
    Method repair of turbine blade tip 有权
    涡轮叶片尖端的方法修复

    公开(公告)号：US08091228B2

    公开(公告)日：2012-01-10

    申请号：US11842181

    申请日：2007-08-21

    申请人： David J. Hiskes

    发明人： David J. Hiskes

    IPC分类号： B23P6/00

    CPC分类号： F01D5/005 ,  B23P6/005 ,  F01D5/20 ,  F05D2230/232 ,  F05D2230/234 ,  F05D2230/80 ,  Y10T29/49318

    摘要： A method of repair of a turbine blade involves inspecting a turbine blade having an internal cavity and a cap. The cap is removed and replaced with a replacement cap. The replacement cap has an opening. The opening provides access to the internal cavity of the internal blade so that the replacement cap may be attached to the turbine blade through the opening.

    摘要翻译： 涡轮叶片的修复方法包括检查具有内腔和盖的涡轮叶片。 盖子被取下，更换为更换盖子。 更换盖子有一个开口。 该开口提供进入内部叶片的内部空腔，使得替换盖可以通过开口附接到涡轮机叶片。