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    COMPRESSOR AIRFOIL
    2.
    发明申请
    COMPRESSOR AIRFOIL 有权
    压缩机AIRFOIL

    公开(公告)号：US20090290987A1

    公开(公告)日：2009-11-26

    申请号：US12175822

    申请日：2008-07-18

    申请人： DAVID PARKER ,  J. PAGE STROHL ,  RICHARD RAMIREZ ,  ROBERT MOORE

    发明人： DAVID PARKER ,  J. PAGE STROHL ,  RICHARD RAMIREZ ,  ROBERT MOORE

    IPC分类号： F01D5/14

    CPC分类号： F01D5/141 ,  F05D2220/3216

    摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

    摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 压缩机部件，例如压缩机叶片，在翼型跨度的一部分上具有增加的厚度，以增加刚度。 此外，已经重新安装翼型件以在叶片根部/附接区域中引起压缩应力。 增加的刚度和复位翼型结合起来以改善压缩机部件的高循环疲劳能力。

    Compressor airfoil
    3.
    发明授权
    Compressor airfoil 有权
    压缩机翼型

    公开(公告)号：US08057188B2

    公开(公告)日：2011-11-15

    申请号：US12175822

    申请日：2008-07-18

    申请人： David Parker ,  J. Page Strohl ,  Richard Ramirez ,  Robert Moore

    发明人： David Parker ,  J. Page Strohl ,  Richard Ramirez ,  Robert Moore

    IPC分类号： B63H1/26 ,  B63H7/02 ,  B64C11/16 ,  B64C27/46 ,  F01D5/14 ,  F03B3/12 ,  F03B7/00 ,  F03D11/02 ,  F04D29/38

    CPC分类号： F01D5/141 ,  F05D2220/3216

    摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

    摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 诸如压缩机叶片的压缩机部件在翼型跨度的一部分上具有增加的厚度，以增加刚度。 此外，已经重新安装翼型件以在叶片根部/附接区域中引起压缩应力。 增加的刚度和复位翼型结合起来以改善压缩机部件的高循环疲劳能力。

    Hook ring segment for a compressor vane
    5.
    发明授权
    Hook ring segment for a compressor vane 有权
    用于压缩机叶片的钩环段

    公开(公告)号：US07618234B2

    公开(公告)日：2009-11-17

    申请号：US11674731

    申请日：2007-02-14

    申请人： James G. Brackett ,  Charles Ellis ,  Michael Davis McGhee ,  J. Page Strohl

    发明人： James G. Brackett ,  Charles Ellis ,  Michael Davis McGhee ,  J. Page Strohl

    IPC分类号： F01D9/04

    CPC分类号： F01D9/04 ,  F01D9/042 ,  F01D25/246 ,  F01D25/28 ,  Y10T29/49323

    摘要： Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.

    摘要翻译： 公开了一种用于燃气涡轮发动机中的压缩机定子叶片组件的实施例。 在本发明的一个实施例中，定子叶片组件设置有多个叶片，每个叶片具有附接件和通道，其被加工成附件的前壁和后壁。 向前钩环段被压入附件的前壁中的通道中，并且后钩环被压入附件的后壁中的通道中。 钩环段将多个叶片连接在一起，以便提供压缩机壳体中的安装槽的均匀接合。 这种布置增加了钩环和压缩机壳体之间的接触面积，使得各个叶片振动的阻尼得到改善，并且降低了操作应力。

    BLADE DISK SEAL
    6.
    发明申请
    BLADE DISK SEAL 审中-公开
    刀片密封

    公开(公告)号：US20090148298A1

    公开(公告)日：2009-06-11

    申请号：US12330755

    申请日：2008-12-09

    申请人： J. Page Strohl ,  Anthony Petett ,  Robert J. Kraft

    发明人： J. Page Strohl ,  Anthony Petett ,  Robert J. Kraft

    IPC分类号： F01D5/30

    CPC分类号： F01D5/3007 ,  F01D11/006 ,  F05D2260/94

    摘要： An apparatus and method are disclosed for reducing the operating stresses in a disk of a gas turbine engine while providing a seal plate to minimize leakage of a cooling fluid from the blades positioned in the disk. The seal plate is fastened to a tang of one or more of the blades. The seal plate configuration can be utilized with a newly manufactured disk and blades or with a modification to an existing disk and blades. The disk, blade, and seal plate configuration reduce operating stresses in the disk that are caused by mechanical loading on the disk by one or more rotating blades.

    摘要翻译： 公开了一种用于降低燃气涡轮发动机的盘中的操作应力同时提供密封板以最小化冷却流体从位于盘中的叶片的泄漏的装置和方法。 密封板固定在一个或多个刀片的柄脚上。 密封板配置可以与新制造的盘和刀片一起使用，或者对现有的盘和刀片进行修改。 盘，刀片和密封板构造减少了由一个或多个旋转刀片在盘上的机械加载引起的盘中的操作应力。

    Turbine Static Structure for Reduced Leakage Air
    7.
    发明申请
    Turbine Static Structure for Reduced Leakage Air 有权
    用于减少泄漏空气的涡轮静态结构

    公开(公告)号：US20080148737A1

    公开(公告)日：2008-06-26

    申请号：US11614329

    申请日：2006-12-21

    申请人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

    发明人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

    IPC分类号： F02C7/20 ,  F01D11/00

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/57

    摘要： A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

    摘要翻译： 公开了具有减少的泄漏空气的涡轮机静态结构。 公开了一种具有很少段的静态结构的涡轮机支撑环，其中段具有改善的热膨胀能力，并且减少了空气泄漏。 多个径向延伸的槽被放置在段中以降低刚度。 为了最小化通过支撑环的空气泄漏，大体上圆周槽被放置在环中并与大致径向延伸的狭槽连接。 位于每个大致径向延伸的狭槽和大致圆周的狭槽中并且彼此接触的是两个金属板。 板被固定到支撑环结构上，以便提供密封构件，而补偿热生长。

    Turbine static structure for reduced leakage air
    8.
    发明授权
    Turbine static structure for reduced leakage air 有权
    涡轮静态结构，减少泄漏空气

    公开(公告)号：US07958735B2

    公开(公告)日：2011-06-14

    申请号：US11614329

    申请日：2006-12-21

    申请人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

    发明人： Charlie Ellis ,  J. Page Strohl ,  Matt Thomas

    IPC分类号： F01D9/04

    CPC分类号： F01D25/246 ,  F01D11/08 ,  F05D2240/11 ,  F05D2240/57

    摘要： A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

    摘要翻译： 公开了具有减少的泄漏空气的涡轮机静态结构。 公开了一种具有很少段的静态结构的涡轮机支撑环，其中段具有改善的热膨胀能力，并且减少了空气泄漏。 多个径向延伸的槽被放置在段中以降低刚度。 为了最小化通过支撑环的空气泄漏，大体上圆周槽被放置在环中并与大致径向延伸的狭槽连接。 位于每个大致径向延伸的狭槽和大致圆周的狭槽中并且彼此接触的是两个金属板。 板被固定到支撑环结构上，以便提供密封构件，而补偿热生长。

    Vane platform rail configuration for reduced airfoil stress
    9.
    发明授权
    Vane platform rail configuration for reduced airfoil stress 有权
    叶片平台导轨配置减少翼型应力

    公开(公告)号：US07293957B2

    公开(公告)日：2007-11-13

    申请号：US11692505

    申请日：2007-03-28

    申请人： Charlie Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

    发明人： Charlie Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

    IPC分类号： F01D9/04

    CPC分类号： F01D9/041 ,  F01D11/005 ,  F05D2260/941

    摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.

    摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着最内侧叶片组装轨道放置开口来实现的，该开口减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。

    Vane platform rail configuration for reduced airfoil stress
    10.
    发明申请
    Vane platform rail configuration for reduced airfoil stress 有权
    叶片平台导轨配置减少翼型应力

    公开(公告)号：US20060013685A1

    公开(公告)日：2006-01-19

    申请号：US10891400

    申请日：2004-07-14

    申请人： Charles Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

    发明人： Charles Ellis ,  David Parker ,  J. Page Strohl ,  David Medrano

    IPC分类号： F01D1/02

    CPC分类号： F01D9/041 ,  F05D2260/941

    摘要： A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.

    摘要翻译： 公开了一种用于燃气涡轮发动机的叶片组件，其具有较低的热致应力，导致改进的部件耐久性。 叶片组件翼型中的应力通过增加叶片平台的柔性并降低其对热偏转的抵抗力而降低。 这是通过沿着叶片组装轨道放置开口来实现的，其减小了平台的有效刚度，从而降低了叶片组件的翼型件中的操作应力。 然后将可拆卸密封件放置在开口中，以防止不期望的泄漏，同时保持增加的平台灵活性的益处。