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    FATIGUE RESISTANT TURBINE THROUGH BOLT
    3.
    发明申请
    FATIGUE RESISTANT TURBINE THROUGH BOLT 审中-公开
    通过螺栓的耐疲劳涡轮

    公开(公告)号：US20150107072A1

    公开(公告)日：2015-04-23

    申请号：US14059528

    申请日：2013-10-22

    申请人： Kazim Ozbaysal ,  Zafir A. M. Abdo ,  Kenneth K. Starr ,  Sachin R. Shinde

    发明人： Kazim Ozbaysal ,  Zafir A. M. Abdo ,  Kenneth K. Starr ,  Sachin R. Shinde

    IPC分类号： F16B33/06 ,  B23P9/02

    CPC分类号： F16B33/06 ,  B23P9/02 ,  C21D6/004 ,  C21D6/005 ,  C21D6/007 ,  C21D6/02 ,  C21D7/08 ,  C21D9/0093 ,  C22C19/055 ,  C22C19/056 ,  F01D5/066 ,  Y10T29/47

    摘要： A fatigue resistant turbine through bolt formed from a base material covered by a first surface modification and a second surface modification is disclosed. The first surface modification may be in contact with the base material and, in at least one embodiment, may be a low plasticity burnished layer that increases the residual compressive stresses on an outer surface of the turbine through bolt. The second surface modification may cover the first surface modification and, in at least one embodiment, may be a spinel oxide layer on the low plasticity burnished layer. The second surface modification may be positioned on the first surface modification or on the bare turbine through bolt contact surface without low plastiocity burnishing on the shaft of the turbine through bolt. The first and second surface modifications reduce the likelihood of fretting fatigue failures.

    摘要翻译： 公开了一种由基材覆盖的第一表面改性和第二表面改性形成的耐疲劳涡轮机通过螺栓。 第一表面改性可以与基材接触，并且在至少一个实施方案中可以是低塑性抛光层，其通过螺栓增加涡轮机的外表面上的残余压应力。 第二表面改性可以覆盖第一表面改性，并且在至少一个实施方案中可以是低塑性抛光层上的尖晶石氧化物层。 第二表面改性可以通过螺栓接触表面定位在第一表面改性或裸露的涡轮机上，而不会通过螺栓在涡轮轴上的低塑性抛光。 第一和第二表面修改减少了疲劳疲劳失效的可能性。

    USE OF ELEVATED PRESSURES FOR REDUCING CRACKS IN SUPERALLOY WELDING AND CLADDING
    4.
    发明申请
    USE OF ELEVATED PRESSURES FOR REDUCING CRACKS IN SUPERALLOY WELDING AND CLADDING 审中-公开
    用于减少超级焊接和封盖中的裂纹的高压

    公开(公告)号：US20140209576A1

    公开(公告)日：2014-07-31

    申请号：US13754967

    申请日：2013-01-31

    申请人： Kazim Ozbaysal ,  Zafir A. M. Abdo

    发明人： Kazim Ozbaysal ,  Zafir A. M. Abdo

    IPC分类号： B23K26/34

    CPC分类号： B23K26/32 ,  B23K26/127 ,  B23K26/342 ,  B23K2101/001 ,  B23K2103/26 ,  C23C24/106 ,  F01D5/286 ,  F01D5/288 ,  F05D2230/31

    摘要： A superalloy component, such as gas turbine blade or vane, is structurally welded by placing the component in an isolation chamber. Inert gas is introduced into the chamber. The substrate is welded in the chamber, creating a weld zone. Pressure is applied directly on the weld zone that is greater than atmospheric pressure. Application of such pressure increases the weld zone ductility and reduces likelihood of solidification cracking and strain age cracking, compared to weld zones formed at atmospheric pressure. In some embodiments an isostatic pressure chamber is used to apply isostatic pressure on the weld zone. In other embodiments the welding is performed by laser welding or cladding, TIG welding electron beam welding or autogenous welding.

    摘要翻译： 通过将组件放置在隔离室中，结构性地焊接超级合金部件，例如燃气轮机叶片或叶片。 惰性气体被引入腔室。 将衬底焊接在腔室中，形成焊接区域。 压力直接施加在大于大气压力的焊接区上。 与大气压力下形成的焊接区相比，这种压力的应用增加了焊接区延展性，并降低了凝固裂缝和应变时效开裂的可能性。 在一些实施例中，等静压压力室用于对焊接区施加等静压。 在其它实施例中，焊接通过激光焊接或包层，TIG焊接电子束焊接或自发焊接来进行。

    Repair of superalloy component
    5.
    发明授权
    Repair of superalloy component 有权
    超合金部件修补

    公开(公告)号：US08640942B1

    公开(公告)日：2014-02-04

    申请号：US13799922

    申请日：2013-03-13

    申请人： Kazim Ozbaysal ,  Ahmed Kamel ,  Dhafer Jouini

    发明人： Kazim Ozbaysal ,  Ahmed Kamel ,  Dhafer Jouini

    IPC分类号： B23K31/02 ,  B23P6/04

    CPC分类号： B23K31/02 ,  B23K1/0018 ,  B23K1/20 ,  B23K1/206 ,  B23K26/3584 ,  B23K26/361 ,  B23K35/3033 ,  B23K35/304 ,  B23K2101/001 ,  B23P6/005 ,  C22C19/056 ,  F01D5/005 ,  F05D2230/237 ,  F05D2260/36 ,  Y10T29/49318

    摘要： A method of repairing a superalloy component (22) wherein a section (24) of the component containing a plurality of service-induced cracks (18, 20) is removed, then a replacement section (26) of superalloy material is installed with a structural braze joint (28) containing no boron or silicon. The replacement section may have a textured surface ((38) to enhance bonding with an overlying thermal barrier coating (42). The replacement section may be pre-formed to standardized dimensions in expectation of a typical service-induced crack pattern, and the removed section excavated accordingly. The interface between the replacement section and the component may be shaped to provide a mechanical interlock there between.

    摘要翻译： 一种修复超合金部件（22）的方法，其中除去包含多个工作引起的裂纹（18,20）的部件的部分（24），然后将超合金材料的更换部分（26）安装成具有结构 不含硼或硅的钎焊接头（28）。 替换部分可以具有纹理表面（38）以增强与上覆热障涂层（42）的粘合。替换部分可以预期形成为期望典型的服务引起的裂纹图案的标准化尺寸，并且被移除 相应的部分挖掘，更换部分和部件之间的接口可以成形为在其间提供机械互锁。

    Ni—Ti—CR near ternary eutectic alloy for gas turbine component repair
    6.
    发明授权
    Ni—Ti—CR near ternary eutectic alloy for gas turbine component repair 有权
    用于燃气轮机部件修复的三元共晶合金附近的Ni-Ti-CR

    公开(公告)号：US09573228B2

    公开(公告)日：2017-02-21

    申请号：US13495223

    申请日：2012-06-13

    申请人： Kazim Ozbaysal

    发明人： Kazim Ozbaysal

    IPC分类号： B23K35/30 ,  B23K1/00 ,  C22C19/05 ,  F01D5/00

    CPC分类号： B23K1/0018 ,  B23K1/206 ,  B23K35/3033 ,  B23K35/304 ,  B23K2101/001 ,  C22C19/055 ,  C22C19/056 ,  C22F1/10 ,  F01D5/005 ,  F01D5/12 ,  F01D9/02 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/80 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/701

    摘要： A ternary near eutectic alloy of Ni, Ti, Cr is described having a relatively low melting temperature of approximately 1230 deg. C. or less, suitable for fusing cracks in turbine blades and vanes without substantial risk of cracking during the repair process. Such an alloy is suitable for low temperature joining or repair of turbine blades since it contains the same components as typical turbine blades and vanes without foreign elements to lower the melting point of the repaired material or adversely affect the mechanical properties of the repaired component. Exclusion of boron eliminates the formation of brittle boron compounds, detrimental to the properties of the repair or seam.

    摘要翻译： 描述了具有约1230度的较低熔融温度的Ni，Ti，Cr的三元附近共晶合金。 C.或更小，适用于在涡轮机叶片和叶片中熔化裂纹，而在修复过程中不会有明显的开裂风险。 这种合金适用于涡轮叶片的低温接合或修理，因为它包含与典型的涡轮机叶片和叶片相同的组件，没有异物以降低修理材料的熔点或不利地影响修理的部件的机械性能。 排除硼消除了脆性硼化合物的形成，对修复或接缝的性能有害。

    BRAZED ARTICLES, BRAZE ASSEMBLIES AND METHODS THEREFOR UTILIZING GOLD/COPPER/NICKEL BRAZING ALLOYS
    7.
    发明申请
    BRAZED ARTICLES, BRAZE ASSEMBLIES AND METHODS THEREFOR UTILIZING GOLD/COPPER/NICKEL BRAZING ALLOYS 有权
    BRAZED ARTICLES，BRAZE ASSEMBLIES及其使用金/铜/镍合金合金的方法

    公开(公告)号：US20090305079A1

    公开(公告)日：2009-12-10

    申请号：US11930858

    申请日：2007-10-31

    申请人： Kazim Ozbaysal ,  David Edwin Budinger

    发明人： Kazim Ozbaysal ,  David Edwin Budinger

    IPC分类号： B32B15/01 ,  B23K31/02 ,  B23K1/20 ,  B23K1/002

    CPC分类号： B22F7/064 ,  B22F5/009 ,  B22F7/08 ,  B23K35/3013 ,  B32B15/01 ,  B32B15/016 ,  C22C1/0425 ,  C22C1/0466 ,  C22C5/02 ,  C22C9/00 ,  C22C14/00 ,  Y10T428/12 ,  Y10T428/12806

    摘要： A brazing assembly includes a tungsten/carbide/cobalt substrate (e.g., wear pad), a second substrate including titanium or titanium alloy (e.g., a midspan shroud of a fan or compressor blade) and a brazing material including gold, nickel, and copper present in respective amounts to improve the ductility of the braze joint. A brazed article includes a first substrate, a second substrate, and a braze joint having a post-braze hardness of between 450 and 600 KHN. A method to improve the impact resistance of a braze joint between a tungsten/carbide/cobalt substrate and a substrate including titanium or alloy thereof includes utilizing a brazing material including gold, nickel, and copper and brazing at temperatures less than about 1900° F. (1038° C.).

    摘要翻译： 钎焊组件包括钨/碳化物/钴基底（例如耐磨垫），包括钛或钛合金（例如，风扇或压缩机叶片的中跨护罩）的第二基底和包括金，镍和铜的钎焊材料 以各自的量存在以改善钎焊接头的延展性。 钎焊制品包括第一基板，第二基板和钎焊硬度在450和600KHN之间的钎焊接头。 提高钨/碳化物/钴基底和包括钛或其合金的基体之间的钎焊接头的耐冲击性的方法包括利用包括金，镍和铜的钎焊材料并在低于约1900°F的温度下进行钎焊。 （1038℃）。

    Isothermal structural repair of superalloy components including turbine blades
    9.
    发明授权
    Isothermal structural repair of superalloy components including turbine blades 有权
    超级合金部件的等温结构修复包括涡轮叶片

    公开(公告)号：US09174314B2

    公开(公告)日：2015-11-03

    申请号：US13414751

    申请日：2012-03-08

    申请人： Kazim Ozbaysal

    发明人： Kazim Ozbaysal

    IPC分类号： F01D5/14 ,  B23P6/04 ,  B22D19/10 ,  B23K35/30 ,  B23P6/00 ,  F01D5/00

    CPC分类号： B23P6/045 ,  B22D19/10 ,  B23K35/3033 ,  B23K2101/001 ,  B23P6/007 ,  F01D5/005 ,  F05D2230/80 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T428/12639

    摘要： Structural repair of cracks and other defects in superalloy components, such as steam or gas turbine blades in stationary or aero gas turbines, are performed by heating the blade substrate to an isothermal hold temperature below the substrate's incipient melting point and filling the crack with molten superalloy filler material. The molten filler solidifies into a casting and bonds with the component substrate at the isothermal hold temperature. Heat treatment processes are completed, so that the former crack is filled with cast superalloy material having identical or similar structural properties as the adjoining substrate superalloy material. The casting repair method may be utilized universally for all types of superalloy component defects, including those previously repaired by cosmetic, lower strength welding or brazing methods.

    摘要翻译： 通过将叶片基板加热到低于基板初始熔点的等温保持温度并用熔融超合金填充裂纹来进行超级合金部件（例如固定或航空燃气轮机中的蒸汽或燃气涡轮叶片）中的裂缝和其他缺陷的结构修复 填充材料。 熔融填料固化成铸件并在等温保持温度下与组分衬底结合。 完成热处理工艺，使得前者的裂纹填充有与相邻的基底超耐热合金材料具有相同或相似结构特性的铸造超耐热合金材料。 铸造修复方法可以普遍用于所有类型的超合金部件缺陷，包括以前通过化妆品，低强度焊接或钎焊方法修复的缺陷。