利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

27 条记录 (耗时 0.042 秒)

    Dual-alloy disk system
    2.
    发明授权
    Dual-alloy disk system 失效
    双合金盘系统

    公开(公告)号：US5106012A

    公开(公告)日：1992-04-21

    申请号：US225907

    申请日：1988-07-29

    申请人： John M. Hyzak ,  Timothy E. Howson ,  Wilford H. Couts, Jr. ,  Steven H. Reichman ,  Hugo E. Delgado ,  Daniel D. Kruger ,  Michael E. Sauby ,  Sulekh C. Jain ,  Bruce P. Bardes ,  Richard G. Menzies ,  Swami Ganesh

    发明人： John M. Hyzak ,  Timothy E. Howson ,  Wilford H. Couts, Jr. ,  Steven H. Reichman ,  Hugo E. Delgado ,  Daniel D. Kruger ,  Michael E. Sauby ,  Sulekh C. Jain ,  Bruce P. Bardes ,  Richard G. Menzies ,  Swami Ganesh

    IPC分类号： B21J5/00 ,  B21K1/32 ,  F01D5/02

    CPC分类号： B21K1/32 ,  B21J5/00 ,  F01D5/02 ,  Y10S72/70 ,  Y10T29/49316 ,  Y10T29/4932

    摘要： Two pieces of metal are bonded together at a surface by placing the two pieces into contact at the surface and forging the two pieces in a die which causes substantial displacement of the metal originally at the surface in a direction parallel to and outwardly from the edges of the surface. In this way, many of the defects which are potentially present at the original surface are displaced with moving metal away from the original contact between the two pieces of metal into sacrificial ribs and the remaining defects are exposed to significant strain. A portion of the displaced metal which contains many of the defects and which forms the sacrificial ribs is removed from the resulting bonded work piece as the sacrificial ribs are removed from the work piece. The result is a bond with superior properties and with a bond surface which can be located very precisely. This system is particularly appropriate for forming dual-alloy high-pressure turbine disks for gas turbines in which an annular peripheral ring of a second super-alloy is bonded to a central core of a first super-alloy. The system is particularly effective if, prior to forging, surfaces to be bonded are closely shape-conforming, are very clean, and are diffusion-bonded using hot isostatic pressing while the surfaces are gas-free. The sacrificial ribs are formed by vents in the impression of the forging dies. The vents are adjacent to the outer edges of the bond surface. The system may be accomplished by using one or more strikes of the same dies, or may include multiple strikes in which only one side of the bond is vented during each strike.

    摘要翻译： 两块金属在表面上通过将两个部件在表面上接触并且将两个部件锻造在模具中而在一个表面上结合在一起，该模具使原来在表面处的金属在平行于和向外从 表面。 以这种方式，可能存在于原始表面的许多缺陷被移动的金属从两块金属之间的原始接触件移开到牺牲肋中，并且剩余的缺陷暴露于显着的应变。 当牺牲肋从工件上移除时，包含许多缺陷并形成牺牲肋的位移金属的一部分从所得到的粘合工件中被去除。 结果是具有优异性能和可以非常精确地定位的粘结表面的粘结。 该系统特别适用于形成用于燃气轮机的双合金高压涡轮盘，其中第二超合金的环形外围环结合到第一超级合金的中心芯。 如果在锻造之前，要结合的表面紧密形状，非常干净，并且在表面无气体时使用热等静压进行扩散粘合，该系统是特别有效的。 牺牲肋由锻造模具的印模形成。 通风口与接合表面的外边缘相邻。 该系统可以通过使用相同模具的一个或多个冲击来实现，或者可以包括多次冲击，其中在每次冲击期间仅释放粘结件的一侧。

    PEENING PROCESS FOR ENHANCING SURFACE FINISH OF A COMPONENT
    4.
    发明申请
    PEENING PROCESS FOR ENHANCING SURFACE FINISH OF A COMPONENT 有权
    用于增强部件表面处理的珩磨工艺

    公开(公告)号：US20110192205A1

    公开(公告)日：2011-08-11

    申请号：US12702534

    申请日：2010-02-09

    申请人： Swami Ganesh

    发明人： Swami Ganesh

    IPC分类号： C21D7/06

    CPC分类号： B24C1/10 ,  B24C7/0007 ,  C21D7/06 ,  Y10T29/479

    摘要： A process for treating a surface of a component to improve its surface finish and induce residual compresses stresses in a near-surface region of the component. The process entails performing a first peening operation to form residual compressive stress layers in the near-surface region of the component, and then performing at least a second peening operation to cause surface smoothing of the surface of the component while retaining residual compressive stresses in the near-surface region of the component. The first peening operation comprises wet glass bead peening at a first intensity with a first glass bead media, and the second peening operation comprises wet glass bead peening at a second intensity with a second glass bead media, wherein the second intensity is lower than the first intensity and the second glass bead media is smaller than the first glass bead media.

    摘要翻译： 用于处理部件的表面以改善其表面光洁度并在部件的近表面区域中引起残余压缩应力的方法。 该过程需要执行第一喷丸操作以在部件的近表面区域中形成残余的压应力层，然后进行至少一次第二喷丸操作以引起部件表面的表面平滑化，同时保留部件中的残余压应力 组件的近表面区域。 第一个喷丸操作包括以第一强度的湿玻璃珠喷丸处理与第一玻璃珠粒介质，并且第二喷丸操作包括用第二玻璃珠介质以第二强度的湿玻璃珠喷丸处理，其中第二强度低于第一强度 强度和第二玻璃珠介质小于第一玻璃珠介质。

    TURBINE ROTOR APPARATUS AND SYSTEM
    6.
    发明申请
    TURBINE ROTOR APPARATUS AND SYSTEM 审中-公开
    涡轮转子装置和系统

    公开(公告)号：US20090060735A1

    公开(公告)日：2009-03-05

    申请号：US11848645

    申请日：2007-08-31

    申请人： Swami Ganesh ,  Robin Carl Schwant ,  Lyle B. Spiegel

    发明人： Swami Ganesh ,  Robin Carl Schwant ,  Lyle B. Spiegel

    IPC分类号： F01D1/00 ,  F01D5/02 ,  F04D3/00

    CPC分类号： F01D5/063 ,  F05D2230/233 ,  F05D2230/235 ,  Y02T50/671

    摘要： A segmented turbine rotor is disclosed. The segmented turbine rotor has a plurality of rows of a plurality of turbine blades. At least one rotor segment of a plurality of rotor segments of the segmented turbine rotor includes a ring disposed circumferentially about and having an axis substantially parallel to a central axis of the rotor, the ring defining a cavity disposed at a center thereof and having an outer surface supporting at least one row of the plurality of rows of turbine blades.

    摘要翻译： 公开了一种分段涡轮转子。 分段涡轮转子具有多排多个涡轮叶片。 分段式涡轮机转子的多个转子段中的至少一个转子段包括围绕并且具有基本上平行于转子的中心轴线的轴线设置的环，该环限定了设置在其中心处的空腔， 表面支撑多排涡轮叶片的至少一排。

    Thermomechanical processing method for achieving coarse grains in a superalloy article
    7.
    发明授权
    Thermomechanical processing method for achieving coarse grains in a superalloy article 失效
    在超级合金制品中实现粗晶的热机械加工方法

    公开(公告)号：US5571345A

    公开(公告)日：1996-11-05

    申请号：US268696

    申请日：1994-06-30

    申请人： Swami Ganesh ,  Eric S. Huron

    发明人： Swami Ganesh ,  Eric S. Huron

    IPC分类号： B22F3/24 ,  C22F1/10

    CPC分类号： B22F3/24 ,  C22F1/10 ,  Y10S148/902

    摘要： A method is provided for obtaining a uniform grain size on the order of about ASTM 5 or coarser in at least a portion of an article formed from a .gamma.' precipitation strengthened nickel-base superalloy. The method comprises forming an article by: providing a billet, preheating the billet above 2000.degree. F. for at least 0.5 hours, working at least a portion to near-net shape at working conditions including a first strain rate of less than about 0.01 per second and at a subsolvus temperature at or near the recrystallization temperature, supersolvus heating to form a grain size in the portion of at least 5 ASTM, and cooling to reprecipitate .gamma.' within the article. The method can be utilized to form a .gamma.' precipitation strengthened nickel-base superalloy article whose grain size varies uniformly between portions thereof, so as to yield a desirable microstructure and property gradient in the article in accordance with the in-service temperature and stress-state gradient experienced by the article. The method is particularly useful for the making of relatively large components such as turbine disks used in gas turbine engines, which are subjected to stress and temperature conditions that vary radially from the center of the disk to its outer rim.

    摘要翻译： 提供了一种方法，用于在由γ'沉淀强化的镍基超级合金形成的制品的至少一部分中获得大约为ASTM 5或更粗的大小的均匀晶粒尺寸。 该方法包括通过以下步骤来形成物品：提供坯料，将坯料预热到2000°F以上至少0.5小时，在包括第一应变速率小于约0.01的工作条件下工作至少一部分至接近净形状 第二和在重结晶温度或接近重结晶温度的亚沉积温度下，加热至少5 ASTM部分中的晶粒尺寸，并冷却以在制品内再沉淀γ'。 该方法可用于形成晶粒尺寸在其各部分之间均匀变化的γ'沉淀强化镍基超合金制品，从而根据使用中的温度和应力 - 压力产生所需的微结构和性能梯度， 文章经历的状态渐变。 该方法特别适用于制造相对较大的部件，例如在燃气涡轮发动机中使用的涡轮盘，其经受从盘的中心到其外缘径向变化的应力和温度条件。

    Methods of forming blades and method for rendering a blade resistant to erosion
    8.
    发明授权
    Methods of forming blades and method for rendering a blade resistant to erosion 有权
    形成刀片的方法和使刀片耐腐蚀的方法

    公开(公告)号：US09291062B2

    公开(公告)日：2016-03-22

    申请号：US13607046

    申请日：2012-09-07

    申请人： Michael Lewis Jones ,  Swami Ganesh

    发明人： Michael Lewis Jones ,  Swami Ganesh

    IPC分类号： B05D3/12 ,  B23K31/02 ,  B05D1/36 ,  F01D5/28

    CPC分类号： F01D5/288 ,  B23K26/342 ,  B23K26/702 ,  B23K2101/001 ,  F01D5/286 ,  F05D2220/31

    摘要： Methods of forming a blade and rendering a blade resistant to erosion includes positioning a backing plate(s) or elongated backing plate(s) adjacent at least one side of a forward face of a leading edge surface of the blade. The methods include depositing an erosion resistant material in a plurality of layers by fusion bonding the erosion resistant material to the forward face of the leading edge surface of the blade. The backing plates providing a template or guide for depositing the plurality of layers of erosion resistant material. The plurality of layers of erosion resistant material form an erosion shield and a leading edge of the blade. Methods include removing the backing plate.

    摘要翻译： 形成叶片并且使得抗侵蚀的刀片的方法包括在叶片的前缘表面的前面的至少一侧附近定位背板或细长背板。 所述方法包括通过将抗侵蚀材料熔融粘合到叶片的前缘表面的前表面而将抗侵蚀材料沉积在多个层中。 背板提供用于沉积多层抗侵蚀材料的模板或引导件。 多层抗侵蚀材料形成侵蚀屏蔽和叶片的前缘。 方法包括移除背板。

    Multiple alloy turbine rotor section, welded turbine rotor incorporating the same and methods of their manufacture
    9.
    发明授权
    Multiple alloy turbine rotor section, welded turbine rotor incorporating the same and methods of their manufacture 有权
    多合金涡轮转子部分，包含其的焊接涡轮转子及其制造方法

    公开(公告)号：US08414267B2

    公开(公告)日：2013-04-09

    申请号：US12570566

    申请日：2009-09-30

    申请人： Swami Ganesh ,  Robin Carl Schwant

    发明人： Swami Ganesh ,  Robin Carl Schwant

    IPC分类号： F01D5/02

    CPC分类号： F01D5/063 ,  B21J5/002 ,  B21K1/28 ,  B22F5/009 ,  B22F7/062 ,  B23K35/0261 ,  B23K2101/001 ,  B23P15/006 ,  C22C19/00 ,  F01D5/28 ,  F05D2230/23 ,  F05D2230/25 ,  Y02E10/721 ,  Y10T29/49316 ,  Y10T29/4932

    摘要： A method of making a multiple alloy, multi-section welded turbine rotor includes providing a forged multiple alloy rotor section having an integral microstructure, the rotor section comprising a first alloy having a first alloy composition and second alloy having a second alloy composition, a first weld face comprising the first alloy on a first end and an a second weld face comprising the second alloy on an opposed second end. The method also includes providing a first rotor section comprising the first alloy composition and a second rotor section comprising the second alloy composition. The method also includes welding the first rotor section to the first weld face and welding the second rotor section to the second weld face.

    摘要翻译： 制造多合金，多段焊接涡轮转子的方法包括提供具有整体微结构的锻造多合金转子部分，所述转子部分包括具有第一合金组成的第一合金和具有第二合金组成的第二合金，第一合金 在第一端上包括第一合金的焊接面和在相对的第二端上包括第二合金的第二焊接面。 该方法还包括提供包括第一合金组合物的第一转子部分和包括第二合金组合物的第二转子部分。 该方法还包括将第一转子部分焊接到第一焊接面并将第二转子部分焊接到第二焊接面。

    TURBINE DISK PREFORM, WELDED TURBINE ROTOR MADE THEREWITH AND METHODS OF MAKING THE SAME
    10.
    发明申请
    TURBINE DISK PREFORM, WELDED TURBINE ROTOR MADE THEREWITH AND METHODS OF MAKING THE SAME 有权
    涡轮盘预制件，焊接式涡轮转子及其制造方法

    公开(公告)号：US20130004317A1

    公开(公告)日：2013-01-03

    申请号：US13172943

    申请日：2011-06-30

    申请人： Swami Ganesh ,  Steven Louis Breitenbach ,  Robin Carl Schwant

    发明人： Swami Ganesh ,  Steven Louis Breitenbach ,  Robin Carl Schwant

    IPC分类号： F01D5/02 ,  C21D7/08 ,  B23P15/04 ,  C21D7/06

    CPC分类号： F01D5/063 ,  B23K2101/001 ,  Y10T29/479 ,  Y10T29/49321 ,  Y10T29/49325

    摘要： A method of making a turbine rotor is disclosed. The method includes forming a last stage disk preform having a disk axis, the preform having a rotor face and an opposed shaft face, the rotor face having a circumferential, axially-extending rotor rib protruding therefrom, the shaft face having a circumferential, axially-extending shaft rib protruding therefrom, the disk preform comprising a disk preform material. The method also includes joining the rotor rib to a rotor preform to form a rotor joint, the rotor preform comprising a rotor preform material. The method further includes joining the shaft rib to a shaft to form a shaft joint, the shaft comprising a shaft material, wherein the disk preform material is different than the rotor preform material and the shaft material.

    摘要翻译： 公开了一种制造涡轮转子的方法。 该方法包括形成具有盘轴的最后级盘预制件，预型件具有转子面和相对的轴面，转子面具有从其突出的圆周方向轴向延伸的转子肋，该轴面具有周向的， 延伸的轴肋从其突出，盘预制件包括盘预制件材料。 该方法还包括将转子肋连接到转子预制件以形成转子接头，转子预制件包括转子预制件材料。 该方法还包括将轴肋连接到轴以形成轴接头，该轴包括轴材料，其中盘预制件材料与转子预制件材料和轴材料不同。