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    Extended tip turbine blade for heavy duty industrial gas turbine
    1.
    发明授权
    Extended tip turbine blade for heavy duty industrial gas turbine 有权
    用于重型工业燃气轮机的延伸尖端涡轮叶片

    公开(公告)号：US06733232B2

    公开(公告)日：2004-05-11

    申请号：US10195687

    申请日：2002-07-15

    申请人： Steve Ingistov ,  Robert Pistor

    发明人： Steve Ingistov ,  Robert Pistor

    IPC分类号： F01D518

    CPC分类号： F01D5/20 ,  F01D5/18

    摘要： An improved turbine blade having a tip configured to provide a reduced blade tip clearance between the blade tip and the inside of a turbine casing and to provide an improved flow path for the discharge of cooling air from the turbine blade tip.

    摘要翻译： 一种改进的涡轮机叶片，其具有构造成在叶片尖端和涡轮机壳体的内部之间提供减小的叶片顶端间隙的尖端，并且提供用于从涡轮机叶片尖端排出冷却空气的改进的流动路径。

    Cooling passages and methods of fabrication
    2.
    发明授权
    Cooling passages and methods of fabrication 有权

    公开(公告)号：US06644921B2

    公开(公告)日：2003-11-11

    申请号：US10010549

    申请日：2001-11-08

    申请人： Ronald Scott Bunker ,  Bin Wei

    发明人： Ronald Scott Bunker ,  Bin Wei

    IPC分类号： F01D518

    CPC分类号： F01D5/187 ,  F01D5/147 ,  F05D2230/11 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/2212 ,  Y02T50/676

    摘要： A turbine portion, for example a turbine blade, for exposure in a hot fluid flow includes at least one internal cooling passage disposed therein. A cooling fluid is introduced within the cooling passage(s) to maintain the bulk temperature of the turbine portion at some acceptable temperature level. A plurality of concavities are disposed on the interior surface of the cooling passage. In one embodiment, the concavities are formed on the interior surface of cooling passage in an array pattern such that a spiral bulk fluid motion is obtained, similar to that which would be formed by a helical rib, but without the rib. The concavity surface pattern serves to enhance heat transfer to the same degree as the conventional rib rougheners, but with significantly less pressure loss due to friction. The spiral motion of the bulk cooling fluid also serves to recirculate central coolant to the heat transfer surface, thereby making the heat exchange process more effective than that for turbulated surfaces.

    Method for reducing cooled turbine element stress and element made thereby
    5.
    发明授权
    Method for reducing cooled turbine element stress and element made thereby 有权
    降低涡轮机元件应力的方法和由此制成的元件

    公开(公告)号：US06514037B1

    公开(公告)日：2003-02-04

    申请号：US09964040

    申请日：2001-09-26

    申请人： Michael Joseph Danowski ,  Gulcharan Singh Brainch

    发明人： Michael Joseph Danowski ,  Gulcharan Singh Brainch

    IPC分类号： F01D518

    CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/114

    摘要： A cooled turbine element including an airfoil and a flowpath boundary member extending laterally from either an inboard end or an outboard end of the airfoil. The member has a flowpath face and an outside face which is cooler than said flowpath face creating a tendency for the member to deflect in a direction away from the flowpath face and causing a thermally induced tensile radial stress in a region of the trailing edge of the airfoil. The element has an interior cooling passage and at least one cooling hole extending from the interior cooling passage to an opening located in an area upstream from the stressed region of the trailing edge to cool the area so the airfoil thermally deflects to a shape corresponding to that of the boundary member thereby lowering the thermally induced tensile radial stress in the airfoil at the trailing edge thereof.

    摘要翻译： 一种冷却的涡轮机元件，包括翼型和从翼型的内侧端部或外侧端部横向延伸的流路边界构件。 该构件具有比所述流路面更冷的流路面和外面，从而形成该构件沿远离流路面的方向偏转的趋势，并且在该流路面的后缘区域中产生热诱导的拉伸径向应力 翼型。 该元件具有内部冷却通道和至少一个从内部冷却通道延伸到位于后缘的应力区域上游区域中的开口的冷却孔，以冷却该区域，使得翼型件热偏转到与之相对应的形状 的边缘部件，从而降低翼缘在其后缘处的热致拉伸径向应力。

    Cooling system for a gas turbine
    6.
    发明授权
    Cooling system for a gas turbine 失效
    燃气轮机的冷却系统

    公开(公告)号：US06506021B1

    公开(公告)日：2003-01-14

    申请号：US09984826

    申请日：2001-10-31

    申请人： Ian David Wilson ,  Samir Armando Salamah ,  Noel Jacob Bylina

    发明人： Ian David Wilson ,  Samir Armando Salamah ,  Noel Jacob Bylina

    IPC分类号： F01D518

    CPC分类号： F01D5/08 ,  F01D5/084 ,  F01D5/085 ,  F05D2260/205 ,  F05D2260/2322 ,  Y02T50/676

    摘要： A plurality of arcuate circumferentially spaced supply and return manifold segments are arranged on the rim of a rotor for respectively receiving and distributing cooling steam through exit ports for distribution to first and second-stage buckets and receiving spent cooling steam from the first and second-stage buckets through inlet ports for transmission to axially extending return passages. Each of the supply and return manifold segments has a retention system for precluding substantial axial, radial and circumferential displacement relative to the rotor. The segments also include guide vanes for minimizing pressure losses in the supply and return of the cooling steam. The segments lie substantially equal distances from the centerline of the rotor and crossover tubes extend through each of the segments for communicating steam between the axially adjacent buckets of the first and second stages, respectively.

    摘要翻译： 多个弧形周向隔开的供应和返回歧管段布置在转子的边缘上，用于分别通过出口连接和分配冷却蒸汽，以分配到第一和第二级桶，并从第一级和第二级接收废冷却蒸汽 桶通过入口端口传输到轴向延伸的返回通道。 每个供应和返回歧管段具有用于排除相对于转子的实质轴向，径向和周向位移的保持系统。 这些段还包括用于最小化冷却蒸汽的供应和返回中的压力损失的导叶。 这些段与转子的中心线基本上相等的距离，并且交叉管分别延伸穿过每个段以分别在第一和第二级的轴向相邻的桶之间连通蒸汽。

    Gas turbine moving blade
    8.
    发明授权
    Gas turbine moving blade 有权
    燃气轮机动叶片

    公开(公告)号：US06481967B2

    公开(公告)日：2002-11-19

    申请号：US09790975

    申请日：2001-02-23

    申请人： Yasuoki Tomita ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga ,  Hisato Arimura ,  Shunsuke Torii ,  Jun Kubota ,  Akihiko Shirota ,  Sunao Aoki ,  Tatsuo Ishiguro

    发明人： Yasuoki Tomita ,  Yukihiro Hashimoto ,  Kiyoshi Suenaga ,  Hisato Arimura ,  Shunsuke Torii ,  Jun Kubota ,  Akihiko Shirota ,  Sunao Aoki ,  Tatsuo Ishiguro

    IPC分类号： F01D518

    CPC分类号： F01D5/20 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/22141

    摘要： A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.

    摘要翻译： 提供了一种燃气轮机动叶片，其防止在燃气轮机停止时由于叶片和平台之间的温度差引起的热应力的发生。 在运动叶片的稳定运行时间内，冷却空气进入冷却通道，流过其它冷却通道，以冷却叶片，然后流出叶片。 具有光滑曲面的凹部在叶片后缘侧的叶片嵌合部附近设置在平台上。 叶片后缘侧的叶片嵌合部的圆角具有比现有的叶片嵌合部曲率大的曲率的曲面。 在圆角下方的用于吹送空气的轮毂槽的横截面积大于叶片后缘的其它槽。 将热障涂层施加到叶片表面。 通过上述结构，使得在燃气轮机停止期间由于叶片和平台之间的温度差导致的热应力变小，并且防止了裂纹的发生。

    Turbine interstage sealing ring
    10.
    发明授权
    Turbine interstage sealing ring 有权
    涡轮级间密封圈

    公开(公告)号：US06464453B2

    公开(公告)日：2002-10-15

    申请号：US09729370

    申请日：2000-12-04

    申请人： Steven Milo Toborg ,  Dennis Eugene Moore ,  Richard William Albrecht, Jr.

    发明人： Steven Milo Toborg ,  Dennis Eugene Moore ,  Richard William Albrecht, Jr.

    IPC分类号： F01D518

    CPC分类号： F01D11/001 ,  F01D5/081 ,  F05D2240/55 ,  Y02T50/676

    摘要： A unitary interstage sealing ring for bridging and sealing the space between the blade shanks of adjacent turbine rotors in a multi-stage turbine. The sealing ring serves to confine relatively cool air conveyed to the turbine so the cooling air flows into the turbine blades for maintaining the blades at a desired temperature. The sealing ring includes a disk-shaped body member that includes a pair of axially-spaced, radially-extending arms that terminate in respective seal teeth for engagement with a stationary annular sealing member. Each of the radial arms includes an outwardly-extending axial arm that terminates in a disk engagement member for sealing engagement with the face of an adjacent turbine disk to confine cooling air within the space between the adjacent turbine disks. Additionally, one of the disk engagement members includes at least one, projection that contacts a respective turbine rotor to limit relative rotation between the sealing ring and the turbine.

    摘要翻译： 用于桥接和密封多级涡轮机中相邻涡轮转子的叶片柄之间的空间的整体级间密封环。 密封环用于限制输送到涡轮机的相对较冷的空气，使得冷却空气流入涡轮机叶片，以将叶片保持在期望的温度。 密封环包括盘形主体构件，其包括一对轴向间隔开的径向延伸的臂，其终止于相应的密封齿中，用于与静止的环形密封构件接合。 每个径向臂包括向外延伸的轴向臂，其终止于盘接合构件，用于与相邻涡轮盘的表面密封接合，以将冷却空气限制在相邻涡轮盘之间的空间内。 此外，一个盘接合构件包括至少一个突出部，其与相应的涡轮转子接触以限制密封环和涡轮机之间的相对旋转。