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    Methods and systems for cooling gas turbine engine airfoils
    1.
    发明授权
    Methods and systems for cooling gas turbine engine airfoils 有权
    用于冷却燃气涡轮发动机翼型的方法和系统

    公开(公告)号：US06561758B2

    公开(公告)日：2003-05-13

    申请号：US09844206

    申请日：2001-04-27

    申请人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Brian Alan Norton

    发明人： Gerard Anthony Rinck ,  Jonathan Philip Clarke ,  Brian Alan Norton

    IPC分类号： F01D518

    CPC分类号： F01D5/20 ,  F01D5/186 ,  Y10T29/49341

    摘要： A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.

    摘要翻译： 燃气涡轮发动机包括包括翼型的转子叶片，其有助于减少由于翼型后缘切割引起的制造损失。 每个翼型件包括在前缘和后缘连接的第一和第二侧壁。 侧壁限定了一个冷却腔，其包括由侧壁和翼型件前缘限定的至少一个前缘室，以及由侧壁和翼型后缘界定的后缘室。 冷却腔后缘室包括尖端区域，喉部和流动连通地连通的通道区域，使得喉部位于尖端区域和通道区域之间。 此外，尖端区域由翼面尖端限制，并且从咽喉分开延伸，使得尖端区域的宽度大于喉部的宽度。

    Fabricated repair of cast nozzle
    4.
    发明授权
    Fabricated repair of cast nozzle 有权
    铸造喷嘴的修补

    公开(公告)号：US06793457B2

    公开(公告)日：2004-09-21

    申请号：US10295185

    申请日：2002-11-15

    申请人： James Walter Caddell ,  Matthew Nicklus Miller ,  Brian Alan Norton

    发明人： James Walter Caddell ,  Matthew Nicklus Miller ,  Brian Alan Norton

    IPC分类号： F01D904

    CPC分类号： B23P6/002 ,  F01D5/005 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/49318 ,  Y10T29/49323

    摘要： A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band. The thickness of the collar is tapered in an axial direction, and a relief is formed in the collar to provide assembly clearance with adjacent components.

    摘要翻译： 一种用于修复具有设置在外带和内带之间的至少一个叶片的涡轮喷嘴段的方法，包括将内带与喷嘴段分离，并将内带连接到具有外带和至少一个叶片的新制造的更换铸件。 替代铸件包括形成在叶片的一端上的安装平台和形成在安装平台上的凸台。 轴环连接到内带并且在其中形成有槽。 然后将凸台插入槽中，并且安装平台被容纳在形成在内带中的凹部中。 连接是通过将老板连接到领带和安装平台到内带来完成的。 轴环的厚度在轴向方向上是锥形的，并且凸起形成在轴环中以提供与相邻部件的组装间隙。

    Selectively thinned turbine blade
    7.
    发明授权
    Selectively thinned turbine blade 失效
    选择性稀薄的涡轮叶片

    公开(公告)号：US07121802B2

    公开(公告)日：2006-10-17

    申请号：US10889838

    申请日：2004-07-13

    申请人： Robert Edward Athans ,  Brian Alan Norton

    发明人： Robert Edward Athans ,  Brian Alan Norton

    IPC分类号： F01D5/16

    CPC分类号： F01D5/22 ,  F05D2240/80 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S416/50

    摘要： A turbine blade includes an airfoil, platform, shank, and dovetail. The platform includes a first side disposed along the pressure side of the airfoil, and an opposite second side disposed along the airfoil suction side. The platform second side includes an integral damper keeper disposed below the midchord of the airfoil, and is locally thinner at the forward and aft ends of the platform second side for reducing blade weight.

    摘要翻译： 涡轮叶片包括翼型件，平台，柄和燕尾榫。 平台包括沿翼型的压力侧设置的第一侧和沿翼型吸力侧设置的相对的第二侧。 平台第二侧包括设置在翼型的中间下方的整体的阻尼器保持器，并且在平台第二侧的前端和后端处局部变薄，以减小叶片的重量。

    Skirted turbine blade
    8.
    发明授权
    Skirted turbine blade 有权
    涡轮叶片

    公开(公告)号：US07097429B2

    公开(公告)日：2006-08-29

    申请号：US10889837

    申请日：2004-07-13

    申请人： Robert Edward Athans ,  William Charles Herman ,  Brian Alan Norton

    发明人： Robert Edward Athans ,  William Charles Herman ,  Brian Alan Norton

    IPC分类号： F01D5/14

    CPC分类号： F01D11/008 ,  Y02T50/671

    摘要： A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.

    摘要翻译： 涡轮叶片包括翼型件，平台，柄和燕尾榫。 柄部包括对应于翼型件的前缘和后缘的相对的前和后面，以及对应于翼型的压力和抽吸侧的相对的第一和第二侧。 柄还包括从两侧向外延伸的凸耳，第一凸耳具有朝向平台向外延伸的倒置的裙部，以连接柄后部。 当安装在发动机中时，裙部与密封体配合以减少叶片间的泄漏。

    Teardrop film cooled blade
    9.
    发明授权
    Teardrop film cooled blade 有权
    泪滴膜冷却叶片

    公开(公告)号：US07008186B2

    公开(公告)日：2006-03-07

    申请号：US10664649

    申请日：2003-09-17

    申请人： Robert John Heeg ,  Brian Alan Norton ,  Scott Joseph Schmid ,  Ganesh Nagab Kumar

    发明人： Robert John Heeg ,  Brian Alan Norton ,  Scott Joseph Schmid ,  Ganesh Nagab Kumar

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F05D2260/201 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

    摘要： A turbine blade includes an airfoil having an internal cooling circuit with a first flow passage disposed directly behind the leading edge followed by a second flow passage separated therefrom by a corresponding bridge. The bridge includes a row of impingement apertures for cooling the leading edge. The suction sidewall of the airfoil includes a row of diffusion film cooling first holes extending in flow communication with the first passage. The first holes have a compound inclination angle, with a quadrilateral cross section forming a generally teardrop shaped outlet in the convex contour of the suction sidewall.

    摘要翻译： 涡轮叶片包括具有内部冷却回路的翼型件，其具有直接设置在前缘后面的第一流动通道，随后是由相应的桥隔开的第二流动通道。 桥梁包括一排用于冷却前缘的冲击孔。 翼型件的吸力侧壁包括一排扩散膜，冷却与第一通道流动连通的第一孔。 第一孔具有复合倾斜角，四边形横截面在吸力侧壁的凸形轮廓中形成大致泪珠状出口。

    Turbine nozzle segment and method of repairing same
    10.
    发明授权
    Turbine nozzle segment and method of repairing same 失效
    涡轮喷嘴段及其修理方法

    公开(公告)号：US06905308B2

    公开(公告)日：2005-06-14

    申请号：US10300098

    申请日：2002-11-20

    申请人： Michael Philip Hagle ,  Brian Alan Norton ,  James Walter Caddell, Jr.

    发明人： Michael Philip Hagle ,  Brian Alan Norton ,  James Walter Caddell, Jr.

    IPC分类号： F01D9/02 ,  B23P6/00 ,  F01D5/00 ,  F02C7/00 ,  F03B3/16

    CPC分类号： B23P6/002 ,  F01D5/005 ,  Y02T50/67 ,  Y02T50/673 ,  Y10T29/49318 ,  Y10T29/49323

    摘要： A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

    摘要翻译： 提供一种用于修复涡轮喷嘴段的方法，其具有设置在外带和内带之间的至少一个叶片。 该方法包括将内带与喷嘴段分离，并将内带连接到具有外带和叶片的新制造的更换铸件。 更换铸件包括翼型桩。 翼型坯被容纳在内带形成的凹部中。 通过将翼型桩连接到内带来完成加盟。 替代铸件可以从新制造的单一铸造中改变。