Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation
    2.
    发明授权
    Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation 失效
    燃气轮机中的弦铰链密封件的补充密封和安装方法

    公开(公告)号:US06764081B2

    公开(公告)日:2004-07-20

    申请号:US10028932

    申请日:2001-12-28

    IPC分类号: F16J1502

    CPC分类号: F16J15/0887 F01D11/005

    摘要: In a gas turbine, a supplemental seal is provided between an annular axially facing sealing surface of a nozzle support ring and an annular axially opposed sealing surface formed by circumferentially adjacent nozzle segments. Each segment carries an inner rail mounting a chordal hinge seal which engages the sealing surface of the nozzle support ring. That seal is supplemented by a generally arcuate V-shaped seal between the sealing surfaces which opens radially inwardly toward a high pressure leakage path past the chordal hinge seal. The supplemental seal is initially compressed and maintained in a compressed condition during installation by application of a solder. At operating temperature, the solder melts away, releasing the supplemental seal to seal between the nozzle support ring and nozzle segments.

    摘要翻译: 在燃气轮机中,在喷嘴支撑环的环形轴向面对的密封表面和由周向相邻的喷嘴段形成的环形轴向相对的密封表面之间提供补充密封。 每个段都带有一个内轨道,其安装一个与喷嘴支撑环的密封表面接合的弦索铰链密封件。 在密封表面之间通过弧形的V形密封件补充该密封件,该密封表面径向向内朝着通过弦杆铰链密封件的高压泄漏路径开口。 在安装期间,通过施加焊料,补充密封件被初始压缩并保持在压缩状态。 在操作温度下,焊料熔化掉,释放补充密封件以密封喷嘴支撑环和喷嘴段之间。

    Supplemental seal for the chordal hinge seals in a gas turbine
    4.
    发明授权
    Supplemental seal for the chordal hinge seals in a gas turbine 失效
    燃气轮机中的弦铰链密封的补充密封

    公开(公告)号:US06641144B2

    公开(公告)日:2003-11-04

    申请号:US10028924

    申请日:2001-12-28

    IPC分类号: F01D904

    CPC分类号: F16J15/0887 F01D11/005

    摘要: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a flexible supplemental seal is disposed between the support ring and inner band of the nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the flexible seal extends between the inner rail and the sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin extends arcuately in sealing engagement with the nozzle support ring.

    摘要翻译: 在具有在每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气涡轮机中,柔性补充密封件设置在喷嘴段的支撑环和内带之间的径向向内 弦铰链密封。 为了最小化或防止跨越铰链密封件的泄漏流动,柔性密封件在内侧轨道和支撑环的密封表面之间延伸,该密封表面在弦向铰链密封件的径向向内。 柔性密封件的第一边缘接合由内轨道承载的直线槽。 相对的边缘与喷嘴支撑环密封接合地弓形延伸。

    Supplemental seal for the chordal hinge seals in a gas turbine
    5.
    发明授权
    Supplemental seal for the chordal hinge seals in a gas turbine 有权
    燃气轮机中的弦铰链密封的补充密封

    公开(公告)号:US06572331B1

    公开(公告)日:2003-06-03

    申请号:US10029228

    申请日:2001-12-28

    IPC分类号: F01D904

    CPC分类号: F01D11/005 F16J15/0887

    摘要: In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment. The supplemental seal is formed of a preloaded flexible sheet metal seal having a first margin secured in a linear groove extending in a tangential direction along the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite second margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Sealing pressure against the preloaded flexible seal from a high pressure region maintains the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends tangentially and end edges thereof overlap one another to form a seal between adjacent nozzle segments.

    摘要翻译: 在具有每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气轮机中,在喷嘴段的支撑环和内轨道之间设置补充密封。 辅助密封件由预加载的柔性金属片密封件形成,该密封件具有固定在沿着沿喷嘴段的内轨道的切线方向延伸的直线槽中的第一边缘,具有弯曲边缘以与其形成密封。 相对的第二边缘具有抵靠喷嘴支撑环的轴向相对的密封表面的边缘。 从高压区域对预加载的柔性密封件的密封压力保持了支撑环的密封表面和段之间的密封。 辅助密封件切向延伸并且其端部边缘彼此重叠以在相邻的喷嘴段之间形成密封。

    Adaptive Eductor System
    6.
    发明申请
    Adaptive Eductor System 有权
    自适应电感系统

    公开(公告)号:US20130156547A1

    公开(公告)日:2013-06-20

    申请号:US13331062

    申请日:2011-12-20

    IPC分类号: F01D25/18

    摘要: An apparatus is provided having a first zone with a fluid flow at a first pressure, and a second zone with a fluid flow at a second pressure. A sump cavity is provided in fluid communication with the first zone and a sump vent. An eductor system may be provided with a fluid flow path therethrough and in fluid communication with the second zone and the sump vent. The eductor system may be provided with an altitude sensing valve and may also be provided with gage pressure sensing valve. The eductor system may further be provided with a second gage pressure sensing valve and may also be provided with an orifice plate. The gage pressure sensing valves may react to the gage pressure of the second zone.

    摘要翻译: 提供一种装置,其具有在第一压力下具有流体流动的第一区域和在第二压力下具有流体流动的第二区域。 提供与第一区域和贮槽通气口流体连通的贮槽腔。 喷射器系统可以设置有穿过其的流体流动路径并且与第二区域和贮槽通气口流体连通。 喷射器系统可以设置有高度感测阀,并且还可以设置有压力传感阀。 喷射器系统还可以设置有第二量规压力感测阀,并且还可以设置有孔板。 计量压力传感阀可以对第二区域的表压进行反应。

    METHOD AND APPARATUS FOR SEGREGATED OIL SUPPLY AND SCAVENGE IN A GAS TURBINE ENGINE
    7.
    发明申请
    METHOD AND APPARATUS FOR SEGREGATED OIL SUPPLY AND SCAVENGE IN A GAS TURBINE ENGINE 有权
    气体涡轮发动机中分散供油和切割的方法与装置

    公开(公告)号:US20130055721A1

    公开(公告)日:2013-03-07

    申请号:US13225510

    申请日:2011-09-05

    IPC分类号: F02C7/06

    摘要: A gas turbine engine oil supply and scavenge apparatus includes: a stationary first frame comprising a first hub and a first outer ring interconnected by an array of radially-extending hollow first struts; a forward wet cavity defined radially inboard of the first frame, having a first rolling element bearing disposed therein; a supply line extending from the first outer ring through one of the first struts and communicating with the forward wet cavity, the supply line adapted to discharge oil to the forward wet cavity; a stationary second frame comprising a second hub and a second outer ring interconnected by an array of radially-extending hollow second struts, the second frame disposed aft of the first frame; and a scavenge path communicating with the forward wet cavity and adapted to remove oil-air mist from the forward wet cavity, the scavenge path defined at least in part by the second frame.

    摘要翻译: 燃气涡轮发动机机油供应和清除装置包括:固定的第一框架,包括第一轮毂和通过径向延伸的中空的第一支柱的阵列互连的第一外环; 径向设置在第一框架内侧的前向湿空腔,其中设置有第一滚动元件轴承; 供应管线从第一外环通过第一支柱中的一个延伸并与前部湿空腔连通,供应管线适于将油排放到前部湿空腔; 固定的第二框架,包括第二轮毂和通过径向延伸的中空的第二支柱的阵列互连的第二外环,所述第二框架设置在所述第一框架的后面; 以及与前进湿腔相通并适于从前方湿腔去除油气雾的清除路径,所述扫气路径至少部分地由第二框架限定。

    Method for modeling material constitutive behavior
    8.
    发明授权
    Method for modeling material constitutive behavior 失效
    材料本构行为建模方法

    公开(公告)号:US07240562B2

    公开(公告)日:2007-07-10

    申请号:US11130851

    申请日:2005-05-17

    IPC分类号: G01D1/16

    CPC分类号: B23B1/00

    摘要: In modeling material constitutive behavior, a methodology determines tool-chip friction and a position of a stagnation point on a cutting tool. The methodology includes measuring a ratio of cutting force to thrust force and measuring a chip thickness, hch, produced by applying the cutting tool to a material. Initial values are estimated for tool chip friction and position of stagnation. The tool chip friction and position of stagnation are calculated to satisfy a specified relationship. Based on tool chip friction and position of stagnation, material strains, material strain-rates, material temperatures, and material stresses are calculated.

    摘要翻译: 在建模材料本构行为时,一种方法确定刀具磨擦和切削刀具上停滞点的位置。 该方法包括测量切削力与推力的比率,并测量通过将切削刀具应用于材料而产生的切屑厚度。 估计工具芯片摩擦和停滞位置的初始值。 计算工具芯片摩擦和停滞位置以满足特定的关系。 基于工具芯片摩擦和停滞位置,计算材料应变,材料应变率,材料温度和材料应力。