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    Non-mechanically fastened TOBI heat shield
    1.
    发明授权
    Non-mechanically fastened TOBI heat shield 有权
    非机械固定TOBI隔热罩

    公开(公告)号：US08899924B2

    公开(公告)日：2014-12-02

    申请号：US13164234

    申请日：2011-06-20

    Applicant: Ioannis Alvanos

    Inventor： Ioannis Alvanos

    IPC: F04D31/00 ,  F01D5/08 ,  F02C7/18

    CPC classification number: F01D5/081 ,  F02C7/18 ,  F05D2260/30 ,  Y02T50/676 ,  Y10T29/49327

    Abstract: A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.

    Abstract translation: 高压涡轮机包括定子，转子，切向的车载喷射器和隔热罩。 转子位于定子的下游，切向的车载喷射器将冷却空气引导到转子。 隔热板通过与定子和切向机载喷射器的邻接保持。

    Gas turbine engine case
    6.
    发明授权
    Gas turbine engine case 有权
    燃气涡轮发动机外壳

    公开(公告)号：US08162605B2

    公开(公告)日：2012-04-24

    申请号：US12013617

    申请日：2008-01-14

    Applicant: Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry

    Inventor： Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry

    IPC: F01D25/28

    CPC classification number: F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/49826

    Abstract: A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.

    Abstract translation: 燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。 在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

    Gas turbine engine with concave pocket with knife edge seal
    7.
    发明授权
    Gas turbine engine with concave pocket with knife edge seal 有权
    带凹口的燃气轮机，带刀口密封

    公开(公告)号：US07708520B2

    公开(公告)日：2010-05-04

    申请号：US11605678

    申请日：2006-11-29

    Applicant: Roger E. Paolillo ,  Ioannis Alvanos ,  Cheng-Zhang Wang

    Inventor： Roger E. Paolillo ,  Ioannis Alvanos ,  Cheng-Zhang Wang

    IPC: F01D11/02

    CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2250/712

    Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.

    Abstract translation: 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。

    Segmented fluid seal assembly
    9.
    发明申请
    Segmented fluid seal assembly 审中-公开
    分段流体密封组件

    公开(公告)号：US20080044284A1

    公开(公告)日：2008-02-21

    申请号：US11505165

    申请日：2006-08-16

    Applicant: Ioannis Alvanos

    Inventor： Ioannis Alvanos

    IPC: F01D11/00

    CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2230/60 ,  F05D2260/30

    Abstract: A rotor assembly for a turbine engine includes a rotor disk having rotor blades mounted about the circumference and rotatable about a central longitudinal axis. A fluid seal extends about the circumference of the rotor disk in close proximity to a stationary component to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a plurality of disk seal segments and a plurality of blade seal segments. The disk seal segments each attach to the rotor disk between the rotor blades. The blade seal segments attach to the blades. After the blades are assembled the blade seal segments and the disk seal segments align to form a segmented, ring-like fluid seal around the circumference of the rotor disk.

    Abstract translation: 用于涡轮发动机的转子组件包括转子盘，转子盘具有围绕圆周安装的转子叶片，并可围绕中心纵向轴线旋转。 流体密封件围绕转子盘的圆周延伸，靠近固定部件，以将转子叶片和固定部件之间的空间分离成单独的空腔。 流体密封件包括多个盘密封段和多个叶片密封段。 盘密封片段各自连接到转子叶片之间的转子盘上。 叶片密封段附接到叶片。 在叶片组装之后，叶片密封段和盘密封段对齐以在转子盘的圆周周围形成分段的环状流体密封。

    Turbine cooling air sealing
    10.
    发明申请
    Turbine cooling air sealing 有权
    涡轮冷却空气密封

    公开(公告)号：US20070059158A1

    公开(公告)日：2007-03-15

    申请号：US11224613

    申请日：2005-09-12

    Applicant: Ioannis Alvanos ,  Rajendra Agrawal ,  Hector Pinero

    Inventor： Ioannis Alvanos ,  Rajendra Agrawal ,  Hector Pinero

    IPC: F03B11/00

    CPC classification number: F01D5/081 ,  F01D11/001 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28

    Abstract: A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing means restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing means restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing means and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.

    Abstract translation: 涡轮发动机部分具有静止叶片台和旋转叶片台。 叶片台与叶片台间隔开以在它们之间形成环形室。 歧管将加压流体输送到腔室。 外径（OD）密封装置限制加压流体从腔室泄漏。 内径（ID）密封装置限制加压流体从腔室泄漏。 流动引导件在内径密封装置和歧管之间径向延伸。 流动导向装置将室平分成一个固定室部分和旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。

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