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    SEGMENTED SEAL FOR GAS TURBINE ENGINE
    14.
    发明申请
    SEGMENTED SEAL FOR GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机的分段密封件

    公开(公告)号：WO2015119687A2

    公开(公告)日：2015-08-13

    申请号：PCT/US2014064956

    申请日：2014-11-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HILL JAMES D ,  SUCIU GABRIEL L ,  MERRY BRIAN D ,  ALVANOS IOANNIS

    IPC: F02C7/28 ,  F01D11/00

    CPC classification number: F01D11/005 ,  F01D5/06 ,  F01D5/081 ,  F01D9/041 ,  F01D11/001 ,  F05D2220/32 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2260/30 ,  Y02T50/676

    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.

    Abstract translation: 本公开的一个示例性实施例涉及燃气涡轮发动机。 发动机包括第一转子盘，第二转子盘和周向分段的密封件。 分段式密封件接合第一转子盘和第二转子盘。 分段式密封件还包括接触第一盘的前表面，接触第二盘的后表面以及径向外表面。 此外，（1）后表面和（2）前表面和径向外表面中的一个包括穿孔以允许流体流过分段密封件的内部。

    PRETRENCHED ROTOR FOR GAS TURBINE ENGINE
    15.
    发明申请
    PRETRENCHED ROTOR FOR GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的预制转子

    公开(公告)号：WO2014189564A3

    公开(公告)日：2015-02-19

    申请号：PCT/US2014016240

    申请日：2014-02-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS

    IPC: F01D5/02 ,  F04D29/26

    CPC classification number: F01D5/143 ,  F01D11/001 ,  F04D29/164 ,  F04D29/321 ,  F04D29/329 ,  F04D29/542 ,  Y02T50/673

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor having a pretrench that receives at least a portion of a tip of a stator, the portion of the tip extending radially into the pretrench.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括转子，该转子具有接收定子顶端的至少一部分的预转，所述尖端的该部分径向地延伸到所述预压。

    TURBOMACHINERY SEAL
    17.
    发明申请
    TURBOMACHINERY SEAL 审中-公开

    公开(公告)号：WO2013115874A3

    公开(公告)日：2013-09-26

    申请号：PCT/US2012064456

    申请日：2012-11-09

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  SUCIU GABRIEL L

    IPC: F01D11/00 ,  F01D11/12

    CPC classification number: F01D11/001 ,  F01D11/122 ,  F01D11/127 ,  F05D2230/64 ,  F05D2250/184 ,  F05D2260/38

    Abstract: A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor.

    Abstract translation: 一种用于将旋转机器的转子密封到其定子的密封件，所述定子外接转子并且通过间隙与转子分开，所述密封件包括非旋转密封元件，所述非旋转密封元件容纳在定子中的环形槽内并且相对于所述定子径向可平移并且延伸到间隙 用于密封由转子承载的旋转密封元件。 容纳在非旋转密封元件和狭槽的底部之间的弹性偏置元件朝向旋转密封元件径向向内地偏置非旋转密封元件并限制非旋转密封元件的径向向外移动。 从槽延伸到所述间隙中的引导件接合非旋转密封元件以防止其与机器的转子轴向错位。

    INTEGRATED BLADED FLUID SEAL
    18.
    发明专利
    INTEGRATED BLADED FLUID SEAL 未知

    公开(公告)号：CA2564073A1

    公开(公告)日：2007-04-27

    申请号：CA2564073

    申请日：2006-10-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA ,  REINHARDT GREGORY E

    IPC: F01D11/08 ,  F01D5/20 ,  F01D25/12

    Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

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