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    SEAL MECHANISM OF GAS TURBINE ENGINE
    1.
    发明专利
    SEAL MECHANISM OF GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11229810A

    公开(公告)日：1999-08-24

    申请号：JP33516798

    申请日：1998-11-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

    IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16

    Abstract: PROBLEM TO BE SOLVED: To achieve an abrasive end portion for a seal mechanism of a gas turbine engine that receives a high degree of wear which is more durable, and the production of which is less expensive. SOLUTION: An abrasive end portion 28 includes a zirconium oxide wear coating 44 which is harder than a abraded seal surface such that it is able to grind the abraded seal surface, and which directly covers the top which has substantially no macrogrit. The coating 44 has a pillar-like structure and contains a stabilizer of approximately 3 wt.% to approximately 25 wt.%. The stabilizer may be selected from yttrium oxide, magnesium oxide, calcium oxide, or a mixture of these materials.

    5.
    发明专利
    未知

    公开(公告)号：DE69826096T2

    公开(公告)日：2005-09-29

    申请号：DE69826096

    申请日：1998-11-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

    IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28

    Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.

    6.
    发明专利
    未知

    公开(公告)号：DE69826096D1

    公开(公告)日：2004-10-14

    申请号：DE69826096

    申请日：1998-11-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FRELING MELVIN ,  GUPTA DINESH K ,  LAGUEUX KEN ,  DEMASI-MARCIN JEANINE T

    IPC: F01D5/20 ,  F01D11/00 ,  F01D11/12 ,  F02C7/28 ,  F16J15/16 ,  F01D5/28

    Abstract: A gas turbine engine seal system includes a rotating member 12;30 having an abrasive tip 28 disposed in use in rub relationship to a stationary, abradable seal surface. The abrasive tip comprises a zirconium oxide abrasive coat 44 having a columnar structure that is harder than the abradable seal surface such that the abrasive tip can cut the abradable seal surface. The coat 44 comprises zirconium oxide and about 3% to 25% of a stabilizer selected from yttrium oxide, magnesium oxide, calcium oxide or mixtures thereof.

    TURBOMACHINERY BLADE OUTER AIR SEAL
    9.
    发明公开
    TURBOMACHINERY BLADE OUTER AIR SEAL 审中-公开
    TURBOMASCHINENSCHAUFELAUSSENLUFTDICHTUNG

    公开(公告)号：EP3068978A4

    公开(公告)日：2017-08-30

    申请号：EP14861879

    申请日：2014-11-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PHILBRICK GRAHAM RYAN ,  LAGUEUX KEN

    IPC: F01D9/04 ,  F01D11/00 ,  F01D11/12

    CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/001 ,  F01D11/122 ,  F05D2220/30 ,  F05D2240/11 ,  F05D2240/307 ,  F05D2300/10 ,  F05D2300/20

    Abstract: A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.

    Abstract translation: 涡轮机械密封板包括具有限定具有基板宽度的表面的第一材料的基板。 基底包括第一末端延伸部分，该第一末端延伸部分从基底的末端部分凸起并延伸。 第一终点延伸部相对于表面向外延伸直至终点延伸高度。 涡轮机械密封板还包括具有第二材料的涂层，该第二材料覆盖基板的表面并限定涂层宽度。 涂层邻接第一终点延伸的一侧。 涂层宽度可以基本上等于末端延伸高度。

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