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    NON-LINEAR BUMPER BEARINGS
    2.
    发明申请
    NON-LINEAR BUMPER BEARINGS 审中-公开
    非线性保温轴承

    公开(公告)号：WO2015102719A3

    公开(公告)日：2015-09-11

    申请号：PCT/US2014060070

    申请日：2014-10-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUONG LOC QUANG ,  HU XIAOLAN

    IPC: F01D25/16 ,  F02C7/06 ,  F16C17/03 ,  F16C27/02

    CPC classification number: F01D25/164 ,  F01D5/021 ,  F01D25/16 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/52 ,  F16C17/02 ,  F16C17/03 ,  F16C17/24 ,  F16C27/02 ,  F16C33/108 ,  F16C2360/23

    Abstract: A bumper bearing assembly includes a bearing housing having a level of radial spring stiffness, wherein the bearing housing defines a bearing seat. A bumper bearing is connected to the bearing housing by a spring having a level of radial spring stiffness lower than that of the bearing housing. The bumper bearing is configured to apply the level of radial spring stiffness of the spring against a rotor with the bumper bearing spaced apart from the bearing seat. The bearing housing is configured to apply the level of radial spring stiffness of the bearing housing against the rotor with the bumper bearing seated against the bearing seat.

    Abstract translation: 保险杠轴承组件包括具有径向弹簧刚度水平的轴承壳体，其中轴承壳体限定轴承座。 保险杠轴承通过具有比轴承壳体的径向弹簧刚度水平低的弹簧连接到轴承壳体。 缓冲器轴承构造成将缓冲器轴承与轴承座隔开的情况下将弹簧的径向弹簧刚度水平应用于转子。 轴承壳体构造成在保险杠轴承座靠在轴承座上时将轴承壳体的径向弹簧刚度水平应用于转子。

    NON-LINEARLY DEFLECTING BRUSH SEAL LAND
    4.
    发明公开
    NON-LINEARLY DEFLECTING BRUSH SEAL LAND 审中-公开
    NICHTLINEARER ABLENKENDEBÜRSTENDICHTUNGSFLÄCHE

    公开(公告)号：EP3055512A4

    公开(公告)日：2017-06-21

    申请号：EP14852811

    申请日：2014-09-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUONG LOC QUANG ,  HU XIAOLAN

    IPC: F01D11/08 ,  F01D5/08 ,  F01D11/00 ,  F16J15/32 ,  F16J15/3288 ,  F16J15/44

    CPC classification number: F01D11/00 ,  F01D5/081 ,  F01D11/001 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3288 ,  Y02T50/676

    Abstract: A brush seal land is disclosed. The brush seal land may comprise a first portion configured to be coupled to a turbine disc of an aircraft engine and a second portion having a contact surface. The brush seal land may comprise a concave annular structure. The second portion may deflect through a clearance area in response to contact with a brush. The second portion may not deflect in response to contact with a brush after the second portion has deflected through a clearance area in response to contact with the brush. The contact surface comprises tungsten carbide. The brush seal land may comprise INCONEL. The brush seal land may be configured to be coupled to an annular member extending from the turbine disc. The brush seal land may reduce abrasion to an annular member extending from the turbine disc by a brush.

    Abstract translation: 公开了一种刷式密封面。 刷式密封面可以包括构造成联接到飞机发动机的涡轮盘的第一部分和具有接触表面的第二部分。 刷式密封面可以包括凹形环形结构。 响应于与刷子的接触，第二部分可以偏转穿过间隙区域。 在第二部分响应于与刷子的接触而偏转通过间隙区域之后，第二部分可以不响应于与刷子的接触而偏转。 接触表面包含碳化钨。 刷式密封面可以包括INCONEL。 刷式密封件台面可构造成联接到从涡轮盘延伸的环形构件。 刷式密封面可以减少对通过刷子从涡轮盘延伸的环形构件的磨损。

    DETUNING TRAILING EDGE COMPOUND LEAN CONTOUR
    5.
    发明公开
    DETUNING TRAILING EDGE COMPOUND LEAN CONTOUR 审中-公开
    VERSTELLENDE ZUSAMMENGESETZTE SCHMALE KONTUR EINER AUSTRITTSKANTE

    公开(公告)号：EP3055507A4

    公开(公告)日：2017-06-21

    申请号：EP14851901

    申请日：2014-10-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUONG LOC QUANG ,  HU XIAOLAN ,  YANG GAO ,  GARCIA JESUS A ,  SAPIRO DAN G

    IPC: F01D5/14 ,  F01D5/16

    CPC classification number: F01D5/141 ,  F01D5/14 ,  F01D5/145 ,  F01D5/16 ,  F01D5/26 ,  F05D2240/304 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A rotor blade comprises a blade platform and an airfoil. The airfoil comprises a blade tip, a leading edge, and a trailing edge with a stiffening compound lean contour. The blade tip is radially opposite the blade platform, and defines a blade span between the blade itself and the blade platform. The leading and trailing edges extend from the blade platform to the blade tip to define blade chords between the leading edge and the trailing edge. The compound lean contour comprises a positive lean section located at the lean tip, and extending along a lean axis to a lean end. The negative lean section is located radially inward of the positive lean section, and extends along the lean axis to the lean end.

    Abstract translation: 转子叶片包括叶片平台和翼型件。 翼型包括叶片尖端，前缘和具有加强复合物倾斜轮廓的后缘。 叶片尖端与叶片平台径向相对，并且限定叶片自身和叶片平台之间的叶片跨度。 前缘和后缘从叶片平台延伸到叶片尖端，以在前缘和后缘之间限定叶片弦。 该复合贫油轮廓包括位于贫尖端的正贫油部分，并沿着贫油轴延伸至贫油端。 负倾斜部分位于正倾斜部分的径向内侧，并且沿着倾斜轴线延伸至倾斜端部。

    Reducción de la excitación de paletas separadas uniformemente en boquillas de turbina
    6.
    发明专利
    Reducción de la excitación de paletas separadas uniformemente en boquillas de turbina 未知

    公开(公告)号：ES2706388T3

    公开(公告)日：2019-03-28

    申请号：ES13849387

    申请日：2013-10-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUONG LOC QUANG ,  HU XIAOLAN ,  YANG GAO ,  FALCONER STEVEN R ,  GORDON RALPH E ,  GARCIA JESUS A ,  SAPIRO DAN G ,  KAUL ULRIKE ,  JOHNSON GREGORY G ,  FISHLER BENJAMIN E

    IPC: F01D9/04 ,  F01D5/14 ,  F01D5/16

    Abstract: Método para reducir las amplitudes de excitación que afectan a la durabilidad de los álabes de turbina en un conjunto de boquilla de turbina que tiene una pluralidad de paletas (10) y álabes (32) de turbina, que comprende las etapas de: identificar un diseño de álabe de turbina de dicho conjunto de boquilla (20) de turbina; realizar un análisis de modelo modal de al menos una de dichos álabes (32) de turbina en dicho diseño de álabe de turbina utilizando un ordenador; garantizar que cada uno de dichos álabes (32) de turbina no sufra aero-excitación de un flujo de aguas arriba en dichas paletas (10) en un rango de velocidad de funcionamiento; identificar las frecuencias naturales de los álabes con respecto a dichas paletas (10) utilizando dicho ordenador; caracterizado por que el método comprende, además, las etapas de: determinar al menos una modificación a un borde de salida (42, 44) de al menos una de dichas paletas para reducir las amplitudes de excitación, y modificar al menos una de dichas paletas (10) en dicho borde de salida (42, 44) de acuerdo con la determinación de la etapa anterior; y - realizar un análisis CFD para modificar el campo de presión local mediante la descarga de aire en el borde de salida de la aleta de la boquilla para evitar la acumulación de la energía del fluido extraída por dichos álabes; modificar un campo de presión local mediante la utilización de un flujo de descarga de aire próximo a dicho borde de salida (42, 44) de acuerdo con el análisis CFD de la etapa anterior.

    TURBINE DISC WITH REDUCED NECK STRESS CONCENTRATION
    8.
    发明专利
    TURBINE DISC WITH REDUCED NECK STRESS CONCENTRATION 未知

    公开(公告)号：CA2887943A1

    公开(公告)日：2014-06-26

    申请号：CA2887943

    申请日：2013-12-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUONG LOC QUANG ,  HU XIAOLAN

    IPC: F01D5/03 ,  F01D5/02 ,  F02C7/00

    Abstract: A disc with two sides includes a hub having a bore and a bore radius, a neck, and a rim. The neck is connected to and radially outward of the hub and has an inner wedge with a curved section on one side of the disc, an outer wedge with a curved section on that same side of the disc, and a center section between the wedges with a flat side on that same side of the disc. The rim is connected to and radially outward of the neck, the rim having a radius that is no more than seven times greater than the bore radius.

    10.
    发明专利
    未知

    公开(公告)号：DE60138173D1

    公开(公告)日：2009-05-14

    申请号：DE60138173

    申请日：2001-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： JARMON DAVID C ,  HU XIAOLAN ,  BURD STEVEN WAYNE ,  JONES CHRISTOPHER DALE ,  KRAMER STEVEN K ,  KOGSTROM CHRISTOPHER L ,  NAPOLI NICOLAOS ,  BOND BRUCE

    IPC: C04B35/80 ,  F01D5/18 ,  C04B38/06 ,  F01D5/28 ,  F01D9/02 ,  F02C7/00

    Abstract: A ceramic matrix composite part having elongated cooling channels within the wall thereof is manufactured by inserting decomposable inserts within a woven ceramic fiber preform. The inserts are tows of continuous carbon fibers surrounded by a carbonaceous filler, and are inserted where the channels are desired. The preform, with the inserts in place, is disposed within a mold. A ceramic matrix material is added and the fiber preform is consolidated with the ceramic matrix material. The consolidated part is then heated to thermally decompose the inserts to create the elongated channels within the part. The inserts may be flexible and woven into the preform using an automated weaving loom, or they may have limited flexibility and be inserted by machine or by hand.

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