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    11.
    发明专利
    未知

    公开(公告)号：DE602004026820D1

    公开(公告)日：2010-06-10

    申请号：DE602004026820

    申请日：2004-10-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： OTERO EDWIN ,  STRONG PATRICK

    IPC: B22C9/10 ,  F01D5/08 ,  B22C9/04 ,  B22C9/24 ,  F01D5/18 ,  F01D9/02 ,  F01D25/00 ,  F02C7/00

    Abstract: A core (32) for casting a metal part having a body with solid portions (34) spaced apart by hollow portions (36). The body includes at least one support element (38) extending between adjacent solid portions. The support element provides stiffness and strength for the casting core during the casting process. The support element has an optimized shape to prevent the core from fracturing during the casting process and to minimize operating stress in the metal part around the area formed by the support element.

    12.
    发明专利
    未知

    公开(公告)号：NO20050623L

    公开(公告)日：2005-08-05

    申请号：NO20050623

    申请日：2005-02-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND ,  GREGG SHAWN J ,  PROPHETER TRACY ,  OTERO EDWIN

    IPC: F01D5/10 ,  F01D5/18 ,  F01D25/06 ,  F01D5/16 ,  F01D5/12 ,  F01D5/00

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

    TURBINE BLADE DAMPER SEAL
    14.
    发明公开
    TURBINE BLADE DAMPER SEAL 审中-公开
    DÄMPFUNGSDICHTUNGFÜREINE TURBINENSCHAUFEL

    公开(公告)号：EP2836682A4

    公开(公告)日：2016-06-01

    申请号：EP13775907

    申请日：2013-01-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNYDER DANIEL A ,  LANA KYLE CHARLES ,  SANDOVAL JONATHAN PERRY ,  VIRKLER SCOTT DANIEL ,  TARASKEVICH JAIMIE ,  OTERO EDWIN

    IPC: F01D5/26 ,  F01D5/22 ,  F01D5/30 ,  F01D11/00

    CPC classification number: F01D5/22 ,  F01D5/3007 ,  F01D11/006 ,  Y02T50/673

    Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

    Abstract translation: 根据本公开的示例性方面，容纳在位于平台和保持架阻尼器密封件之间的涡轮叶片的空腔中的阻尼器密封件包括中心主体部分，其具有第一端部区域，相对的第二端部 区域和宽度。 阻尼器密封件还包括从中心主体部分的第一端部区域延伸的第一部分，并且第一部分的第一端部区域包括第一向外延伸的突出部，其限定第一扩大部分，第一扩大部分具有大于 中心主体部分和从中心主体部分的相对的第二端部区域延伸的第二部分。

    GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT
    19.
    发明公开
    GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT 审中-公开
    汽轮机摩托车的冷却回路

    公开(公告)号：EP2900961A4

    公开(公告)日：2016-07-27

    申请号：EP13840873

    申请日：2013-09-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  ZELESKY MARK F ,  OTERO EDWIN

    IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

    CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that extends between a leading edge, a trailing edge, a pressure side wall and a suction side wall. A cooling circuit is disposed inside of the airfoil. The cooling circuit includes a first core cavity that radially extends inside of the airfoil. A first axial skin core is in fluid communication with the first core cavity at a first location of the first axial skin core and a second core cavity is in fluid communication with the first axial skin core at a second location of the first axial skin core.

    Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘，后缘，压力侧壁和吸力侧壁之间延伸的翼型件。 冷却回路设置在翼型的内部。 冷却回路包括在翼型件内径向延伸的第一芯腔。 第一轴向皮肤芯在第一轴向皮肤芯的第一位置处与第一芯腔流体连通，并且第二芯腔在第一轴向皮肤芯的第二位置处与第一轴向皮肤皮肤流体连通。

    AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS
    20.
    发明公开
    AIRFOIL WITH IMPROVED INTERNAL COOLING CHANNEL PEDESTALS 有权
    改进了内部冷却通道底座的铲斗

    公开(公告)号：EP2823151A4

    公开(公告)日：2015-06-03

    申请号：EP13757299

    申请日：2013-02-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： OTERO EDWIN

    IPC: F01D5/18 ,  F01D25/10 ,  F02C7/00 ,  F02C7/12

    CPC classification number: F01D5/187 ,  F01D5/188 ,  F05D2240/304 ,  F05D2250/14 ,  F05D2250/231 ,  F05D2260/202 ,  F05D2260/2214

    Abstract: An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.

    Abstract translation: 一种用于涡轮发动机的翼型件，所述翼型件包括第一侧壁，与所述第一侧壁间隔开的第二侧壁，以及形成在所述第一侧壁和所述第二侧壁之间的内部冷却通道。 内部冷却通道包括具有连接到第一侧壁的第一基座端和连接到第二侧壁的第二基座端的至少一个基座。 内部冷却通道还包括在第一侧壁和第一基座端之间围绕第一基座端的周边布置的第一圆角; 以及在所述第二侧壁和所述第二基座端之间围绕所述第二基座端部的周边设置的第二圆角。 第一圆角和第二圆角中的至少一个包括围绕相应基座端的周边不均匀的轮廓。

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