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    Float wall combustor panels having heat transfer augmentation
    21.
    发明公开
    Float wall combustor panels having heat transfer augmentation 审中-公开

    公开(公告)号：EP3453970A3

    公开(公告)日：2019-03-20

    申请号：EP18192983.7

    申请日：2018-09-06

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  AUXIER, James Tilsley

    IPC: F23R3/00 ,  F23M5/08 ,  F28F3/02

    Abstract: Combustor panels (126, 128) for use in gas turbine engines having a panel body (136) having a first side (138) and a second side (137), and a plurality of cooling pins (140) extending from the first side, the plurality of cooling pins arranged in a pin array pattern, wherein at least some of the cooling pins extend a first height (H 1 ) from the first side of the panel body, each cooling pin having a pin width, and is separated from adjacent cooling pins of the pin array by a pin array separation distance (S 0 ). The pin array separation distance is equal to or greater than the pin width.

    Float wall combustor panels having heat transfer augmentation
    22.
    发明公开
    Float wall combustor panels having heat transfer augmentation 审中-公开

    公开(公告)号：EP3453970A2

    公开(公告)日：2019-03-13

    申请号：EP18192983.7

    申请日：2018-09-06

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  AUXIER, James Tilsley

    IPC: F23R3/00 ,  F23M5/08 ,  F28F3/02

    Abstract: Combustor panels (126, 128) for use in gas turbine engines having a panel body (136) having a first side (138) and a second side (137), and a plurality of cooling pins (140) extending from the first side, the plurality of cooling pins arranged in a pin array pattern, wherein at least some of the cooling pins extend a first height (H 1 ) from the first side of the panel body, each cooling pin having a pin width, and is separated from adjacent cooling pins of the pin array by a pin array separation distance (S 0 ). The pin array separation distance is equal to or greater than the pin width.

    TOOTHED COMPONENT OPTIMIZATION FOR GAS TURBINE ENGINE
    23.
    发明公开
    TOOTHED COMPONENT OPTIMIZATION FOR GAS TURBINE ENGINE 审中-公开
    气体涡轮发动机的齿形构件优化

    公开(公告)号：EP3246515A1

    公开(公告)日：2017-11-22

    申请号：EP17171142.7

    申请日：2017-05-15

    Applicant: United Technologies Corporation

    Inventor： MARIANO, Thomas A. ,  PORTER, Steven D.

    IPC: F01D5/02 ,  F01D5/06 ,  F01D5/14

    CPC classification number: F01D5/025 ,  F01D5/02 ,  F01D5/026 ,  F01D5/06 ,  F01D5/066 ,  F01D5/14 ,  F01D9/02 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2260/50

    Abstract: Methods of manufacturing toothed components for gas turbine engines are provided. The methods include forming a first tooth in the component with a top land, a bottom land, a side wall extending therebetween, and a fillet radius transitioning between the side wall and the bottom land, forming a second tooth in the component adjacent the first tooth, the second tooth having a top land, a bottom land, a side wall extending therebetween and facing the first tooth, and a fillet radius transitioning between the side wall and the bottom land, the bottom land of the second tooth extending toward the bottom land of the first tooth, wherein the bottom lands define a gable area of the component, and forming a stress relief feature in the gable area such that the stress relief feature reduces a stress concentration near the gable area during operation of the toothed component.

    Abstract translation: 提供了用于燃气涡轮发动机的齿形部件的制造方法。 所述方法包括在部件中形成具有顶部平台，底部平台，在其间延伸的侧壁以及在侧壁和底部平台之间过渡的圆角半径的第一齿，在邻近第一齿的部件中形成第二齿 ，第二齿具有顶部刃带，底部刃带，在它们之间延伸并面向第一齿的侧壁以及在侧壁和底部刃带之间过渡的圆角半径，第二齿的底部刃带朝向底部刃带延伸 其中所述底部刃带限定所述部件的山墙区域，并且在所述山墙区域中形成应力消除特征，使得所述应力消除特征在所述齿形部件的操作期间降低所述山墙区域附近的应力集中。

    MINI-DISK FOR GAS TURBINE ENGINE
    24.
    发明公开
    MINI-DISK FOR GAS TURBINE ENGINE 审中-公开
    迷你盘用于燃气轮机发动机

    公开(公告)号：EP3192968A1

    公开(公告)日：2017-07-19

    申请号：EP17151853.3

    申请日：2017-01-17

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  PARTYKA, Julian

    IPC: F01D5/08

    CPC classification number: F01D5/081 ,  F01D5/082 ,  F05D2230/642 ,  F05D2260/941 ,  Y02T50/676

    Abstract: According to one embodiment, a mini-disk (314) of a gas turbine engine having an axis is provided. The mini-disk includes a bore (320), a web (322) extending radially with respect to the axis of the gas turbine engine from the bore, a base (324) extending axially with respect to the axis of the gas turbine engine from the bore, a connector (331) located on an end of the base, the connector configured to connect with a hub arm (334a; 334b) of the gas turbine engine, and an expansion feature (346) configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.

    Abstract translation: 根据一个实施例，提供了一种具有轴线的燃气涡轮发动机的小型盘（314）。 微型盘包括孔（320），相对于燃气涡轮发动机的轴线从孔径向延伸的腹板（322），相对于燃气涡轮发动机的轴线轴向延伸的基部（324）， 所述孔，位于所述基部的端部上的连接器（331），所述连接器构造成与所述燃气涡轮发动机的毂臂（334a; 334b）连接，以及膨胀特征部（346），所述膨胀特征部配置在所述基部中并位于 所述孔和所述连接器，所述扩张特征被构造成减小所述基部的轴向刚度。

    TIE ROD FOR A MID-TURBINE FRAME
    26.
    发明公开
    TIE ROD FOR A MID-TURBINE FRAME 审中-公开
    ZUGSTREBEFÜREINEN MITTELTURBINENRAHMEN

    公开(公告)号：EP3045682A1

    公开(公告)日：2016-07-20

    申请号：EP16151125.8

    申请日：2016-01-13

    Applicant: United Technologies Corporation

    Inventor： FARAH, Jorge I. ,  PORTER, Steven D. ,  SANCHEZ, Paul K. ,  SEDOR, Joseph J.

    IPC: F01D25/16 ,  F01D9/06 ,  F02C7/20

    Abstract: A mid-turbine frame (57) for a gas turbine engine (20) includes an inner frame case (64) that includes a bolt opening (156) and at least one spoke (65) for connecting an outer frame case (62) to the inner frame case (64) that includes an inlet passage (118) that extends in a radial direction. A central bolt (112) extends through the bolt opening (156) for securing at least one spoke (65) to the inner frame case (64).

    Abstract translation: 用于燃气涡轮发动机（20）的中涡轮机架（57）包括内框架壳体（64），其包括螺栓开口（156）和至少一个辐条（65），用于将外框架壳体（62）连接到 内框架壳体（64）包括沿径向延伸的入口通道（118）。 中心螺栓（112）延伸穿过螺栓孔（156），用于将至少一个轮辐（65）固定到内框架壳体（64）上。

    HARDWARE GEOMETRY FOR INCREASING PART OVERLAP AND MAINTAINING CLEARANCE
    27.
    发明公开
    HARDWARE GEOMETRY FOR INCREASING PART OVERLAP AND MAINTAINING CLEARANCE 审中-公开
    五金 - 几何设计祖尔·德霍尔德·德尔·德尔伯勒

    公开(公告)号：EP3037627A1

    公开(公告)日：2016-06-29

    申请号：EP15201381.9

    申请日：2015-12-18

    Applicant: United Technologies Corporation

    Inventor： PORTER, Steven D. ,  OLS, John T. ,  LANA, Kyle C.

    IPC: F01D11/00 ,  F01D5/08

    CPC classification number: F01D9/02 ,  F01D1/04 ,  F01D5/081 ,  F01D11/001 ,  F05D2240/80 ,  Y02T50/676

    Abstract: A gas-turbine engine (20) is provided. The gas-turbine engine (20) comprises a high pressure turbine (54) with an aft blade platform (106). A static structure may be disposed aft of the high pressure turbine (54) and proximate a cavity (104) defined by the aft blade platform (106). A vane of the static structure may have a vane platform (102) with a shaped tip (126; 200; 202; 204) extending into the cavity (104).

    Abstract translation: 提供一种燃气涡轮发动机（20）。 燃气涡轮发动机（20）包括具有后叶片平台（106）的高压涡轮机（54）。 静态结构可以设置在高压涡轮机（54）的后方并靠近由后叶片平台（106）限定的空腔（104）。 静态结构的叶片可以具有叶片平台（102），其具有延伸到空腔（104）中的成形尖端（126; 200; 202; 204）。

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