中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

120 records (took 0.028 seconds)

    Advanced braze joint for tube-to-tube connection
    43.
    发明授权
    Advanced braze joint for tube-to-tube connection 有权

    公开(公告)号：US10139023B2

    公开(公告)日：2018-11-27

    申请号：US14992646

    申请日：2016-01-11

    Applicant: United Technologies Corporation

    Inventor： Thomas N. Slavens ,  Carey Clum

    IPC: F01D9/06 ,  F16L13/02 ,  B23K1/00 ,  B23K1/19 ,  F02C3/04 ,  B23K33/00 ,  B23K1/18 ,  B23K101/06 ,  B23K103/04 ,  B23K103/08 ,  B23K101/00

    Abstract: Systems for tube-to-tube connections are described herein. A device having an aperture for receiving a tube may comprise: an inlet portion comprising a first diameter, the inlet portion located at an inlet of the aperture; a braze filler collector portion located axially adjacent to the inlet portion comprising a second diameter, the second diameter being greater than the first diameter; a necked portion located axially adjacent to the braze filler collector portion comprising a third diameter, the third diameter being less than the first diameter and the second diameter; a flow surface comprising a fourth diameter, the fourth diameter being less than the third diameter, the flow surface defining a void; and a collection pocket located axially adjacent to the necked portion, the collection pocket configured to collect a braze filler material from the necked portion to prevent the braze filler material from contacting the flow surface.

    TRAILING EDGE PRESSURE AND FLOW REGULATOR
    44.
    发明申请
    TRAILING EDGE PRESSURE AND FLOW REGULATOR 审中-公开

    公开(公告)号：US20180209286A1

    公开(公告)日：2018-07-26

    申请号：US15416394

    申请日：2017-01-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler ,  Carey Clum ,  Matthew A. Devore

    IPC: F01D9/06 ,  F02C3/04 ,  F02C7/12

    CPC classification number: F01D9/065 ,  F01D5/187 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

    Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.

    Film cooling hole arrangement for gas turbine engine component
    47.
    发明授权
    Film cooling hole arrangement for gas turbine engine component 有权

    公开(公告)号：US11408302B2

    公开(公告)日：2022-08-09

    申请号：US15783318

    申请日：2017-10-13

    Applicant: United Technologies Corporation

    Inventor： Carey Clum ,  Dominic J. Mongillo, Jr.

    IPC: F01D25/12 ,  F01D5/18 ,  F01D9/06 ,  F01D9/04

    Abstract: A component for a gas turbine engine includes an outer surface bounding a hot gas path of the gas turbine engine, and a cooling passage configured to deliver a cooling airflow therethrough. The cooling passage includes a passage wall located opposite the outer surface to define a component thickness and a plurality of protrusions located along the passage wall. Each protrusion has a protrusion height extending from the passage wall and a protrusion streamwise width extending along the passage wall in a flow direction of the cooling airflow through the cooling passage. One or more cooling holes extend from the passage wall to the outer surface. A cooling hole inlet of a cooling hole is located at the passage wall, in a protrusion wake region downstream of a protrusion of the plurality of protrusions.

    Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
    48.
    发明授权
    Apparatus and method for mitigating particulate accumulation on a component of a gas turbine 有权

    公开(公告)号：US11371703B2

    公开(公告)日：2022-06-28

    申请号：US16239911

    申请日：2019-01-04

    Applicant: United Technologies Corporation

    Inventor： Dennis M. Moura ,  Carey Clum

    IPC: F23R3/08 ,  F23R3/00 ,  F01D5/18 ,  F01D25/32 ,  F23R3/04

    Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

    Coriolis optimized U-channel with root flag
    49.
    发明授权
    Coriolis optimized U-channel with root flag 有权

    公开(公告)号：US11015454B2

    公开(公告)日：2021-05-25

    申请号：US15967950

    申请日：2018-05-01

    Applicant: United Technologies Corporation

    Inventor： Timothy J. Jennings ,  Carey Clum

    IPC: F01D5/18

    Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source radially inward of the platform. The second passage is configured to receive cooling air from the first passage near the tip. A root flag passage is configured to purge the cooling air from the second passage near the trailing edge.

    AIRFOIL HAVING IMPINGEMENT LEADING EDGE
    50.
    发明申请
    AIRFOIL HAVING IMPINGEMENT LEADING EDGE 有权

    公开(公告)号：US20210079793A1

    公开(公告)日：2021-03-18

    申请号：US16552450

    申请日：2019-08-27

    Applicant: United Technologies Corporation

    Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

    IPC: F01D5/18 ,  F01D5/14

    Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.

Patent Agency Ranking