中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

120 records (took 0.02 seconds)

    Tip leakage flow directionality control
    21.
    发明授权
    Tip leakage flow directionality control 有权

    公开(公告)号：US10815790B2

    公开(公告)日：2020-10-27

    申请号：US15918190

    申请日：2018-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark F. Zelesky ,  Andrew S. Aggarwala

    IPC: F01D5/18 ,  F01D11/10 ,  F01D5/14 ,  F01D5/20

    Abstract: An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.

    Tip leakage flow directionality control
    22.
    发明授权
    Tip leakage flow directionality control 有权

    公开(公告)号：US10774659B2

    公开(公告)日：2020-09-15

    申请号：US15918246

    申请日：2018-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Mark F. Zelesky ,  Andrew S. Aggarwala

    IPC: F01D5/20 ,  F01D9/02 ,  F01D25/12 ,  F01D11/08

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.

    Combustor panel cooling arrangements
    23.
    发明授权
    Combustor panel cooling arrangements 有权

    公开(公告)号：US10731855B2

    公开(公告)日：2020-08-04

    申请号：US15683965

    申请日：2017-08-23

    Applicant: United Technologies Corporation

    Inventor： Mark F. Zelesky ,  Carey Clum

    IPC: F23R3/00 ,  F23R3/06 ,  F23R3/26 ,  F02C7/12

    Abstract: Combustors and panels for use in combustor sections of gas turbine engines, the panels having a panel body having a first wall with a first sidewall and a second sidewall extending each extending from the first wall in the same direction at edges of the first wall and a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall, wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall.

    COMBUSTOR PANEL COOLING ARRANGEMENTS
    27.
    发明申请
    COMBUSTOR PANEL COOLING ARRANGEMENTS 审中-公开

    公开(公告)号：US20190063749A1

    公开(公告)日：2019-02-28

    申请号：US15683965

    申请日：2017-08-23

    Applicant: United Technologies Corporation

    Inventor： Mark F. Zelesky ,  Carey Clum

    IPC: F23R3/00 ,  F23R3/06 ,  F23R3/26 ,  F02C7/12

    CPC classification number: F23R3/002 ,  F02C7/12 ,  F23R3/06 ,  F23R3/26 ,  F23R2900/03042

    Abstract: Combustors and panels for use in combustor sections of gas turbine engines, the panels having a panel body having a first wall with a first sidewall and a second sidewall extending each extending from the first wall in the same direction at edges of the first wall and a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall, wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall.

    TIP CLEARANCE CONTROL FOR GAS TURBINE ENGINE
    29.
    发明申请
    TIP CLEARANCE CONTROL FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180320542A1

    公开(公告)日：2018-11-08

    申请号：US15589009

    申请日：2017-05-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Mark F. Zelesky ,  Ioannis Alvanos ,  Brian Merry

    IPC: F01D11/24

    Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.

Patent Agency Ranking