中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

54 records (took 0.021 seconds)

    Cooling flow for leading panel in a gas turbine engine combustor
    12.
    发明授权
    Cooling flow for leading panel in a gas turbine engine combustor 有权

    公开(公告)号：US10344979B2

    公开(公告)日：2019-07-09

    申请号：US15108107

    申请日：2015-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frank J. Cunha ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F23R3/00 ,  F02C3/14 ,  F23M5/08 ,  F23R3/14 ,  F23R3/58

    Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.

    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
    13.
    发明申请
    CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR 审中-公开
    燃气轮机发动机燃油通风的CO-SWIRL方向

    公开(公告)号：US20160281988A1

    公开(公告)日：2016-09-29

    申请号：US15037484

    申请日：2014-12-03

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： John S. Tu, JR. ,  Timothy S. Snyder ,  James B. Hoke ,  James P. Bangerter ,  Dennis J. Duhamel ,  David A. Burns

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

    Abstract translation: 用于燃气涡轮发动机的燃烧器中的衬板包括一个包括多个喷射通道的前部区域，每个喷射通道以与燃烧气体的局部涡流方向一致的方向指向。 用于燃气涡轮发动机的燃烧器中的另一衬里面板包括稀释通道前方的前部区域和前部区域的尾部后部区域。 前部区域包括多个通常沿周向引导的排出通道。 后部区域包括多个通过轴向大体定向的排出通道。 一种冷却燃气涡轮发动机的燃烧器内的壁组件的方法包括在与燃烧气体的局部涡流方向一致的前向区域内定向多个排出通道。

    HYBRID THROUGH HOLES AND ANGLED HOLES FOR COMBUSTOR GROMMET COOLING
    14.
    发明申请
    HYBRID THROUGH HOLES AND ANGLED HOLES FOR COMBUSTOR GROMMET COOLING 审中-公开
    通过螺栓和螺栓固定用于燃烧器冷却

    公开(公告)号：US20160201913A1

    公开(公告)日：2016-07-14

    申请号：US14886973

    申请日：2015-10-19

    Applicant: United Technologies Corporation

    Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

    IPC: F23R3/06 ,  F23R3/00

    CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

    Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。

    High shear swirler with recessed fuel filmer for a gas turbine engine
    15.
    发明授权
    High shear swirler with recessed fuel filmer for a gas turbine engine 有权

    公开(公告)号：US11378275B2

    公开(公告)日：2022-07-05

    申请号：US16705547

    申请日：2019-12-06

    Applicant: United Technologies Corporation

    Inventor： Justin M. Locke ,  Timothy S. Snyder ,  William Proscia

    IPC: F23R3/28 ,  F23R3/14 ,  F23R3/30

    Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

    HIGH SHEAR SWIRLER WITH RECESSED FUEL FILMER
    17.
    发明申请
    HIGH SHEAR SWIRLER WITH RECESSED FUEL FILMER 有权

    公开(公告)号：US20210172604A1

    公开(公告)日：2021-06-10

    申请号：US16705547

    申请日：2019-12-06

    Applicant: United Technologies Corporation

    Inventor： Justin M. Locke ,  Timothy S. Snyder ,  William Proscia

    IPC: F23R3/14 ,  F23R3/28

    Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

    Combustor having a beveled grommet
    18.
    发明授权
    Combustor having a beveled grommet 有权

    公开(公告)号：US10753613B2

    公开(公告)日：2020-08-25

    申请号：US15172194

    申请日：2016-06-03

    Applicant: United Technologies Corporation

    Inventor： Crisen McKenzie ,  Timothy S. Snyder

    IPC: F23R3/06 ,  F23R3/50 ,  F23R3/00 ,  F02C3/04

    Abstract: A combustor includes a shell that at least partially defines a combustion chamber and a grommet mounted in the shell. The grommet has a body that defines a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber. The body carries a first surface, an opposite, second surface and a third surface that defines the passage and joins the first surface and the second surface. The third surface includes a bevel surface with respect to at least one of the first surface and the second surface.

Patent Agency Ranking