中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

100 records (took 0.029 seconds)

    TURBINE VANE WITH VARIABLE TRAILING EDGE INNER RADIUS
    51.
    发明申请
    TURBINE VANE WITH VARIABLE TRAILING EDGE INNER RADIUS 审中-公开
    涡轮风扇与可变轨迹边缘内径半径

    公开(公告)号：US20160069197A1

    公开(公告)日：2016-03-10

    申请号：US14787490

    申请日：2014-05-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven D. Porter ,  John T. Ols

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F01D5/141 ,  F01D5/18 ,  F01D9/047 ,  F01D25/162 ,  F05D2240/122 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A turbine vane has an airfoil extending between an inner platform and an outer platform. The airfoil is hollow. A hollow within the airfoil extends between an inner leading edge to an inner trailing edge. An inner radius is defined at the inner trailing edge in a circumferential direction measured between walls which extend from the inner leading edge to the inner trailing edge. The inner radius varies along a radial length defined between the inner and outer platforms. A mid-turbine frame and a gas turbine engine are also disclosed.

    Abstract translation: 涡轮叶片具有在内平台和外平台之间延伸的翼型件。 翼型是空心的。 翼型内的中空部分在内前缘到内后缘之间延伸。 在从内部前缘延伸到内部后缘的壁之间测量的在圆周方向上的内部后缘处限定内部半径。 内半径沿着内平台和外平台之间限定的径向长度而变化。 还公开了中涡轮机架和燃气涡轮发动机。

    COMBUSTOR TO VANE SEALING ASSEMBLY AND METHOD OF FORMING SAME
    52.
    发明申请
    COMBUSTOR TO VANE SEALING ASSEMBLY AND METHOD OF FORMING SAME 有权

    公开(公告)号：US20210222878A1

    公开(公告)日：2021-07-22

    申请号：US16746210

    申请日：2020-01-17

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Caroline Karanian ,  John T. Ols

    IPC: F23R3/00

    Abstract: A gas turbine engine includes a turbine section including a first vane stage. The gas turbine engine further includes a combustor disposed forward of the first vane stage. The combustor includes a combustion chamber in fluid communication with the first vane stage. The combustion chamber is radially defined between a first shell and a second shell. The first shell includes a first seal assembly at an aft end of the first shell. The first seal assembly includes a conformal seal forming a first seal between the first shell and a forward face of the first vane stage. The second shell includes a second seal assembly at an aft end of the second shell. The second seal assembly includes a brush seal forming a second seal between the second shell and the forward face of the first vane stage.

    Mini-disk for gas turbine engine
    57.
    发明授权
    Mini-disk for gas turbine engine 有权

    公开(公告)号：US10655480B2

    公开(公告)日：2020-05-19

    申请号：US14997864

    申请日：2016-01-18

    Applicant: United Technologies Corporation

    Inventor： Steven D. Porter ,  Julian Partyka

    IPC: F01D5/08 ,  F01D11/00 ,  F01D5/30 ,  F01D5/06

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

    Toothed component optimization for gas turbine engine
    58.
    发明授权
    Toothed component optimization for gas turbine engine 有权

    公开(公告)号：US10584590B2

    公开(公告)日：2020-03-10

    申请号：US15155242

    申请日：2016-05-16

    Applicant: United Technologies Corporation

    Inventor： Thomas A. Mariano ,  Steven D. Porter

    IPC: B25G3/28 ,  F01D5/02 ,  F01D5/06 ,  F01D5/14 ,  F01D9/02 ,  F02C3/04 ,  F02C7/18

    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.

Patent Agency Ranking