中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

14 records (took 0.023 seconds)

    COUNTER ROTATING LOW PRESSURE COMPRESSOR AND TURBINE EACH HAVING A GEAR SYSTEM
    2.
    发明申请
    COUNTER ROTATING LOW PRESSURE COMPRESSOR AND TURBINE EACH HAVING A GEAR SYSTEM 审中-公开
    逆向压缩机和涡轮机，具有齿轮系统

    公开(公告)号：WO2013187944A2

    公开(公告)日：2013-12-19

    申请号：PCT/US2013/027550

    申请日：2013-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel, L. ,  MERRY, Brian, D.

    IPC: F02C3/067 ,  F02K3/072

    CPC classification number: F02K3/072 ,  F02C3/113 ,  F02C7/36 ,  F05D2250/36 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A compressor section includes a counter rotating low pressure compressor that includes outer and inner compressor blades interspersed with one another and are configured to rotate in an opposite direction than one another about an axis of rotation. A transmission couples at least one of the outer and inner compressor blades to a shaft. A turbine section includes a counter rotating low pressure turbine having an outer rotor that includes an outer set of turbine blades. An inner rotor has an inner set of turbine blades interspersed with the outer set of turbine blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples at least one of the outer and inner rotors to the shaft.

    Abstract translation: 压缩机部分包括反向旋转的低压压缩机，该压缩机包括彼此分散的外部和内部压缩机叶片，并且构造成围绕旋转轴线沿彼此相反的方向旋转。 A变速器将外压缩机叶片和内压缩机叶片中的至少一个联接到轴。 涡轮部分包括具有包括外部涡轮叶片组的外转子的反转旋转低压涡轮机。 内转子具有与外部涡轮叶片组分布的内部涡轮叶片组。 外转子构造成围绕与内转子的旋转轴线相反的方向旋转。 齿轮系将至少一个外转子和内转子连接到轴上。

    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO MID TURBINE FRAME
    3.
    发明申请
    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO MID TURBINE FRAME 审中-公开
    具有安装在中间涡轮机框架上的齿轮系统的逆转低压涡轮机

    公开(公告)号：WO2013172905A2

    公开(公告)日：2013-11-21

    申请号：PCT/US2013/027549

    申请日：2013-02-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel, L. ,  MERRY, Brian, D.

    IPC: F02K3/072 ,  F02K3/00 ,  F02C7/00 ,  F01D25/14

    CPC classification number: F02C3/107 ,  F01D1/26 ,  F01D25/162 ,  F02C3/067 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2250/36 ,  F05D2250/44 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. The gear system is mounted to a mid-turbine frame.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴。 外涡轮转子直接驱动轴并且包括外部一组叶片。 内部涡轮转子具有与外部组叶片交替散布的内部一组叶片。 内涡轮转子被构造成围绕与外涡轮转子的旋转轴线相反的方向旋转。 齿轮系将内涡轮转子与轴连接，并且构造成以比外套叶片更快的速度旋转内组叶片。 齿轮系统安装到中涡轮机架。

    INTEGRATED INLET VANE AND STRUT
    4.
    发明申请
    INTEGRATED INLET VANE AND STRUT 审中-公开
    集成的入口和输入

    公开(公告)号：WO2014011246A2

    公开(公告)日：2014-01-16

    申请号：PCT/US2013/033241

    申请日：2013-03-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel, L. ,  MERRY, Brian, D. ,  BRILLIANT, Lisa, I.

    CPC classification number: F01D1/04 ,  F01D9/02

    Abstract: A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.

    Abstract translation: 燃气涡轮发动机壳体结构包括彼此径向间隔开的内部和外部环形壳体部分，以提供流动路径，并且周向布置的翼型件径向延伸并且互连内部和外部环形壳体部分。 翼型件包括多个叶片和多个支柱叶片。 每个叶片都有一个叶片前缘。 每个支柱叶片包括支柱叶片前缘。 叶片前缘和支柱叶片前缘在公共平面对齐。 叶片包括第一轴向长度，支柱叶片包括至少是第一轴向长度的两倍的第二轴向长度。

    TURBINE ENGINE CASE MOUNT
    6.
    发明申请
    TURBINE ENGINE CASE MOUNT 审中-公开
    涡轮发动机壳体安装

    公开(公告)号：WO2013138103A1

    公开(公告)日：2013-09-19

    申请号：PCT/US2013/029000

    申请日：2013-03-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel, L. ,  ALVANOS, Ioannis ,  MERRY, Brian, D.

    IPC: F02K3/00 ,  F02K99/00 ,  B64C1/00

    CPC classification number: B64D27/26 ,  Y02T50/44

    Abstract: A mount for a turbine engine has a semi-circular yoke with a first leg and a second leg. The mount also has a stanchion with a cylindrical section attached to the yoke, and a conical section attached to the cylindrical section. A mounting bracket is attached to the conical section.

    Abstract translation: 用于涡轮发动机的安装座具有带有第一腿和第二腿的半圆形轭。 安装座还具有支柱，其具有附接到轭的圆柱形部分，以及附接到圆柱形部分的锥形部分。 安装支架连接到锥形部分。

Patent Agency Ranking