中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

45 records (took 0.019 seconds)

    GAS TURBINE ENGINE AIRFOIL
    11.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开

    公开(公告)号：US20170184119A1

    公开(公告)日：2017-06-29

    申请号：US15460333

    申请日：2017-03-16

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F04D29/38 ,  F02K3/06 ,  F04D29/32 ,  F02C3/04

    Abstract: A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0° view. The various views include the 0° view which projects into an axial plane in the axial direction. A 90° view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0° and 90° views. The airfoil has a maximum leading edge projection in a 20° to 40° view. The radial direction is normal to the axial and tangential directions.

    Gas turbine engine airfoil
    12.
    发明授权
    Gas turbine engine airfoil 有权
    燃气涡轮发动机翼型

    公开(公告)号：US09163517B2

    公开(公告)日：2015-10-20

    申请号：US14625413

    申请日：2015-02-18

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F01D5/14 ,  F02K3/00

    CPC classification number: F01D5/141 ,  F02C3/107 ,  F02K3/00 ,  F02K3/06 ,  F04D29/384 ,  F05D2200/222 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/301 ,  F05D2250/713 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope crosses an initial axial stacking offset that corresponds to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is between 1.5 and 2.0 or less than 1.4.

    Abstract translation: 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型件具有层叠偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。 正斜率跨过与零交叉位置处的0％跨度位置相对应的初始轴向堆积偏移。 第一轴向堆叠偏移X1从过零位置提供到曲线上的负最大值。 第二轴向堆叠偏移X2从过零点提供到曲线上的最大值。 第二轴向叠置偏移X2 / X1之间的比率在1.5至2.0或小于1.4之间。

    GAS TURBINE ENGINE AIRFOIL
    16.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开
    气体涡轮发动机气翼

    公开(公告)号：US20170023004A1

    公开(公告)日：2017-01-26

    申请号：US15113470

    申请日：2014-08-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F04D29/38 ,  F02K3/06 ,  F04D29/32 ,  F02C3/04 ,  F02C7/36

    CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/324 ,  F04D29/325 ,  F04D29/386 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/314 ,  Y02T50/672 ,  Y02T50/673

    Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE−Yd)/(Yd−YTE) at 40% span position is about 1.5 and (YLE−Yd)/(Yd−YTE) at 20% span position is about 2.

    Abstract translation: 在一个示例性实施例中，用于涡轮发动机的翼型件包括沿径向从在内部流动路径位置处的0％跨度位置延伸到在翼型末端处的100％跨度位置的压力和吸力侧。 翼型几何对应于切向前缘和后缘曲线以及切向堆积偏移曲线。 翼型从根部延伸。 零切向参考点对应于根的切线中心。 YLE对应于在给定跨度位置处从前缘到参考点的切向距离。 YTE对应于在给定跨度位置处从后缘到参考点的切线距离。 Yd对应于给定跨度位置处的切向堆积偏移。 （YLE-YD）/（YD-YTE）在40％跨度位置约为1.5，（YLE-Yd）/（Yd-YTE）在20％跨度位置约为2。

    GAS TURBINE ENGINE AIRFOIL
    19.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 有权
    气体涡轮发动机气翼

    公开(公告)号：US20160024929A1

    公开(公告)日：2016-01-28

    申请号：US14876995

    申请日：2015-10-07

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F01D5/14 ,  F01D5/145 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

    Abstract translation: 用于涡轮发动机的翼型件包括具有压力和吸力侧的翼型件，所述翼型件在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型顶端处的100％跨度位置。 翼型件具有前缘二面体和跨度位置之间的关系。 前缘二面体从0％跨度位置到100％跨度位置为负。 正二面对应于吸力侧倾，负二面对应于压力侧倾。 翼型件是用于燃气轮机的风扇叶片。 翼型件具有后缘二面体和跨度位置之间的关系。 后缘二面体从0％跨度位置到100％跨度位置为正。 正二面对应于吸力侧倾，负二面对应于压力侧倾。

    GAS TURBINE ENGINE AIRFOIL
    20.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 审中-公开
    气体涡轮发动机气翼

    公开(公告)号：US20150361797A1

    公开(公告)日：2015-12-17

    申请号：US14837183

    申请日：2015-08-27

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

    IPC: F01D5/14 ,  F02C3/107

    CPC classification number: F01D5/141 ,  F02C3/107 ,  F02K3/00 ,  F02K3/06 ,  F04D29/384 ,  F05D2200/222 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/301 ,  F05D2250/713 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.

    Abstract translation: 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型件具有层叠偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。 正斜坡向后倾斜，负斜坡相对于发动机轴向前倾斜。 正斜率跨过与过零位置的0％跨度位置对应的初始轴向堆积偏移。 第一轴向堆叠偏移X1从过零位置提供到曲线上的负最大值。 第二轴向堆叠偏移X2从过零点提供到曲线上的最大值。 第二轴向叠置偏移量X2 / X1的比率小于2.0。

Patent Agency Ranking