中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

52 records (took 0.016 seconds)

    GAS TURBINE ENGINE AIRFOIL
    13.
    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：US20160298643A1

    公开(公告)日：2016-10-13

    申请号：US15191860

    申请日：2016-06-24

    Applicant: United Technologies Corporation

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

    IPC: F04D29/38 ,  F04D29/32

    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 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
    14.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 有权
    气体涡轮发动机气翼

    公开(公告)号：US20150354362A1

    公开(公告)日：2015-12-10

    申请号：US14624240

    申请日：2015-02-17

    Applicant: United Technologies Corporation

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

    IPC: F01D5/14 ,  F02C3/04

    CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C3/14 ,  F02C7/36 ,  F02K3/04 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/4031 ,  F05D2270/3013 ,  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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).

    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。 翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨度位置到第一峰具有增加的总弦长的曲线。 第一个峰出现在45-65％跨度位置的范围内，并且该曲线或者保持一般恒定或具有从第一峰到100％跨度位置的总弦长减小。 总和弦长度在8.2-10.5英寸（20.8-26.7厘米）范围内的0％跨度位置。

    Gas turbine engine airfoil
    15.
    发明授权
    Gas turbine engine airfoil 有权
    燃气涡轮发动机翼型

    公开(公告)号：US09140127B2

    公开(公告)日：2015-09-22

    申请号：US14626167

    申请日：2015-02-19

    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 ,  F01D5/02 ,  F02C3/107 ,  F02K3/00 ,  F05D2200/222 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2250/713 ,  F05D2260/40311 ,  Y02T50/672 ,  Y02T50/673

    Abstract: An airfoil of 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 tangential 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 toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.

    Abstract translation: 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末端处的100％跨度位置。 翼型件具有切向堆积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。 正斜坡倾斜到吸力侧，负斜坡朝向压力侧倾斜。 从0％跨度位置开始的初始斜率为零或正。 第一个关键点在5-15％范围内。

    CONTOURED FLOWPATH SURFACE
    16.
    发明申请
    CONTOURED FLOWPATH SURFACE 审中-公开
    轮廓流动面

    公开(公告)号：US20150204201A1

    公开(公告)日：2015-07-23

    申请号：US14421645

    申请日：2013-03-15

    Applicant: United Technologies Corporation

    Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  James Glaspey ,  Brian Green ,  Barry M. Ford ,  Renee J. Jurek

    IPC: F01D5/30 ,  F01D5/02

    CPC classification number: F01D5/30 ,  F01D5/02 ,  F01D5/143 ,  F01D5/145 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/673

    Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.

    Abstract translation: 用于燃气涡轮发动机的转子组件的间隔件组件包括具有非轴对称流路表面的端壁段，第一凹陷和第二凹陷。 流路表面的周边包括前边缘，后边缘，吸力侧边缘和压力侧边缘。 第一凹部沿着与吸力侧边缘相邻的流路面形成，第二凹部沿着与压力侧边缘相邻的流路面形成。

    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：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。

Patent Agency Ranking