中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

103 records (took 0.03 seconds)

    Gas turbine engine airfoil
    72.
    发明授权
    Gas turbine engine airfoil 有权
    燃气涡轮发动机翼型

    公开(公告)号：US09574574B2

    公开(公告)日：2017-02-21

    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: F01D5/14 ,  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。

    EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES
    73.
    发明申请
    EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开
    高效的，用于气体涡轮发动机的低压比推进器

    公开(公告)号：US20160377027A1

    公开(公告)日：2016-12-29

    申请号：US15252811

    申请日：2016-08-31

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon

    IPC: F02K3/06 ,  F02K1/06

    CPC classification number: F02K3/06 ,  F01D17/14 ,  F02K1/06 ,  F05D2220/327 ,  F05D2260/4031

    Abstract: A gas turbine engine includes a gear assembly, a bypass flow passage, and a core flow passage. The bypass flow passage includes an inlet. A fan is arranged at the inlet of the bypass flow passage. A first shaft and a second shaft are mounted for rotation about an engine central longitudinal axis. A first turbine is coupled with the first shaft such that rotation of the first turbine is configured to drive the fan, through the first shaft and gear assembly, at a lower speed than the first shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes 12 (N) of the fan blades, a solidity value (R) that is from 1.0 to 1.2, and a ratio of N/R that is from 10.0 to 12.0.

    Abstract translation: 燃气涡轮发动机包括齿轮组件，旁通流动通道和芯流动通道。 旁通流路包括入口。 在旁通流路的入口设有风扇。 第一轴和第二轴安装成围绕发动机中心纵向轴线旋转。 第一涡轮机与第一轴联接，使得第一涡轮的旋转被配置成以比第一轴低的速度通过第一轴和齿轮组件驱动风扇。 风扇包括从轮毂延伸的轮毂和一排风扇叶片。 该行包括12（N）个风扇叶片，固体值（R）为1.0至1.2，N / R比为10.0至12.0。

    GAS TURBINE ENGINE AIRFOIL
    77.
    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：US20160341212A1

    公开(公告)日：2016-11-24

    申请号：US15113868

    申请日：2014-08-22

    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

    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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE−Xd)/(Xd−XTE) at 100% span position is about 1 and (XLE−Xd)/(Xd−XTE) at 90% span position is about 1.

    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。 翼型几何对应于轴向前缘和后缘曲线以及轴向堆叠偏移曲线。 翼型从根部延伸，零轴向参考点对应于根部的轴向中心。 XLE对应于在给定跨度位置处从前缘到参考点的轴向距离。 XTE对应于在给定跨度位置处从后缘到参考点的轴向距离。 Xd对应于给定跨度位置处的轴向堆积偏移。 （XLE-Xd）/（Xd-XTE）在100％跨度位置约为1，（XLE-Xd）/（Xd-XTE）在90％跨度位置约为1。

    TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS
    78.
    发明申请
    TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS 有权
    TURBOFAN布局与叶片通道变化

    公开(公告)号：US20160273361A1

    公开(公告)日：2016-09-22

    申请号：US14699322

    申请日：2015-04-29

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Sue-Li Chuang

    IPC: F01D5/14 ,  F02C3/04 ,  F02K3/06 ,  F04D29/32 ,  F04D29/38

    CPC classification number: F01D5/14 ,  F01D5/141 ,  F02C3/10 ,  F04D29/32 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/36 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and 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. Facing pressure and suction sides of adjacent airfoils define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side. The width diverges without converging along the channel for at least some of the span positions.

    Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括限定轴线的转子轮毂和围绕转子轮毂周向间隔开的翼型阵列。 每个翼型件包括在前缘和后缘之间的压力和吸力侧面，并且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。 相邻翼型件的面对压力和吸力侧在相邻翼型件的给定跨度位置处限定具有在面向的压力和吸力侧之间的宽度的弦向方向的通道。 沿着通道的每个压力侧位置处的宽度被定义为到沿吸力侧的位置的最小距离。 宽度发散，而不会沿着通道聚集至少一些跨度位置。

    GAS TURBINE ENGINE AIRFOIL
    79.
    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：US20160238023A1

    公开(公告)日：2016-08-18

    申请号：US15063594

    申请日：2016-03-08

    Applicant: United Technologies Corporation

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

    IPC: F04D29/38 ,  F02K3/04 ,  F02C3/14 ,  F02C7/36 ,  F04D29/32 ,  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 constant or has a decreasing total chord length from the first peak toward 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). The curve is at least a third order polynomial and has an initial positive slope.

    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，曲线或者保持恒定，或者从第一个峰到100％的跨度位置具有减小的总弦长。 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。 该曲线是至少三阶多项式并具有初始正斜率。

    Gas turbine engine airfoil
    80.
    发明授权
    Gas turbine engine airfoil 有权
    燃气涡轮发动机翼型

    公开(公告)号：US09399917B2

    公开(公告)日：2016-07-26

    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: F01D5/06 ,  F01D5/14 ,  F04D29/32 ,  F04D29/38

    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。

Patent Agency Ranking