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    GAS TURBINE ENGINE AIRFOIL
    11.
    发明申请
    GAS TURBINE ENGINE AIRFOIL 有权
    气体涡轮发动机气翼

    公开(公告)号：US20150233252A1

    公开(公告)日：2015-08-20

    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。

    Gas turbine engine airfoil
    12.
    发明授权
    Gas turbine engine airfoil 有权

    公开(公告)号：US10519971B2

    公开(公告)日：2019-12-31

    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 ,  F01D5/14 ,  F04D29/32 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06

    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.

    EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES
    14.
    发明申请
    EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20180230943A1

    公开(公告)日：2018-08-16

    申请号：US15936552

    申请日：2018-03-27

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Byron R. Monzon

    IPC: F02K3/06 ,  F02K1/06 ,  F01D17/14

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

    Abstract: A gas turbine engine includes a bypass flow passage and a core flow passage. The bypass flow passage defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is located upstream of the bypass flow passage. The bypass flow passage includes an inlet and an outlet that define a design fan pressure ratio of approximately 1.3 to 1.55. A first, inner shaft and a second, outer shaft are concentric. A first turbine is coupled with the first shaft, and the first shaft is coupled with the fan. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number of the fan blades, the number (N) being 18, a solidity value (R) at tips of the fan blades that is from 1.0 to 1.1, and a ratio of N/R that is from 16.4 to 18.0.

    Gas turbine engine airfoil
    18.
    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
    19.
    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
    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：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。

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