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    GAS TURBINE ENGINE AIRFOIL
    51.
    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。

    Turbofan arrangement with blade channel variations
    52.
    发明授权
    Turbofan arrangement with blade channel variations 有权
    Turbofan安排与刀片通道变化

    公开(公告)号：US09470093B2

    公开(公告)日：2016-10-18

    申请号：US14699322

    申请日：2015-04-29

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Sue-Li Chuang

    IPC: F04D29/32 ,  F01D5/14

    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。

    TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS
    53.
    发明申请
    TURBOFAN ARRANGEMENT WITH BLADE CHANNEL VARIATIONS 审中-公开
    TURBOFAN布局与叶片通道变化

    公开(公告)号：US20160273547A1

    公开(公告)日：2016-09-22

    申请号：US15045343

    申请日：2016-02-17

    Applicant: United Technologies Corporation

    Inventor： Edward J. Gallagher ,  Sue-Li Chuang

    IPC: F04D29/38 ,  F02C3/10 ,  F04D29/32

    CPC classification number: F01D5/14 ,  F01D5/141 ,  F02C3/10 ,  F04D29/32 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/36 ,  F05D2250/70 ,  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 defining 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 converging and diverging along the channel for at least some 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顶端处的100％跨度位置，面向压力和抽吸 相邻翼型件的侧面在相邻翼型件的给定跨度位置处限定在弦向方向上的通道，该通道在面对的压力和吸力侧之间具有宽度。 沿着通道的每个压力侧位置处的宽度被定义为到沿着吸力侧的位置的最小距离，在至少一些跨度位置处，沿着通道收敛和发散的宽度。

    GAS TURBINE ENGINE AIRFOIL
    57.
    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
    58.
    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。

    GAS TURBINE ENGINE AIRFOIL
    60.
    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。

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