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    GAS TURBINE ENGINE AIRFOIL
    15.
    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：WO2015126824A1

    公开(公告)日：2015-08-27

    申请号：PCT/US2015/016154

    申请日：2015-02-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GALLAGHER, Edward J. ,  MONZON, Byron R. ,  LIU, Ling ,  LI, Linda S. ,  WHITLOW, Darryl ,  FORD, Barry M.

    IPC: F01D5/14

    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末端处的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
    17.
    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：WO2015126454A1

    公开(公告)日：2015-08-27

    申请号：PCT/US2014/052516

    申请日：2014-08-25

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GALLAGHER, Edward J. ,  MONZON, Byron R. ,  LIU, Ling ,  LI, Linda S. ,  WHITLOW, Darryl ,  FORD, Barry M.

    IPC: F01D5/14

    CPC classification number: F04D29/325 ,  F01D5/141 ,  F02K3/06 ,  F04D19/002 ,  F04D29/324 ,  F04D29/384 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  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 curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span. 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.

    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。 翼型件具有对应于后缘扫掠角度和跨度位置之间的关系的曲线。 后缘扫掠角度在40-70％跨度位置的范围内在10°至20°的范围内，后缘扫掠角度从0％跨度到至少95％跨度为正。 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。

    GAS TURBINE ENGINE AIRFOIL
    18.
    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：WO2015126450A1

    公开(公告)日：2015-08-27

    申请号：PCT/US2014/052293

    申请日：2014-08-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GALLAGHER, Edward J. ,  MONZON, Byron R. ,  LIU, Ling ,  LI, Linda S. ,  WHITLOW, Darryl ,  FORD, Barry M.

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

    Abstract: 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 has a relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/- 0.04 inch (1.01 mm) per 1% span.

    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。 翼型件具有轴向前缘位置和跨度位置之间的关系，其是具有大致U形曲线的至少三阶多项式，其具有初始负斜率，随后是正斜率。 正斜坡向前倾斜，负斜坡向前倾斜。 该曲线在曲线从负斜率变化到正斜率的30-50％跨度位置的范围内具有临界点。 曲线通常从55％跨度到75％跨度是线性的，并且具有以每1％跨度约0.0875英寸（2.22mm），每1％跨度+/- 0.04英寸（1.01mm）的速率增加的正斜率。

    NACELLE VENTILATION MANIFOLD
    20.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开
    通风通风口

    公开(公告)号：WO2015122992A1

    公开(公告)日：2015-08-20

    申请号：PCT/US2015/011944

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  PAPA, Federico

    IPC: F02C7/18 ,  F02C7/32

    CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

    Abstract translation: 燃气涡轮发动机包括核心发动机壳体。 机舱位于核心发动机壳体的径向外侧。 外部旁路外壳位于机舱的外侧。 至少有一个待冷却的附件定位在径向位于核心发动机壳体和机舱之间的腔室中。 歧管将冷却空气提供到腔室中，并且围绕核心发动机的中心轴线周向延伸。 机舱在圆周范围内具有不对称的流动横截面。

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