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    GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE
    1.
    发明申请
    GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE 审中-公开
    燃气轮机分岔位置风扇可变面积喷嘴

    公开(公告)号：WO2013122687A3

    公开(公告)日：2013-11-07

    申请号：PCT/US2013020077

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE

    IPC: F02K3/02

    CPC classification number: F02K1/15 ,  F02C3/107 ,  F02K1/06 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/30 ,  F02K3/06 ,  F02K3/075 ,  F05D2220/326 ,  F05D2220/327

    Abstract: A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, a fan, and a variable area flow system. The gear system defines a gear reduction ratio of greater than or equal to about 2.3. The fan is driven by the gear system about the axis to generate a bypass flow. The variable area flow system operates to effect the bypass flow.

    Abstract translation: 燃气涡轮发动机包括围绕轴线限定的核心发动机，由核心发动机驱动的齿轮系统，风扇和可变面积流量系统。 齿轮系统限定大于或等于约2.3的齿轮减速比。 风扇由齿轮系统围绕轴线驱动，以产生旁路流。 变面积流量系统运行以影响旁路流量。

    ACOUSTIC LINER WITH VARIED PROPERTIES
    2.
    发明申请
    ACOUSTIC LINER WITH VARIED PROPERTIES 审中-公开
    具有不同特性的声学衬里

    公开(公告)号：WO2014197035A3

    公开(公告)日：2015-02-19

    申请号：PCT/US2014023024

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GILSON JONATHAN ,  BALTAS CONSTANTINE

    IPC: F02C7/045 ,  F01D25/24 ,  F02C7/24

    CPC classification number: F02C7/045 ,  F01D25/24 ,  F02C3/107 ,  F02C7/24 ,  F02K1/827 ,  F05D2240/40 ,  F05D2250/00 ,  F05D2250/283 ,  F05D2250/37 ,  F05D2260/963

    Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.

    Abstract translation: 齿轮涡扇发动机包括第一转子，风扇，第二转子，齿轮系，风扇壳体，机舱和多个离散的声学衬垫段。 风扇连接到第一转子并且能够在200和6000Hz之间的频率旋转，并且风扇压力比在1.25和1.60之间。 齿轮系将第一转子连接到第二转子。 风扇壳体和机舱围绕中心线周向布置并且限定其中设置风扇的旁通流动管道。 具有不同几何特性的多个离散声学衬垫段沿着旁路流动管道设置。

    GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE
    3.
    发明专利
    GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE 未知

    公开(公告)号：SG11201402896PA

    公开(公告)日：2014-10-30

    申请号：SG11201402896P

    申请日：2013-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE

    IPC: F02K1/30 ,  F02K1/06

    Abstract: A gas turbine engine (20) comprises a core engine defined about an axis (A). The core engine includes a low pressure turbine (18) which defines a pressure ratio that is greater than about five (5). The engine further includes a fan (20) driven by the core engine about the engine axis (A) to generate a bypass flow (B) and a variable area flow system (42) which operates to effect said bypass flow (B).

    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE
    4.
    发明专利
    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE 未知

    公开(公告)号：SG11201403867QA

    公开(公告)日：2014-09-26

    申请号：SG11201403867Q

    申请日：2013-01-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

    IPC: F01D5/14

    Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE
    5.
    发明公开
    ROTOR WITH FLATTENED EXIT PRESSURE PROFILE 审中-公开
    转子带有扁平输出压力PROFILE

    公开(公告)号：EP2807343A4

    公开(公告)日：2015-10-07

    申请号：EP13741350

    申请日：2013-01-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

    IPC: F01D5/14

    CPC classification number: F01D5/141 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2240/304 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

    GEARED TURBOFAN ENGINE HAVING A REDUCED NUMBER OF FAN BLADES AND IMPROVED ACOUSTICS
    6.
    发明公开
    GEARED TURBOFAN ENGINE HAVING A REDUCED NUMBER OF FAN BLADES AND IMPROVED ACOUSTICS 审中-公开
    TURBOGEBLÄSEMOTORMIT REDUZIERTER ANZAHL VONGEBLÄSESCHAUFELNUND VERBESSERTER AKUSTIK

    公开(公告)号：EP2971535A4

    公开(公告)日：2017-02-15

    申请号：EP14770545

    申请日：2014-02-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BALTAS CONSTANTINE ,  GILSON JONATHAN

    IPC: F01D5/14 ,  F01D5/00 ,  F02C7/00

    CPC classification number: F01D5/141 ,  F05D2220/36 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

    Abstract translation: 转子叶片包括从根部到顶端部分径向延伸并且从前缘到后缘的轴向延伸的翼型件，前缘和后缘在它们之间限定曲率。 基于在翼型的前缘处的入射流速和相对跨度高度处的旋转速度，曲率确定根部和尖端部分之间的相对跨度高度处的相对出射角。 在转子叶片的操作中，相对出口角度确定从75％至95％的相对跨度高度的基本上平坦的出口压力比分布，其中出口压力比分布在±10％ 出口压力比。

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