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    TURBINE SECTION OF HIGH BYPASS TURBOFAN
    252.
    发明申请
    TURBINE SECTION OF HIGH BYPASS TURBOFAN 审中-公开
    高旁路涡轮机涡轮部分

    公开(公告)号：US20150345404A1

    公开(公告)日：2015-12-03

    申请号：US14692090

    申请日：2015-04-21

    Applicant: United Technologies Corporation

    Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz

    IPC: F02C9/18 ,  F02C7/36 ,  F01D25/24 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/20

    Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

    Abstract translation: 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比低于约170。

    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE
    253.
    发明申请
    GAS TURBINE ENGINE WITH GEARED ARCHITECTURE 审中-公开
    具有齿轮架构的气体涡轮发动机

    公开(公告)号：US20150300197A1

    公开(公告)日：2015-10-22

    申请号：US14753048

    申请日：2015-06-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

    IPC: F01D15/12

    CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H57/0479 ,  F16H57/0486

    Abstract: A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).

    Abstract translation: 用于燃气涡轮发动机的齿轮架构包括风扇轴和支撑在风扇轴上的风扇，并且限定大于约六的旁路流量比。 一个框架支撑风扇轴。 齿轮系驱动风扇轴。 齿轮系统具有大于或等于约2.3的齿轮减速比。 扭矩框架至少部分地支撑齿轮系统。 一个输入端耦合到齿轮系统。 下游涡轮机联接以可旋转地驱动输入联接器。 下游涡轮限定大于约五（5）的压力比。

    GEARED TURBOFAN ENGINE WITH INTER-SHAFT DEFLECTION FEATURE
    254.
    发明申请
    GEARED TURBOFAN ENGINE WITH INTER-SHAFT DEFLECTION FEATURE 审中-公开
    具有内部扭矩特征的齿轮涡轮发动机

    公开(公告)号：US20150247454A1

    公开(公告)日：2015-09-03

    申请号：US14433779

    申请日：2013-03-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Pedro Laureano ,  Frederick M. Schwarz

    IPC: F02C3/10 ,  F02C7/36 ,  F02C7/06 ,  F02C3/107

    CPC classification number: F02C3/10 ,  F01D5/026 ,  F01D21/045 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F04D29/054 ,  F05D2250/311 ,  F05D2250/36 ,  Y02T50/672 ,  Y10T29/49321

    Abstract: A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a first turbine driving the first compressor and a second turbine driving the second compressor. An inner shaft defines a driving link between the second compressor and the second turbine and an outer shaft defines a driving link between the first compressor and the first turbine. The inner shaft and the outer shaft are concentric about a common axis of rotation. A bumper is disposed on the inner shaft within an axial region common to an aft portion of the outer shaft for accommodating interaction between the inner and outer shafts during high load conditions.

    Abstract translation: 公开的燃气涡轮发动机包括压缩机部分，其包括设置在第二压缩机的轴向前方的第一压缩机，与压缩机部分流体连通的燃烧器和与燃烧器流体连通的涡轮部分。 涡轮部分包括驱动第一压缩机的第一涡轮机和驱动第二压缩机的第二涡轮机。 内轴限定第二压缩机和第二涡轮机之间的驱动连杆，外轴限定第一压缩机和第一涡轮机之间的驱动连杆。 内轴和外轴与共同的旋转轴线同心。 保险杠设置在内轴上的与外轴的后部共同的轴向区域中，用于在高负载条件下容纳内轴和外轴之间的相互作用。

    GAS TURBINE ENGINE WITH FORWARD MOMENT ARM
    255.
    发明申请
    GAS TURBINE ENGINE WITH FORWARD MOMENT ARM 审中-公开
    燃气涡轮发动机与前进的臂

    公开(公告)号：US20150240725A1

    公开(公告)日：2015-08-27

    申请号：US14432289

    申请日：2013-09-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： David Bomzer ,  Frederick M. Schwarz

    IPC: F02C7/36 ,  F02C3/10 ,  F02C7/20 ,  F01D5/02

    CPC classification number: F02C7/20 ,  B64D2027/262 ,  F02C3/107 ,  F05D2250/30 ,  Y02T50/672 ,  Y10T29/49321

    Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

    Abstract translation: 燃气涡轮发动机包括可围绕轴线旋转的多个风扇叶片，其中多个风扇叶片中的每一个包括前缘。 燃气涡轮发动机还包括涡轮部分，其包括具有后缘的后部大多数涡轮机叶片和由涡轮机部分驱动的用于使多个风扇叶片绕轴线旋转的齿轮架构。 燃气涡轮发动机的重心位于距离尾部最大涡轮机叶片的后缘的第一轴向距离处，其在多个风扇叶片的前缘之间的总长度的约35％和约75％之间， 尾部最后部的涡轮叶片。

    Turbofan Engine Main Bearing Arrangement
    257.
    发明申请
    Turbofan Engine Main Bearing Arrangement 有权
    涡轮发动机主轴承布置

    公开(公告)号：US20150125293A1

    公开(公告)日：2015-05-07

    申请号：US14207722

    申请日：2014-03-13

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Frederick M. Schwarz

    IPC: F02C7/06 ,  F02C3/107

    CPC classification number: F01D25/16 ,  F01D5/02 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/52 ,  F05D2240/54 ,  F05D2260/40311

    Abstract: A turbofan engine (20; 300; 400) comprises a fan (28), a fan drive gear system (60), a fan shaft (120) coupling the fan drive gear system to the fan, a low spool, an intermediate spool, and a core spool. The low spool engages at least three main bearings of which at least two are non-thrust bearings and at least one is a thrust bearing. The fan shaft engages at least two bearings (148, 150). The core spool engages at least two bearings (250, 260). The intermediate spool engages at least two of said bearings (220, 200, 230; 220, 200, 230-2; 200, 220, 230-3).

    Abstract translation: 涡扇发动机（20; 300; 400）包括风扇（28），风扇驱动齿轮系统（60），将风扇驱动齿轮系统联接到风扇的风扇轴（120），低阀芯，中间阀芯， 和芯轴。 低滑阀接合至少三个主轴承，其中至少两个是非推力轴承，并且至少一个是推力轴承。 风扇轴接合至少两个轴承（148,150）。 芯轴与至少两个轴承（250,260）接合。 中间卷轴接合至少两个所述轴承（220,200,230; 220,200,230-2; 200,220,230-3）。

    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE
    258.
    发明申请
    GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE 审中-公开
    具有功率密度范围的齿轮涡轮发动机

    公开(公告)号：US20150113943A1

    公开(公告)日：2015-04-30

    申请号：US14593056

    申请日：2015-01-09

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

    IPC: F02C7/36 ,  F02C3/107 ,  F02K3/06

    CPC classification number: F02C7/36 ,  F01D1/26 ,  F01D15/12 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2270/051

    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.

    Abstract translation: 燃气涡轮发动机涡轮机具有高压涡轮机，该高压涡轮机被构造成以围绕中心轴线的第一方向的高压压缩机作为高压压缩机旋转，以及构造成作为低压阀芯的低压压缩机旋转的低压涡轮机 关于中心轴的第一个方向。 功率密度大于或等于约1.5且小于或等于约5.5lbf /立方英寸。 风扇通过变速机构连接到低压阀芯，并沿与第一方向相反的第二方向旋转。

    TURBOMACHINE THRUST BALANCING SYSTEM
    260.
    发明申请
    TURBOMACHINE THRUST BALANCING SYSTEM 审中-公开
    涡轮平衡平衡系统

    公开(公告)号：US20140314541A1

    公开(公告)日：2014-10-23

    申请号：US13723421

    申请日：2012-12-21

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F01D25/16

    CPC classification number: F01D25/16 ,  F02C7/06 ,  F05D2240/52 ,  F05D2260/15

    Abstract: An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine.

    Abstract translation: 涡轮机械推力平衡系统的一个示例包括与涡轮联接的构件，用于从其传递旋转动力。 承载装置可旋转地支撑构件。 承载装置构造成抵消涡轮机产生的基本上所有的推力。

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