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    TURBINE ENGINE GEARBOX
    81.
    发明申请
    TURBINE ENGINE GEARBOX 审中-公开
    涡轮发动机齿轮箱

    公开(公告)号：US20160131043A1

    公开(公告)日：2016-05-12

    申请号：US14940632

    申请日：2015-11-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune

    IPC: F02C7/36 ,  F02K3/04 ,  F16H1/28

    CPC classification number: F02C7/36 ,  F01D15/12 ,  F02K3/04 ,  F02K3/072 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/46 ,  F16H57/0006 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement. Each of the at least two double helical gears are disposed to rotate about respective axes, and each have a first plurality of gear teeth axially spaced from a second plurality of gear teeth by a spacer. Each of the first plurality of gear teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer. Each first end of the first plurality of gear teeth is circumferentially offset from each first end of the second plurality of gear teeth. A gear ratio of the gear reduction is greater than about 2.3:1. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机包括风扇，压缩机，燃烧器和风扇驱动涡轮机转子。 风扇驱动涡轮驱动风扇通过齿轮减速。 齿轮减速包括至少两个啮合啮合的双斜齿轮。 所述至少两个双螺旋齿轮中的每一个设置成围绕相应的轴线旋转，并且每个具有通过间隔件与第二多个齿轮齿轴向间隔开的第一多个齿轮齿。 第一多个齿轮齿中的每一个具有面向间隔件的第一端，并且第二多个齿轮齿中的每一个具有面向间隔件的第一端。 第一多个齿轮齿的每个第一端从第二多个齿轮齿的每个第一端周向地偏移。 齿轮减速的齿轮比大于约2.3：1。 还公开了一种方法。

    Turbofan Engine Bearing and Gearbox Arrangement
    82.
    发明申请
    Turbofan Engine Bearing and Gearbox Arrangement 审中-公开
    涡轮发动机轴承和齿轮箱布置

    公开(公告)号：US20160032827A1

    公开(公告)日：2016-02-04

    申请号：US14776913

    申请日：2014-03-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： William G. Sheridan ,  Michael E. McCune

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

    CPC classification number: F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/403 ,  F05D2260/4031

    Abstract: A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.

    Abstract translation: 涡轮风扇发动机（20）具有将风扇驱动齿轮系统（60）联接到风扇（28）的风扇轴（120）。 低阀芯包括将低压涡轮机联接到风扇驱动齿轮系统的低压涡轮机（50）和低轴（56）。 芯轴卷轴包括高压涡轮机（46），压缩机（44）和将高压涡轮机联接到芯轴卷轴压缩机的芯轴（52）。 第一轴承（150）接合风扇轴，第一轴承是推力轴承。 第二轴承（160）与风扇驱动齿轮系的与第一轴承相反的一侧接合风扇轴，第二轴承是滚子轴承。 第三轴承（180）接合低卷筒轴和风扇轴。

    Fan Axial Containment System
    84.
    发明申请
    Fan Axial Containment System 审中-公开
    风机轴向封闭系统

    公开(公告)号：US20160003093A1

    公开(公告)日：2016-01-07

    申请号：US14770599

    申请日：2014-03-13

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune

    IPC: F01D21/04 ,  F01D15/12 ,  F01D25/16 ,  F01D25/24 ,  F01D5/02 ,  F01D17/06

    CPC classification number: F01D21/045 ,  F01D5/02 ,  F01D15/12 ,  F01D17/06 ,  F01D21/08 ,  F01D25/162 ,  F01D25/24 ,  F02C7/06 ,  F05D2220/36 ,  F05D2240/52 ,  F05D2260/83 ,  Y02T50/671

    Abstract: A gas turbine engine (20) and method for containing a fan inside an engine after a fan thrust bearing assembly failure. The engine (20) may comprise a fan (42), a housing (100) including a compartment (102), a fan shaft (104) inside the compartment (102) and comprising a bowl (108), a support structure (110) inside the compartment (102), a speed sensor pickup (114) mounted on the outer surface (120) of the bowl (108), a speed sensor (112) mounted on the support structure (110), and a fan thrust bearing assembly (41) disposed forward of the bowl (108). The fan thrust bearing assembly (41) including a bearing (126). The speed sensor (112) and the sensor pickup (114) define a defining a sensor gap (116). The bearing (126) and the outer surface (120) defining a fan thrust bearing gap (130), wherein the sensor gap (116) is less than the fan thrust bearing gap.

    Abstract translation: 一种燃气涡轮发动机（20）以及在风扇推力轴承组件发生故障后在发动机内容纳风扇的方法。 发动机（20）可以包括风扇（42），包括隔室（102）的壳体（100），隔室（102）内的风扇轴（104），并且包括碗（108），支撑结构（110） ），安装在所述碗（108）的外表面（120）上的速度传感器拾取器（114），安装在所述支撑结构（110）上的速度传感器（112）和风扇止推轴承 组件（41）布置在碗（108）的前方。 风扇推力轴承组件（41）包括轴承（126）。 速度传感器（112）和传感器拾取器（114）限定了传感器间隙（116）。 轴承（126）和外表面（120）限定了风扇止推轴承间隙（130），其中传感器间隙（116）小于风扇推力轴承间隙。

    EPICYCLIC GEAR TRAIN
    85.
    发明申请
    EPICYCLIC GEAR TRAIN 有权
    环形齿轮火车

    公开(公告)号：US20150345321A1

    公开(公告)日：2015-12-03

    申请号：US14824351

    申请日：2015-08-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F01D15/12 ,  F01D5/02 ,  F01D25/16 ,  F01D1/02 ,  F16H57/04 ,  F01D25/18

    CPC classification number: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

    Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).

    Abstract translation: 涡轮发动机具有风扇轴。 至少有一个锥形轴承安装在风扇轴上。 风扇轴包括沿至少一个径向分量的方向延伸的至少一个通道，并且与至少一个锥形轴承相邻。 风扇安装在锥形轴承上旋转。 一个行星齿轮系被联接以驱动风扇。 行星齿轮系包括支撑与太阳齿轮啮合的中间齿轮的载体。 环形齿轮围绕并与中间齿轮啮合。 每个中间齿轮支撑在相应的轴颈轴承上。 行星齿轮系确定齿轮减速比大于或等于约2.3。 涡轮部分联接以通过行星齿轮系驱动风扇。 涡轮部分具有包括大于约5的压力比的风扇驱动涡轮机。风扇包括小于约1.45的压力比，并且风扇具有大于约十（10）的旁路比。

    RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME
    89.
    发明申请
    RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME 有权
    环形齿轮安装与油气动力计划

    公开(公告)号：US20140286755A1

    公开(公告)日：2014-09-25

    申请号：US14293279

    申请日：2014-06-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael E. McCune ,  Lawrence E. Portlock

    IPC: F02C7/36

    CPC classification number: F16H57/0424 ,  F01D5/027 ,  F01D25/18 ,  F02C7/28 ,  F02C7/36 ,  F05D2240/55 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F05D2260/98 ,  F16D1/076 ,  F16H1/28 ,  F16H57/0402 ,  F16H57/042 ,  F16H57/0421 ,  F16H57/043 ,  F16H57/0458 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/08 ,  Y10T29/49462

    Abstract: A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed.

    Abstract translation: 涡轮发动机包括风扇部分，其包括多个风扇叶片，涡轮部分和联接在涡轮部分和风扇部分之间的行星齿轮系，用于在涡轮部分和风扇部分之间提供减速。 行星齿轮系包括多个中间齿轮。 载体支撑多个中间齿轮。 太阳齿轮与多个中间齿轮啮合，并且环形齿轮围绕并与多个中间齿轮啮合。 齿圈包括第一和第二部分，每个部分具有带齿的内周边。 所述环形齿轮的第一和第二部分具有与所述齿相对的外周表面，所述外周表面提供第一厚度，第二厚度大于所述第一厚度并且从所述第一厚度轴向向内，以及凸缘，其径向延伸远离所述轴线。 还公开了一种用于涡轮发动机的行星齿轮系和设计行星齿轮系的方法。

    MOUNTING SYSTEM FOR A PLANATARY GEAR TRAIN IN A GAS TURBINE ENGINE
    90.
    发明申请
    MOUNTING SYSTEM FOR A PLANATARY GEAR TRAIN IN A GAS TURBINE ENGINE 有权
    一种气体涡轮发动机中的平面齿轮火箭安装系统

    公开(公告)号：US20140256504A1

    公开(公告)日：2014-09-11

    申请号：US14151946

    申请日：2014-01-10

    Applicant: United Technologies Corporation

    Inventor： Michael E. McCune ,  Gino Pagluica

    IPC: F16H57/00

    CPC classification number: F16H57/0018 ,  F01D25/164 ,  F02C7/36 ,  F05D2230/60 ,  F05D2240/50 ,  F05D2260/40311 ,  F16H1/48 ,  Y02T50/671 ,  Y10T29/53 ,  Y10T477/688

    Abstract: A mounting system for a planetary gear train in a gas turbine engine comprises a support strut, a deflection flange and a deflection limiter. The support strut extends between a stationary engine case and a rotating engine shaft that provides input to the planetary gear train in the gas turbine engine. The deflection flange extends from a rotating output component of the planetary gear train. The deflection limiter is connected to the support strut and engages the deflection flange when the gear train becomes radially displaced.

    Abstract translation: 用于燃气涡轮发动机中的行星齿轮系的安装系统包括支撑支柱，偏转凸缘和偏转限制器。 支撑支柱在固定的发动机壳体和向燃气涡轮发动机中的行星齿轮系提供输入的旋转发动机轴之间延伸。 偏转凸缘从行星齿轮系的旋转输出部件延伸。 偏转限制器连接到支撑支柱，并且当齿轮系变为径向位移时，其接合偏转凸缘。

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