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    ガスタービンエンジン
    41.
    发明专利
    ガスタービンエンジン 有权
    气体涡轮发动机

    公开(公告)号：JP2014234822A

    公开(公告)日：2014-12-15

    申请号：JP2014042229

    申请日：2014-03-05

    Applicant: ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation ,  United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： MCCUNE MICHAEL E ,  JASON HUSBAND ,  FREDERICK M SCHWARZ ,  DANIEL BERNARD KUPRATIS ,  SUCIU GABRIEL L ,  WILLIAM K ACKERMANN

    IPC: F02C3/107 ,  F01D25/00 ,  F02C7/36 ,  F02K3/06

    CPC classification number: F01D25/16 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: 【課題】歯車の噛合部における整列のずれを防止しつつ、エンジンの効率を向上させる。【解決手段】ガスタービンエンジン20が、ファン42を駆動するファンシャフト76と、このファンシャフト76を支持するフレーム82と、ファンシャフト76を駆動する複数の歯車とを備えている。可撓性支持部78が、複数の歯車を少なくとも部分的に支持する。第1のタービンセクション46は、第1の出口点401において第1の出口面積を有するとともに、第1の速度で回転する。第2のタービンセクション54は、第2の出口点400において第2の出口面積を有するとともに、第1の速度よりも高速の第2の速度で回転する。第1の性能量が、第1の速度の二乗と第1の出口面積との積として定義される。第2の性能量が、第2の速度の二乗と第2の出口面積との積として定義される。第2の性能量に対する第1の性能量の比は、約0.5〜約1.5である。【選択図】図1D

    Abstract translation: 要解决的问题：为了防止齿轮啮合网格的错位，提高发动机效率。解决方案：燃气轮机发动机20具有驱动风扇42的风扇轴76，支撑风扇轴76的框架82和多个齿轮 驱动风扇轴76.柔性支撑件78至少部分支撑多个齿轮。 第一涡轮机部分46在第一出口点401处具有第一出口区域并以第一速度旋转。 第二涡轮部分54在第二出口点处具有第二出口区域，并以比第一速度快的第二速度旋转。 第一性能数量被定义为第一速度平方和第一出口区域的乘积。 第二性能量被定义为第二速度平方和第二出口区的乘积。 第一性能量与第二性能量的比率在约0.5至约1.5之间。

    Gas turbine engine with pylon mounted accessory drive
    45.
    发明专利
    Gas turbine engine with pylon mounted accessory drive 有权
    气体涡轮发动机带有垂直安装附件驱动器

    公开(公告)号：JP2013148085A

    公开(公告)日：2013-08-01

    申请号：JP2013005035

    申请日：2013-01-16

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： WINTER MICHAEL

    IPC: F02C7/32 ,  B64D29/06 ,  B64D41/00 ,  F01D25/24 ,  F02C7/00 ,  F02C7/20 ,  F02C7/36

    CPC classification number: F02C7/32 ,  Y02T50/671

    Abstract: PROBLEM TO BE SOLVED: To provide an accessory gearbox for a gas turbine engine which provides power to larger generators than conventional engines, yet facilitates nacelle packaging.SOLUTION: An engine pylon assembly for a gas turbine engine 10 comprises a core nacelle 12 defined about an engine centerline axis, a fan nacelle 34 mounted at least partially around the core nacelle 12 to define a fan bypass flow path for a fan bypass airflow, an engine pylon P to support the core nacelle 12 and the fan nacelle 34, and an accessory gearbox 60 mounted within the engine pylon P axially aft of the fan nacelle 34. The gas turbine engine 10 includes the accessory gearbox 60 within the engine pylon P. An accessory component 66 may be mounted within the engine pylon P to save weight and space within the core nacelle 12 as well as provide a relatively lower temperature operating environment.

    Abstract translation: 要解决的问题：提供一种用于燃气涡轮发动机的附件齿轮箱，其为常规发动机提供大功率发电机的功率，但也有助于机舱包装。解决方案：用于燃气涡轮发动机10的发动机塔架组件包括围绕 发动机中心线轴，至少部分地围绕核心机舱12安装的风扇机舱34，以限定用于风扇旁路气流的风扇旁路流路，支撑核心机舱12和风扇机舱34的发动机塔架P以及附件齿轮箱 60安装在发动机塔架P轴向后方的风扇机舱34.燃气涡轮发动机10包括在发动机塔架P内的附件齿轮箱60.附件部件66可以安装在发动机塔架P内，以将重量和空间保持在 核心机舱12，并提供相对较低温度的操作环境。

    Gas turbine engine and disassembly method of front structure of gas turbine engine
    46.
    发明专利
    Gas turbine engine and disassembly method of front structure of gas turbine engine 有权
    气体涡轮发动机前轮结构的气体发动机和拆卸方法

    公开(公告)号：JP2013096413A

    公开(公告)日：2013-05-20

    申请号：JP2012237381

    申请日：2012-10-29

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： OTTO JOHN R ,  CIGAL BRIAN P ,  SHARMA SUNIL ,  DAVIS TODD A

    IPC: F02C7/00 ,  F01D25/00 ,  F01D25/24 ,  F01D25/28 ,  F02C7/36 ,  F02K3/06

    Abstract: PROBLEM TO BE SOLVED: To reduce the time and costs required for maintaining a specific component of a gas turbine engine (20).SOLUTION: The gas turbine engine (20) includes a central body support (62) that provides an inner annular wall for a core flow path. The central body support (62) includes first splines. A geared architecture (48) interconnects a spool and a fan rotatable about an axis. A flex support (68) interconnects the geared architecture (48) to the central body support (62). The flex support (68) includes second splines that intermesh with the first splines for transferring torque therebetween.

    Abstract translation: 要解决的问题：减少维持燃气涡轮发动机（20）的特定部件所需的时间和成本。 解决方案：燃气涡轮发动机（20）包括中心主体支撑件（62），该中心主体支撑件（62）为核心流动路径提供内部环形壁。 中心体支撑件（62）包括第一花键。 齿轮架构（48）将线轴和可围绕轴线旋转的风扇相互连接。 柔性支撑件（68）将齿轮架构（48）与中心体支撑件（62）相互连接。 柔性支撑件（68）包括与第一花键相互啮合以在其间传递扭矩的第二花键。 版权所有（C）2013，JPO＆INPIT

    Integrated ceramic matrix composite disk for gas turbine engine
    47.
    发明专利
    Integrated ceramic matrix composite disk for gas turbine engine 有权
    用于气体涡轮发动机的集成陶瓷基复合材料盘

    公开(公告)号：JP2012246925A

    公开(公告)日：2012-12-13

    申请号：JP2012119126

    申请日：2012-05-25

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： ALVANOS IOANNIS ,  SUCIU GABRIEL L

    IPC: F01D5/28 ,  F01D5/02 ,  F01D5/12 ,  F01D5/20 ,  F01D9/02 ,  F01D9/04 ,  F01D11/02 ,  F01D11/08 ,  F01D25/00 ,  F02C7/00 ,  F02C7/28

    CPC classification number: F01D5/282 ,  F01D5/066 ,  F01D5/284 ,  F01D5/34 ,  F01D11/001 ,  F05D2300/6033

    Abstract: PROBLEM TO BE SOLVED: To provide an additional disk for a gas turbine engine.SOLUTION: CMC disks 64A, 64B and 64C for a gas turbine engine 20 include CMC hubs 68A, 68B and 68C defined about an axis, and a plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs. The CMC disks 64A, 64B and 64C for the gas turbine engine 20 include the plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs 68A, 68B and 68C, and rails 80A, 80C integrated with the respective CMC hubs on sides opposite to the plurality of airfoils. The rails define rail platforms adjacent to the plurality of airfoils and tapered to a rail inner bore.

    Abstract translation: 要解决的问题：提供用于燃气涡轮发动机的附加盘。 解决方案：用于燃气涡轮发动机20的CMC盘64A，64B和64C包括围绕轴限定的CMC轮毂68A，68B和68C以及与各个CMC轮毂一体化的多个CMC翼型66A，66B和66C。 用于燃气涡轮发动机20的CMC盘64A，64B和64C包括与相应的CMC集线器68A，68B和68C一体化的多个CMC翼型66A，66B和66C，以及与侧面上的相应CMC轮毂一体化的轨道80A，80C 与多个翼型件相对。 导轨限定与多个翼型件相邻的轨道平台并且逐渐变细到轨道内孔。 版权所有（C）2013，JPO＆INPIT

    Inlet guide vane flap, fan section, and control method for variable-shape inlet guide vane flap system
    48.
    发明专利
    Inlet guide vane flap, fan section, and control method for variable-shape inlet guide vane flap system 有权
    入口指南VANE FLAP，风扇部分和可变形导向导叶片系统的控制方法

    公开(公告)号：JP2011132963A

    公开(公告)日：2011-07-07

    申请号：JP2011083273

    申请日：2011-04-05

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： LORD WESLEY K ,  SHARMA OM P ,  DYE CHRISTOPHER ,  SUCIU GABRIEL L

    IPC: F04D29/56

    CPC classification number: F01D5/146 ,  F01D5/148 ,  F01D17/162 ,  F04D29/563 ,  F05B2240/311 ,  F05D2240/12 ,  Y02T50/673

    Abstract: PROBLEM TO BE SOLVED: To provide an inlet guide vane flap with increased partial-speed operability and flutter margin, thus avoiding fan rotor mistuning at particular operational conditions. SOLUTION: A variable-shape inlet guide vane (IGV) system 46 includes the variable-shape inlet guide vane flap 48 provided with a flexible part 64 that enables the desired spanwise distribution of axial velocities Cx, α, and β at an inlet of the fan rotor 30. The flexible part 64 is formed of a flexible material such as silicone rubber combined with internal reinforcing fibers or filaments. The form of the flap 48 is not symmetric, but twisted during actuation from the maximum opening position to the maximum closed position. COPYRIGHT: (C)2011,JPO&INPIT

    Abstract translation: 要解决的问题：提供具有增加的部分速度可操作性和颤振余量的入口导向叶片翼片，从而避免在特定操作条件下风扇转子失谐。 解决方案：可变形入口引导叶片（IGV）系统46包括设置有柔性部分64的可变形入口导向叶片翼片48，其能够在轴向速度Cx，α和β处产生期望的翼展方向分布 风扇转子30的入口。柔性部分64由诸如与内部增强纤维或细丝组合的硅橡胶的柔性材料形成。 翼片48的形状不是对称的，而是在从最大打开位置到最大关闭位置的致动期间扭转。 版权所有（C）2011，JPO＆INPIT

    EROSION RESISTANT ANTI-ICING COATING
    49.
    发明专利
    EROSION RESISTANT ANTI-ICING COATING 审中-公开

    公开(公告)号：JP2006348295A

    公开(公告)日：2006-12-28

    申请号：JP2006163240

    申请日：2006-06-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PUTNAM JOHN W

    IPC: C09D183/04 ,  B05D5/00 ,  B05D7/24 ,  B32B27/06 ,  C09D5/08 ,  C09D5/16 ,  C09D7/12 ,  C09D127/12 ,  C09D127/16 ,  C09D127/18 ,  C09D129/10 ,  C09D183/07 ,  C09D183/08 ,  F01D25/02

    Abstract: PROBLEM TO BE SOLVED: To provide an erosion resistant anti-icing coating to be used on various components. SOLUTION: Liquid and/or solid anti-icing fillers and/or oils are combined with erosion resistant silicone and/or fluorocarbon elastomeric materials to create erosion resistant anti-icing coatings. These coatings may be utilized to prevent ice build-up on various gas turbine engine components, aircraft components, watercrafts (i.e., boats and ships), power lines, telecommunication lines, etc. Each coated pin 10 was positioned in a test apparatus 20, where a layer of ice 30 was then grown on each coated pin 10 in the annular gap between the coated pin 10 and the mold 40. Thereafter, the ice adhesion strength on each coated pin 10 was determined quantitatively via a pin shear test. The pin shear test involved constraining the mold at its base 42 while the pin was loaded axially in the direction of arrow A. This puts the ice 30 into shear, and allows the load at which the ice de-bonded from each coated pin 10 to be determined. COPYRIGHT: (C)2007,JPO&INPIT

    INJECTION DEVICE FOR INJECTING FLOW OF PRIMARY FLUID INTO FLOW OF SECONDARY FLUID, MIXING DEVICE, MIXING METHOD, AND CONTROL METHOD
    50.
    发明专利
    INJECTION DEVICE FOR INJECTING FLOW OF PRIMARY FLUID INTO FLOW OF SECONDARY FLUID, MIXING DEVICE, MIXING METHOD, AND CONTROL METHOD 审中-公开

    公开(公告)号：JP2006322458A

    公开(公告)日：2006-11-30

    申请号：JP2006137181

    申请日：2006-05-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BERTOLOTTI FABIO P ,  LISCINSKY DAVID S ,  SABATINO DANIEL R

    IPC: B67D7/74 ,  F02C7/18 ,  F02C6/18 ,  F02K1/28

    Abstract: PROBLEM TO BE SOLVED: To optimize mixing characteristic of two fluids crossing in a jet engine part orthogonally. SOLUTION: In an air mixing device for mixing primary fluid with secondary fluid introduced through an opening part of a wall and flowing on a wall face, the opening part has an airfoil shape provided with a leading edge oriented at a certain angle of attack with respect to secondary fluid flow to promote penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening part is selectively positioned to give desired lift for optimizing mixing of two streams by the angle of attack in accordance with the particular application. In one embodiment, a collar is provided around the opening part to prevent secondary fluid from coming into contact with the wall face during certain operation condition. A plurality of opening parts may be used by combination of a large size airfoil-shaped opening part and a small size airfoil-shaped opening part arranged on the downstream side more than it and combination of the airfoil-shaped opening part and a round-shaped opening part arranged on the upstream side more than it. A pair of opening parts and associated collars may be symmetrically arranged to promote mixture in specific application, and a nozzle may be arranged on an inner side of a wall to improve stream characteristic of primary fluid. COPYRIGHT: (C)2007,JPO&INPIT

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