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    GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION AND MULTIPLE LOW PRESSURE TURBINE SECTIONS
    1.
    发明申请
    GAS TURBINE ENGINE WITH FAN-TIED INDUCER SECTION AND MULTIPLE LOW PRESSURE TURBINE SECTIONS 审中-公开
    具有风扇感应部分和多个低压涡轮部分的燃气轮机发动机

    公开(公告)号：WO2013165521A2

    公开(公告)日：2013-11-07

    申请号：PCT/US2013/026075

    申请日：2013-02-14

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard

    IPC: F01D5/04 ,  F01D5/02 ,  F02C7/04

    CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311

    Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的第一轴和围绕旋转轴线可旋转且相对于第一轴径向向外间隔开的第二轴。 变速机构由第二轴驱动。 风扇包括由变速机构驱动的风扇转子，使得风扇和第一轴以比第二轴慢的速度旋转。 至少有一个诱导阶段位于风扇的尾部，并与风扇转子连接以便旋转。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    2.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
    齿轮涡轮增压燃气轮机发动机结构

    公开(公告)号：WO2013116259A1

    公开(公告)日：2013-08-08

    申请号：PCT/US2013/023724

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC: F02K3/02 ,  F01D1/00

    CPC classification number: F02C7/32 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2260/40311 ,  Y02T50/671

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    Abstract translation: 燃气涡轮发动机通常包括风扇部分，压缩机部分，燃烧器部分和涡轮部分。 可使用诸如行星齿轮组件的减速装置来驱动风扇部分，使得风扇部分可以以不同于涡轮部分的速度旋转，从而提高发动机的整体推进效率。 在这样的发动机架构中，由涡轮区段中的一个驱动的轴向行星齿轮组件提供输入，该输入以不同于涡轮区段的速度驱动风扇区段，使得涡轮区段和风扇区段可以更靠近 最佳速度通过所描述和公开的燃气涡轮发动机的各种部件的公开特征的期望组合提供增加的性能属性和性能。

    GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY
    5.
    发明申请
    GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY 审中-公开
    齿轮涡轮机主要和二次喷嘴积分几何

    公开(公告)号：WO2014105237A2

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/061927

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KUPRATIS, Daniel Bernard ,  KOHLENBERG, Gregory A.

    CPC classification number: F02K3/075 ,  F01D21/045 ,  F02C7/32 ,  F02K1/04 ,  F05D2260/30 ,  F05D2260/311 ,  Y10T29/49245

    Abstract: A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.

    Abstract translation: 所公开的示例性齿轮涡扇发动机包括：风扇部分，其包括可围绕轴线旋转的多个风扇叶片和围绕发动机轴线限定的核心发动机部分。 核心引擎部分包括主喷嘴，主喷嘴包括主喷嘴后缘处的主外径和主后缘的主要最大内径。 旁通通道，二次喷嘴，其包括次级喷嘴后缘处的外径和次级后缘的次级最大内径。 主喷嘴的最大内径和主喷嘴后缘的外径之间的比率以及次级后缘的最大内径与次喷嘴后缘的外径之间的比率都是 小于约0.700。

    REVERSE CORE GEAR TURBOFAN
    6.
    发明申请
    REVERSE CORE GEAR TURBOFAN 审中-公开
    反转核心齿轮TURBOFAN

    公开(公告)号：WO2014007880A2

    公开(公告)日：2014-01-09

    申请号：PCT/US2013/033776

    申请日：2013-03-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KUPRATIS, Daniel Bernard ,  MOON, Francis R.

    CPC classification number: F02C6/02 ,  F01D17/141 ,  F02C3/05 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C3/145 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/065 ,  F02K3/075 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2250/36 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2270/053

    Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

    Abstract translation: 燃气涡轮发动机在轴向外部位置处具有风扇。 风扇围绕旋转轴线旋转。 风扇将空气输送到外部旁路管道中，并穿过定位在外部旁路管道径向内部的增压器风扇。 增压风扇将空气输送到径向中间管道中，并且穿过冷涡轮机进入径向内部核心管道，其被引导到压缩机中。 来自压缩机的空气沿着朝向风扇的方向轴向地流动通过燃烧器部分，并且在涡轮机部分的排气口被引导进入中间管道。 减速器通过风扇驱动涡轮部分驱动风扇。 还公开了一种方法。

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    8.
    发明申请
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开

    公开(公告)号：WO2013158187A1

    公开(公告)日：2013-10-24

    申请号：PCT/US2013/023603

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC: F02K3/075

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

    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

    LIGHTWEIGHT FAN DRIVING TURBINE
    9.
    发明申请
    LIGHTWEIGHT FAN DRIVING TURBINE 审中-公开
    轻型风扇驱动涡轮

    公开(公告)号：WO2013130280A1

    公开(公告)日：2013-09-06

    申请号：PCT/US2013/026255

    申请日：2013-02-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard

    IPC: F04B17/00

    CPC classification number: F01D5/284 ,  F01D5/225 ,  F01D5/28 ,  F01D5/3007 ,  F05D2300/174 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A gas turbine engine includes a shaft defining an axis of rotation and a fan driving turbine configured to drive the shaft. The fan driving turbine comprises a plurality of stages that are spaced apart from each other along the axis. Each stage includes a turbine disk comprised of a disk material and a plurality of turbine blades comprised of a blade material. The disk material and the blade material for one of the plurality of stages is selected based on a location of the one stage relative to the other stages of the plurality of stages.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴和构造成驱动轴的风扇驱动涡轮机。 风扇驱动涡轮机包括沿轴线彼此间隔开的多个级。 每个阶段包括由圆盘材料和由叶片材料构成的多个涡轮叶片组成的涡轮盘。 基于一级相对于多级的其他级的位置来选择用于多级中的一级的盘材料和刀片材料。

    GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE
    10.
    发明申请
    GEARED ARCHITECTURE WITH INDUCER FOR GAS TURBINE ENGINE 审中-公开
    具有用于气体涡轮发动机的电动机的齿轮架构

    公开(公告)号：WO2014143074A1

    公开(公告)日：2014-09-18

    申请号：PCT/US2013/033960

    申请日：2013-03-27

    Applicant: UNITED TECHNOLOGIES CORPORATION ,  KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    Inventor： KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

    IPC: F02C7/36 ,  F02C7/00 ,  F02K3/02

    CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2260/40311

    Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.

    Abstract translation: 燃气涡轮发动机包括围绕公共轴线旋转的第一和第二轴。 第一涡轮部分被支撑在第一轴上。 第二压缩机和涡轮机部分被支撑在第二轴上。 燃气涡轮发动机包括风扇。 第一压缩机部分与第二压缩机和第一和第二涡轮机以轴向流动关系布置。 齿轮架构可操作地连接第一轴和风扇。 诱导器操作耦合到齿轮系。

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