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    COOLED COOLING AIR SYSTEM FOR A TURBOFAN ENGINE
    335.
    发明申请
    COOLED COOLING AIR SYSTEM FOR A TURBOFAN ENGINE 审中-公开
    用于涡轮发动机的冷却冷却空气系统

    公开(公告)号：US20170009657A1

    公开(公告)日：2017-01-12

    申请号：US14793119

    申请日：2015-07-07

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Paul W. Duesler

    IPC: F02C7/18 ,  F02K3/02 ,  F02C7/04

    Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.

    Abstract translation: 示例性的燃气涡轮发动机包括限定在发动机芯的风扇机舱和核心罩之间的风扇旁路管道。 发动机内核包括冷却的冷却空气系统，该冷却空气系统构造成从发动机核心内的扩散器处的主要流路泄漏接收冷却空气，并且被配置为向发动机芯内的至少一个部件提供冷却的冷却空气。 冷却的冷却空气系统包括空气 - 空气热交换器。

    Geared Turbofan With High Gear Ratio And High Temperature Capability
    336.
    发明申请
    Geared Turbofan With High Gear Ratio And High Temperature Capability 审中-公开
    具有高齿轮比和高温能力的齿轮涡轮风扇

    公开(公告)号：US20160237914A1

    公开(公告)日：2016-08-18

    申请号：US14624668

    申请日：2015-02-18

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C9/18 ,  F01D5/28 ,  F02C7/36 ,  F02C7/18 ,  F02C7/32 ,  F02K3/06 ,  F02C3/10

    CPC classification number: F02C9/18 ,  F01D5/28 ,  F01D5/286 ,  F02C3/10 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2300/175 ,  F05D2300/607 ,  Y02T50/671

    Abstract: A gas turbine engine comprises a fan rotor having blades with an outer diameter. The outer diameter is greater than or equal to 77 inches (196 centimeters) and less than or equal to 135 inches (343 centimeter). The fan rotor has less than or equal to 26 fan blades, and is driven by a fan drive turbine through a gear reduction. The gear reduction has a gear ratio of greater than 2.6:1. The fan rotor delivers air into a bypass duct as bypass air, and into a duct leading to a compressor rotor as core air. A ratio of bypass air to the core air is greater than or equal to 12:1. An upstream turbine rotor is upstream of the fan drive turbine and drives a compressor rotor. The upstream turbine rotor has at least two stages, and the fan drive turbine rotor has at least three stages. The turbine blades in at least one stage of the fan drive turbine rotor are provided with a performance enhancing feature, which is at least one of the blades being manufactured by a directionally solidified blade material. The blades are provided as single crystal blades, and have a radially outer platform provided with scalloping to reduce the weight of the blades. The blades are provided with cooling air.

    Abstract translation: 燃气涡轮发动机包括具有外径的叶片的风扇转子。 外径大于或等于77英寸（196厘米）且小于或等于135英寸（343厘米）。 风扇转子具有小于或等于26个风扇叶片，并通过齿轮减速由风扇驱动涡轮驱动。 齿轮减速比的传动比大于2.6：1。 风扇转子将空气作为旁路空气输送到旁通管道中，并进入作为核心空气通向压缩机转子的管道。 旁路空气与核心空气的比例大于或等于12：1。 上游涡轮转子在风扇驱动涡轮机的上游并驱动压缩机转子。 上游涡轮转子具有至少两个阶段，并且风扇驱动涡轮转子具有至少三个阶段。 在风扇驱动涡轮转子的至少一个级中的涡轮叶片设置有性能增强特征，其中至少一个叶片由定向凝固的叶片材料制造。 刀片设置为单晶刀片，并且具有设置有扇形的径向外侧平台，以减小叶片的重量。 叶片设有冷却空气。

    COMPRESSOR AREA SPLITS FOR GEARED TURBOFAN
    337.
    发明申请
    COMPRESSOR AREA SPLITS FOR GEARED TURBOFAN 审中-公开
    压缩机领域用于齿轮涡轮机

    公开(公告)号：US20160215730A1

    公开(公告)日：2016-07-28

    申请号：US15062514

    申请日：2016-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Paul H. Spiesman

    IPC: F02K3/06 ,  F01D5/14 ,  F02C3/10

    CPC classification number: F02K3/06 ,  F01D5/06 ,  F01D5/147 ,  F01D25/24 ,  F01D25/30 ,  F02C3/10 ,  F04D19/02 ,  F04D19/026 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/325 ,  F04D29/542 ,  F04D29/563 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2260/40311

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan rotor. The fan rotor includes a fan hub defining a first diameter at a leading edge of a fan blade. The fan blade defines a tip diameter at the leading edge, with a ratio of the fan hub diameter to the fan tip diameter being less than or equal to 0.40. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a fan drive turbine and a high pressure turbine. The fan drive turbine is configured to drive the fan section, and the high pressure turbine is configured to drive the high pressure compressor.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括包括风扇转子的风扇部分。 风扇转子包括在风扇叶片的前缘限定第一直径的风扇毂。 风扇叶片在前缘限定尖端直径，风扇轮毂直径与风扇叶片直径的比值小于或等于0.40。 压缩机部分包括低压压缩机和高压压缩机。 涡轮部分包括风扇驱动涡轮机和高压涡轮机。 风扇驱动涡轮机构造成驱动风扇部分，并且高压涡轮机构造成驱动高压压缩机。

    EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN
    338.
    发明申请
    EXHAUST NOZZLE ARRANGEMENT FOR GEARED TURBOFAN 审中-公开
    用于齿轮涡轮机的排气喷嘴装置

    公开(公告)号：US20160201570A1

    公开(公告)日：2016-07-14

    申请号：US14875762

    申请日：2015-10-06

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Robert E. Malecki

    IPC: F02C7/36 ,  F02K3/06 ,  F02C3/10

    CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D2033/0286 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/068 ,  F05D2220/36 ,  Y02T50/672

    Abstract: A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to drive a fan section including a fan, and a turbine configured to drive the geared architecture. The turbine has an exit point, and a diameter (Dt) defined as the radially outer diameter of a last blade airfoil stage in the turbine at the exit point. A nacelle at least partially surrounds a core engine housing. The fan configured to deliver air into a bypass duct is defined between the nacelle and the core engine housing. A core engine exhaust nozzle is downstream of the exit point, with a downstream most point of the core engine exhaust nozzle being defined at a distance (Lc or Ln) from the exit point.

    Abstract translation: 根据本公开示例的推进系统尤其包括被配置为驱动包括风扇的风扇部分和配置成驱动齿轮架构的涡轮机的齿轮架构。 涡轮机具有出口点，并且直径（Dt）被定义为涡轮机在出口处的最后叶片翼型段的径向外径。 机舱至少部分地围绕核心发动机壳体。 被配置为将空气输送到旁通管道中的风扇被限定在机舱和核心发动机壳体之间。 核心发动机排气喷嘴位于出口点的下游，核心发动机排气喷嘴的下游最点定义在距离出口点的距离（Lc或Ln）处。

    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    339.
    发明申请
    GEARED TURBOFAN ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 有权
    具有用于飞机的低压环境控制系统的齿轮涡轮发动机

    公开(公告)号：US20160169029A1

    公开(公告)日：2016-06-16

    申请号：US14751299

    申请日：2015-06-26

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F01D17/00 ,  F02C7/20 ,  F02C7/36 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14

    CPC classification number: F01D17/00 ,  F01D25/28 ,  F02C3/04 ,  F02C3/14 ,  F02C6/08 ,  F02C7/20 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18

    Abstract: A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. The pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed.

    Abstract translation: 燃气涡轮发动机组件包括将空气输送到主压缩机部分中的风扇部分。 主压缩机部分压缩空气并将空气输送到燃烧部分。 燃烧产物从燃烧部分通过涡轮部分，以驱动风扇部分和主要压缩机部分。 变速箱由涡轮部分驱动以驱动风扇部分。 塔架支撑燃气轮机。 环境控制系统包括在主压缩机部分中的较高压力位置处的较高压力分接头和在较低压力位置处的较低压力分接头。 较低压力位置处于比较高压力位置更低的压力。 低压抽头与通向涡轮压缩机的下游出口和压缩机部分的第一通道连通。 较高压力分接头进入涡轮压缩机的涡轮部分，使得较高压力分接头中的空气驱动涡轮部分，从而驱动涡轮压缩机的压缩机部分。 塔架包括最下表面，而较高压力的水龙头不会在包括最下表面的平面之上延伸。 涡轮压缩机的压缩机部分和涡轮部分的组合出口混合并通过下游以被输送到飞行器使用。 还公开了一种环境控制系统。

    GEARED TURBOFAN ENGINE GEARBOX ARRANGEMENT
    340.
    发明申请
    GEARED TURBOFAN ENGINE GEARBOX ARRANGEMENT 审中-公开
    齿轮式涡轮发动机齿轮箱装置

    公开(公告)号：US20160153356A1

    公开(公告)日：2016-06-02

    申请号：US15013125

    申请日：2016-02-02

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  William G. Sheridan

    IPC: F02C3/107 ,  F02C3/10 ,  F04D29/32 ,  F01D17/10 ,  F01D9/06 ,  F01D5/02 ,  F02C3/06 ,  F02C7/36

    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有多个风扇叶片的风扇部分。 多个风扇叶片在第一流路的第一内侧边界处具有顶尖半径Rt和内侧前缘半径Rh。 核心发动机包括构造成驱动第一压缩机的第一涡轮机和配置成驱动风扇部分的风扇驱动涡轮机。 还公开了一种设计燃气涡轮发动机的方法。

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