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    INTERCOOLED COOLING AIR WITH PLURAL HEAT EXCHANGERS
    62.
    发明申请
    INTERCOOLED COOLING AIR WITH PLURAL HEAT EXCHANGERS 审中-公开
    具有多个热交换器的隔热冷却空气

    公开(公告)号：US20160312711A1

    公开(公告)日：2016-10-27

    申请号：US14745567

    申请日：2015-06-22

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

    IPC: F02C9/18 ,  F01D25/12 ,  F02K3/06 ,  F02C7/18 ,  F02C7/143 ,  F02C3/04

    CPC classification number: F02C9/18 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02K3/06 ,  F04D29/5826 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passing the tapped air through a first heat exchanger and then to a cooling compressor. A second tap taps air from a location closer to the downstream most end than the location of the first tap, and the first and second taps mix together and are delivered into the high pressure turbine. The cooling compressor is positioned downstream of the first heat exchanger, and upstream of a location where air from the first and second taps mix together.

    Abstract translation: 燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 第一分接头从主压缩机部分中的更上游位置中的至少一个抽头抽吸空气，使抽头的空气通过第一热交换器，然后到冷却压缩机。 第二分接头从比第一抽头的位置更靠近下游最端部的位置敲击空气，并且第一和第二抽头混合在一起并被输送到高压涡轮机中。 冷却压缩机位于第一热交换器的下游，并且位于将来自第一和第二抽头的空气混合在一起的位置的上游。

    MOUNTING SYSTEMS FOR GAS TURBINE ENGINES
    63.
    发明申请
    MOUNTING SYSTEMS FOR GAS TURBINE ENGINES 审中-公开
    气体涡轮发动机安装系统

    公开(公告)号：US20160238032A1

    公开(公告)日：2016-08-18

    申请号：US15023289

    申请日：2014-08-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James D. Hill ,  Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F04D29/64 ,  F04D29/52 ,  F01D25/24 ,  F04D29/32

    CPC classification number: F04D29/644 ,  B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F01D25/243 ,  F02C7/20 ,  F04D29/324 ,  F04D29/522 ,  F05D2220/32 ,  Y02T50/44 ,  Y02T50/671

    Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.

    Abstract translation: 用于燃气涡轮发动机的安装系统包括压缩机壳体部分，入口框架，出口框架和安装结构。 压缩机壳体部分容纳可旋转的压缩机叶片。 入口框架连接到压缩机壳体的入口端。 出口框架在与压缩机壳体入口端相对的端部处连接到压缩机壳体部分的出口端。 安装结构的轴向前部安装结构连接到入口框架。 安装结构的轴向后部安装结构连接到出口框架。 安装结构的桥接结构偏离压缩机壳体并且连接前后安装结构，从而跨过入口和出口框架桥接发动机负载，以减少压缩机壳体部分的负载引起的变形。

    MIXING PLENUM FOR SPOKED ROTORS
    65.
    发明申请
    MIXING PLENUM FOR SPOKED ROTORS 有权
    混合转子的混合气体

    公开(公告)号：US20160186571A1

    公开(公告)日：2016-06-30

    申请号：US14797923

    申请日：2015-07-13

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

    IPC: F01D5/08 ,  F01D5/34 ,  F04D29/58 ,  F01D25/00 ,  F04D29/32 ,  F01D5/06 ,  F01D5/12

    CPC classification number: F01D5/087 ,  F01D5/06 ,  F01D5/081 ,  F01D5/12 ,  F01D5/34 ,  F01D11/006 ,  F01D25/005 ,  F01D25/12 ,  F04D29/321 ,  F04D29/58 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/30 ,  F05D2260/20 ,  F05D2300/175 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A gas turbine engine may comprise a first rotor with a primary flowpath along an outer diameter of the first rotor. A secondary flowpath may be radially inward from the primary flowpath. The secondary flowpath may pass through an opening through the first rotor. A blade may be disposed on a distal end of the first rotor. The blade may extend into the primary flowpath. A bleed tube may be in a wall of the primary flowpath and forward of the blade. The bleed tube may extend radially inward from the primary flowpath. The bleed tube may fluidly connect to the opening through the first rotor. A plenum may be aft of the blade and radially inward from the primary flowpath. The plenum may be fluidly connected to the opening through the first rotor. A second rotor may be aft of the plenum.

    Abstract translation: 燃气涡轮发动机可以包括具有沿着第一转子的外径的主流路的第一转子。 二次流路可以从主流路径向向内。 二次流路可穿过第一转子的开口。 叶片可以设置在第一转子的远端上。 叶片可以延伸到主流路。 放气管可以在主流路的壁中并且在叶片的前方。 排放管可以从主流路径向向内延伸。 排放管可以通过第一转子流体连接到开口。 集气室可以是叶片后部并且从主流路径向向内。 气室可以通过第一转子流体连接到开口。 第二转子可能是集气室的后部。

    SIMPLIFIED ENGINE BLEED SUPPLY WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    66.
    发明申请
    SIMPLIFIED ENGINE BLEED SUPPLY WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 审中-公开
    用于飞机的低压环境控制系统的简化发动机供应

    公开(公告)号：US20160177819A1

    公开(公告)日：2016-06-23

    申请号：US14751314

    申请日：2015-06-26

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C3/06

    CPC classification number: F02C6/08 ,  B64D2013/0618 ,  Y02T50/56

    Abstract: A gas turbine engine assembly for an aircraft includes a fan section delivering air into a main compressor section. The main compressor section includes a first compressor section and a second compressor section operating at a higher pressure than the first compressor section. The main compressor section compresses air and delivers air into a combustion section where the air is mixed with fuel and ignited to generate products of combustion that are passed over a turbine section to drive the fan section and main compressor sections. An environmental control system includes a low pressure tap at a location on the first compressor section of the main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use. An environmental control system is also disclosed.

    Abstract translation: 用于飞机的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。 主压缩机部分包括在比第一压缩机部分更高的压力下操作的第一压缩机部分和第二压缩机部分。 主压缩机部分压缩空气并将空气输送到空气与燃料混合并点燃的燃烧部分中，以产生通过涡轮部分驱动风扇部分和主压缩机部分的燃烧产物。 环境控制系统包括在主压缩机部分的第一压缩机部分上的位置处的低压抽头。 低压龙头将气流连通到通向下游出口的第一通道。 压缩机由电动机驱动。 组合的出口将来自第一通道和来自由电动机驱动的压缩机的气流混合，并将下游的气流传递给飞行器使用。 还公开了一种环境控制系统。

    SYSTEM AND METHOD FOR CONTROLLING AN ENVIRONMENTAL CONDITION OF AN ENGINE ELECTRONIC COMPONENT
    67.
    发明申请
    SYSTEM AND METHOD FOR CONTROLLING AN ENVIRONMENTAL CONDITION OF AN ENGINE ELECTRONIC COMPONENT 审中-公开
    用于控制发动机电子部件的环境条件的系统和方法

    公开(公告)号：US20160177781A1

    公开(公告)日：2016-06-23

    申请号：US14974808

    申请日：2015-12-18

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Kurt J. Sobanski ,  Wesley K. Lord ,  William K. Ackermann

    IPC: F01D25/10 ,  F02C3/04

    CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F02C7/32 ,  F02K3/115 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/675

    Abstract: The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to receive the fanstream flowing therethrough. An engine electronic component is positioned in flow communication with the fanstream. A heating element is positioned in the fanstream upstream from the engine electronic component and is operative to heat at least a portion of the fanstream in flow communication with the engine electronic component. The position of the engine electronic component passively thermally conditions the engine electronic component and the heating element actively thermally conditions the engine electronic component.

    Abstract translation: 本公开一般涉及一种燃气涡轮发动机，其包括被配置为产生风扇流的风扇和被配置为接收流过其中的风扇流的风扇流管。 发动机电子部件被定位成与风扇流动地流动连通。 加热元件位于发动机电子部件上游的风扇流中，并且可操作地加热与发动机电子部件流动连通的风扇流的至少一部分。 发动机电子部件的位置被动地热调节发动机电子部件和加热元件，使发动机电子部件发热。

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