BYPASS DUCT HEAT EXCHANGER WITH CONTROLLED FAN
    57.
    发明申请
    BYPASS DUCT HEAT EXCHANGER WITH CONTROLLED FAN 有权
    旁路导管换热器与控制风扇

    公开(公告)号:US20160369706A1

    公开(公告)日:2016-12-22

    申请号:US14745606

    申请日:2015-06-22

    Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.

    Abstract translation: 燃气涡轮发动机包括将空气输送到旁通管道并进入核心发动机的主风扇。 热交换器定位在旁路管道内,并从与燃气涡轮发动机相关联的部件接收待冷却的流体。 定位热交换器风扇以抽吸空气穿过热交换器和用于热交换器风扇的控制。 控制器被编程为在某些条件下停止风扇的运行,并在其他条件下驱动热交换器风扇。 还公开了形成热交换器的方法。

    INTERCOOLED COOLING AIR WITH PLURAL HEAT EXCHANGERS
    59.
    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

    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
    60.
    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

    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。

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