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    LUBRICATION SYSTEM WITH MULTIPLE LUBRICATION CIRCUITS
    52.
    发明申请
    LUBRICATION SYSTEM WITH MULTIPLE LUBRICATION CIRCUITS 审中-公开

    公开(公告)号：US20170362959A1

    公开(公告)日：2017-12-21

    申请号：US15187155

    申请日：2016-06-20

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Michael E. McCune

    IPC: F01D25/20 ,  F02C7/36 ,  F01D25/16 ,  F02C7/06

    CPC classification number: F01D25/20 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2260/98

    Abstract: A system for a turbine engine includes a first bearing, a second bearing, a first rotating assembly, a second rotating assembly, a first lubrication circuit and a second lubrication circuit. The first rotating assembly includes a first component rotatably supported by the first bearing. The second rotating assembly includes a second component rotatably supported by the second bearing. The first lubrication circuit includes a first pump and the first bearing. The first pump is driven by the first rotating assembly and configured to pump lubricant to the first bearing. The second lubrication circuit includes a second pump and the second bearing. The second pump is configured to pump lubricant to the second bearing. The second lubrication circuit is configured discrete from the first lubrication circuit.

    INTEGRATED ENVIRONMENTAL CONTROL AND BUFFER AIR SYSTEM
    55.
    发明申请
    INTEGRATED ENVIRONMENTAL CONTROL AND BUFFER AIR SYSTEM 审中-公开

    公开(公告)号：US20170284305A1

    公开(公告)日：2017-10-05

    申请号：US15089806

    申请日：2016-04-04

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

    IPC: F02C9/18 ,  B64D13/06 ,  F02C7/32 ,  F02C3/04 ,  F02C7/06

    Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into 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. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.

    SIMPLIFIED ENGINE BLEED SUPPLY WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT
    59.
    发明申请
    SIMPLIFIED ENGINE BLEED SUPPLY WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT 有权
    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：US20170022899A1

    公开(公告)日：2017-01-26

    申请号：US14120450

    申请日：2014-06-27

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

    IPC: F02C6/08 ,  F02C7/32 ,  F02C9/18

    CPC classification number: F02C6/08 ,  B64D13/04 ,  B64D2013/0644 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323

    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。

    BYPASS DUCT HEAT EXCHANGER WITH CONTROLLED FAN
    60.
    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

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler

    IPC: F02C9/18 ,  F02C7/14

    CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C7/06 ,  F02C7/14 ,  F02K3/115 ,  F05D2230/31 ,  F05D2260/213 ,  Y02T50/675

    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。

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