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    Integrated Environmental Control System Manifold
    375.
    发明申请
    Integrated Environmental Control System Manifold 审中-公开
    综合环境控制系统歧管

    公开(公告)号：US20170044991A1

    公开(公告)日：2017-02-16

    申请号：US15118565

    申请日：2014-09-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C9/18 ,  F01D25/24 ,  F04D29/54 ,  F02C7/052 ,  F04D29/52 ,  F04D29/58

    CPC classification number: F02C9/18 ,  F01D25/162 ,  F01D25/24 ,  F02C6/08 ,  F02C7/052 ,  F02C7/25 ,  F04D29/522 ,  F04D29/542 ,  F04D29/5853 ,  F04D29/701 ,  F05D2220/32 ,  F05D2240/15

    Abstract: A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.

    Abstract translation: 用于燃气涡轮发动机的压缩机中间壳体包括将压缩机中间壳体连接到内部发动机结构的多个中间壳体支柱。 多个中间壳支柱的每个支柱包括前缘。 在多个中间壳支柱的每个支柱的前缘设置有转向铲。 多个扩散器从压缩机中间壳体径向向外延伸，使得多个扩散器的每个扩散器与相应的转向勺接合。 大致环形的结构防火墙从压缩机中间壳径向向外延伸。 环境控制系统歧管设置在压缩机中间壳体上。 环境控制系统歧管包括出口。

    ADVANCED DISTRIBUTED ENGINE ARCHITECHTURE - DESIGN ALTERNATIVE
    376.
    发明申请
    ADVANCED DISTRIBUTED ENGINE ARCHITECHTURE - DESIGN ALTERNATIVE 审中-公开
    高级分布式发动机结构 - 设计替代

    公开(公告)号：US20170002735A1

    公开(公告)日：2017-01-05

    申请号：US14789036

    申请日：2015-07-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Jeffery F. Perlak ,  Joseph B. Staubach ,  Gabriel L. Suciu ,  James D. Hill ,  Frederick M. Schwarz

    IPC: F02C3/107

    CPC classification number: F02C3/107 ,  F02C3/10 ,  F02C3/145 ,  F05D2210/44 ,  F05D2260/4031

    Abstract: A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.

    Abstract translation: 根据本公开的燃气涡轮发动机包括第一压缩机和用于驱动第一压缩机的第一涡轮机。 核心部分包括用于驱动第二压缩机的第二压缩机和第二涡轮机。 第三涡轮机布置在第一涡轮机和第二涡轮机的流体下游并被配置成驱动动力输出。 第一管道系统流体地布置在低压压缩机和铁芯段之间。 第一管道系统布置成在进入核心部分之前逆转流体流动。

    NACELLE VENTILATION MANIFOLD
    377.
    发明申请
    NACELLE VENTILATION MANIFOLD 审中-公开
    通风通风口

    公开(公告)号：US20160333728A1

    公开(公告)日：2016-11-17

    申请号：US15111553

    申请日：2015-01-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

    IPC: F01D17/14 ,  F01D25/26 ,  F02C9/18 ,  F02C3/04 ,  F02C7/18

    CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

    Abstract translation: 一种燃气涡轮发动机包括一个核心发动机壳体。 机舱位于核心发动机壳体的径向外侧。 外部旁路外壳位于机舱的外侧。 至少有一个待冷却的附件定位在径向位于核心发动机壳体和机舱之间的腔室中。 歧管将冷却空气提供到腔室中，并且围绕核心发动机的中心轴线周向延伸。 机舱在圆周范围内具有不对称的流动横截面。

    AIRCRAFT THERMAL MANAGEMENT SYSTEM
    379.
    发明申请
    AIRCRAFT THERMAL MANAGEMENT SYSTEM 审中-公开
    飞机热管理系统

    公开(公告)号：US20160280387A1

    公开(公告)日：2016-09-29

    申请号：US14667975

    申请日：2015-03-25

    Applicant: United Technologies Corporation

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

    IPC: B64D33/02

    CPC classification number: F02C7/14 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/98 ,  Y02T50/671 ,  Y02T50/675

    Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

    Abstract translation: 飞机热管理系统包括第一流体系统，其包含第一流体，包含热中性传热流体的流体回路，包含第二流体的第二流体系统，被配置为将热量从第一流体传递到热 中性传热流体和被配置为将热量从热中性传热流体传递到第二流体的第二热交换器。 流体回路构造成以与第一流体的压力匹配的压力将热中性传热流体提供给第一热交换器。

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