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    Aircraft thermal management system
    1.
    发明授权
    Aircraft thermal management system 有权

    公开(公告)号：US11156161B2

    公开(公告)日：2021-10-26

    申请号：US16111870

    申请日：2018-08-24

    Applicant: United Technologies Corporation

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

    IPC: F02C7/14

    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.

    Segmented seal for gas turbine engine
    5.
    发明授权
    Segmented seal for gas turbine engine 有权

    公开(公告)号：US10287905B2

    公开(公告)日：2019-05-14

    申请号：US15036019

    申请日：2014-11-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F01D11/00 ,  F01D5/08 ,  F01D11/02 ,  F01D5/06 ,  F01D9/04

    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.

    INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE
    8.
    发明申请
    INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE 审中-公开
    多管脉冲爆震发动机的入口歧管

    公开(公告)号：US20160326956A1

    公开(公告)日：2016-11-10

    申请号：US15109049

    申请日：2014-12-19

    Applicant: United Technologies Corporation

    Inventor： James D. Hill ,  Michael J. Cuozzo

    IPC: F02C5/02 ,  F23R7/00 ,  F02C5/10

    CPC classification number: F02C5/02 ,  F02C5/10 ,  F02C6/08 ,  F23R7/00

    Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.

    Abstract translation: 用于多管脉冲爆震发动机的入口歧管包括设置在第一区域中的无叶漫射器，以收集从压缩机排出的空气; 一种叶片式扩散器，包括设置在第二区域中的多个导向叶片，以减缓来自压缩机的空气; 设置在靠近第二区域的第三区域中的气室，以将空气从压缩机提供到腔室; 以及设置在第四区域中以将来自压缩机的空气分成每个脉冲爆管所需的气流用于爆炸的分流器。

    MOUNTING SYSTEMS FOR GAS TURBINE ENGINES
    9.
    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。

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