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    SINGLE PHASE MICRO/MINI CHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING
    2.
    发明申请
    SINGLE PHASE MICRO/MINI CHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING 审中-公开
    单相微型/微型通道热交换器用于气体涡街机

    公开(公告)号：US20150240722A1

    公开(公告)日：2015-08-27

    申请号：US14625133

    申请日：2015-02-18

    Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

    Inventor： James C. Loebig ,  Emil R. Dejulio ,  Eric S. Donovan

    IPC: F02C7/18 ,  F02C3/04

    CPC classification number: F02C7/18 ,  F02C3/04 ,  F02C7/143 ,  F02K3/115 ,  F05D2220/3219 ,  F05D2230/11 ,  F05D2260/204 ,  F28D9/0037 ,  F28D2021/0026 ,  F28F3/048 ,  F28F9/026 ,  F28F2250/06 ,  F28F2260/02 ,  F28F2275/061

    Abstract: A gas turbine engine heat exchange system including a first multi-width channel heat exchanger (MWCHX) configured to transfer heat between a first air stream and a heat transfer fluid. The first MWCHX includes a first plurality of air-passage mini-channels configured to allow passage of the first air stream therethrough, where each air-passage channel has an air-channel width and an air-channel length greater than the air-channel width. The MWCHX also includes a first plurality of heat transfer fluid channels configured to allow passage of the heat transfer fluid therethrough, where each heat transfer fluid channel has a heat transfer channel width and a heat transfer channel length greater than the heat transfer channel width. The heat transfer channel width is less than the air-channel width.

    Abstract translation: 一种燃气涡轮发动机热交换系统，包括构造成在第一气流和传热流体之间传递热的第一多宽度通道热交换器（MWCHX）。 第一MWCHX包括构造成允许第一空气流通过的第一多个空气通道微通道，其中每个空气通道通道具有大于空气通道宽度的空气通道宽度和空气通道长度 。 MWCHX还包括构造成允许传热流体通过其中的第一多个传热流体通道，其中每个传热流体通道具有大于传热通道宽度的传热通道宽度和传热通道长度。 传热通道宽度小于空气通道宽度。

    FAN BY-PASS DUCT FOR INTERCOOLED TURBO FAN ENGINES
    5.
    发明申请
    FAN BY-PASS DUCT FOR INTERCOOLED TURBO FAN ENGINES 审中-公开
    风扇旁路导管用于混合涡轮风扇发动机

    公开(公告)号：US20160222886A1

    公开(公告)日：2016-08-04

    申请号：US14709826

    申请日：2015-05-12

    Applicant: Rolls-Royce North American Technologies, Inc.

    Inventor： Bradford J. Riehle ,  James C. Loebig

    IPC: F02C7/143 ,  F02K3/02 ,  F02C7/18 ,  F02K3/105

    CPC classification number: F02C7/143 ,  F02C7/18 ,  F02K3/02 ,  F02K3/077 ,  F02K3/105 ,  F02K3/115 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/204 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

    Abstract: An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

    Abstract translation: 一种用于中间冷却涡轮风扇发动机的改进的系统，装置和方法，更具体地说，一种用于使使用最小化压力损失的次级旁通管道的涡轮风扇发动机中间冷却的系统。 次级旁通管道从风扇旁路管径向向内设置，并通过入口接收风扇旁路空气。 风扇旁路空气的一部分流过一个或多个微通道或微通道热交换器。 次级旁通管道具有与风扇旁路喷嘴的喉部下游的旁路空气流连通的出口。 次级旁路空气在出口加速以产生推力。

    GAS TURBINE ENGINE COMBUSTOR LINER
    7.
    发明申请
    GAS TURBINE ENGINE COMBUSTOR LINER 有权
    燃气轮机发动机内燃机

    公开(公告)号：US20150013340A1

    公开(公告)日：2015-01-15

    申请号：US14142604

    申请日：2013-12-27

    Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

    Inventor： Donald E. Pinnick ,  Kenneth W. Froemming ,  Bruce E. Varney ,  James C. Loebig ,  Todd Taylor

    IPC: F23R3/00

    CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/10 ,  F23R2900/00018 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

    Abstract translation: 燃气轮机发动机可变孔隙度燃烧器衬套具有层压合金结构。 层叠合金结构在一侧具有面向燃烧室的燃烧室和在径向相对侧的面向孔的冷却气室。 燃烧室对着的孔通过夹在层压合金结构的金属合金板之间的轴向和周向延伸的流动通道与冷却气室相对的孔流体连通。 基于燃烧室相对孔的布置，冷却气室相对孔的布置和流动通道的布置中的至少一个，在层压允许结构中形成具有各自不同冷却流量的多孔区。

    VORTEX TUBE PARTICLE SEPARATORS WITH COATINGS FOR REBOUND CONTROL
    8.
    发明申请
    VORTEX TUBE PARTICLE SEPARATORS WITH COATINGS FOR REBOUND CONTROL 有权

    公开(公告)号：US20250101914A1

    公开(公告)日：2025-03-27

    申请号：US18371812

    申请日：2023-09-22

    Applicant: Rolls-Royce North American Technologies Inc.

    Inventor： James C. Loebig

    IPC: F02C7/052 ,  B01D45/16 ,  B04C3/00

    Abstract: A vortex particle separator adapted for use with a gas turbine engine includes a vortex tube, a plurality of swirl vanes, and an outlet tube. The vortex tube receives atmospheric air laden with particles. The plurality of swirl vanes are arranged within the vortex tube and separate the atmospheric air into a first flow of air having the particles and a second flow of air that is relatively free of the particles. The outlet tube extends into the vortex tube to define a scavenge passageway between the outlet tube and the vortex tube that receives the first flow of air. The outlet tube defines an intake passageway that receives the second flow of air. The vortex particle separator further includes a layer of material having a low coefficient of restitution on at least one of an interior surface of the vortex tube and a surface of the swirl vanes.

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