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    MICRO TURBINE GENERATOR WITH GUIDE VANE STRUCTURE
    3.
    发明申请
    MICRO TURBINE GENERATOR WITH GUIDE VANE STRUCTURE 审中-公开

    公开(公告)号：US20180172270A1

    公开(公告)日：2018-06-21

    申请号：US15385041

    申请日：2016-12-20

    申请人： NATIONAL CHUNG SHAN INSTITUTE OF SCIENCE AND TECHNOLOGY

    发明人： YUNG-MAO TSUEI ,  CHIH-CHUAN LEE

    IPC分类号： F23R3/02 ,  F02C3/14 ,  H02K7/18

    CPC分类号： F23R3/02 ,  F02C3/145 ,  F02C7/141 ,  F23C2900/03001 ,  H02K7/1823 ,  Y02T50/675

    摘要： A micro turbine generator includes a compressor, a guide channel, an expansion chamber, and a recuperator. The expansion chamber includes an air inlet, an air outlet, and a guide vane structure. The air inlet is disposed at one end of the expansion chamber, connected with the compressor through the guide channel, and receives an air compressed by the compressor. The air outlet is disposed at the other end of the expansion chamber, connected with the recuperator, and discharges the air, allowing the air to enter the recuperator. The guide vane structure extends inward from an inner wall of the expansion chamber to allow the air to pass the guide vane structure before being discharged from the air outlet to enter the recuperator.

    REVERSE FLOW GAS TURBINE ENGINE WITH OFFSET RGB
    5.
    发明申请
    REVERSE FLOW GAS TURBINE ENGINE WITH OFFSET RGB 审中-公开

    公开(公告)号：US20180073429A1

    公开(公告)日：2018-03-15

    申请号：US15407401

    申请日：2017-01-17

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Jean DUBREUIL

    IPC分类号： F02C3/107 ,  F02C7/36 ,  F02C7/32

    CPC分类号： F02C3/107 ,  F02C3/145 ,  F02C6/206 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/324 ,  F05D2220/329 ,  F05D2220/76 ,  F05D2260/53 ,  Y02T50/671

    摘要： A gas turbine engine has an engine case housing a low pressure compressor drivingly connected to a low pressure turbine by a low pressure compressor shaft extending along an engine axis. The low pressure turbine is disposed forward of the low pressure compressor. A low pressure turbine shaft is drivingly connected to the low pressure turbine and extends forwardly of the low pressure turbine. A reduction gear box (RGB) is drivingly connected to the low pressure turbine shaft. The RGB is offset from the engine axis to free an access to low pressure compressor shaft connection. The offset positioning of the RGB allows to provide an access port in an axially forwardly facing surface of the engine case to access the low pressure compressor shaft and more particularly a connection thereof to the LP turbine.

    GAS TURBINE COMBUSTION ACOUSTIC DAMPING SYSTEM
    8.
    发明申请
    GAS TURBINE COMBUSTION ACOUSTIC DAMPING SYSTEM 有权
    气体涡轮机燃烧阻尼系统

    公开(公告)号：US20150233580A1

    公开(公告)日：2015-08-20

    申请号：US14566963

    申请日：2014-12-11

    申请人： Andrew J. Olsen ,  Ivar Austrem ,  M. Serkan Yildirim ,  Zheji Liu

    发明人： Andrew J. Olsen ,  Ivar Austrem ,  M. Serkan Yildirim ,  Zheji Liu

    IPC分类号： F23R3/26 ,  F02C3/04

    CPC分类号： F02C7/24 ,  F01D5/02 ,  F02C3/04 ,  F02C3/145 ,  F02C7/18 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/201 ,  F05D2260/96 ,  F05D2260/963 ,  F05D2270/14 ,  F23R3/002 ,  F23R3/06 ,  F23R3/14 ,  F23R3/286 ,  F23R3/54 ,  F23R3/60 ,  F23R2900/00014 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044

    摘要： A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

    摘要翻译： 燃气轮机可以包括可旋转的轴，围绕可旋转轴布置并被构造成输出压缩空气的压缩机和围绕可旋转轴设置的燃烧器。 燃烧器可以构造成接收压缩空气并输出高温压缩气体。 燃气轮机还可以包括设置在可旋转轴周围并被配置为容纳高温压缩气体的动力涡轮机，以及限定多个孔并设置在燃烧器周围的第一衬套。 动力涡轮机可构造成膨胀高温压缩气体并旋转可旋转轴。 第一衬垫可以具有第一端和纵向相对的第二端。 第一端可以在燃烧器的上游端处或邻近燃烧器的上游端处联接到壳体的内表面，并且第二端可以基本上没有与壳体的任何连接。

    GAS TURBINE ENGINE EXHAUST FLUID PASSAGE DUCT
    9.
    发明申请
    GAS TURBINE ENGINE EXHAUST FLUID PASSAGE DUCT 有权
    气体涡轮发动机排气流量通道

    公开(公告)号：US20140260325A1

    公开(公告)日：2014-09-18

    申请号：US14206798

    申请日：2014-03-12

    申请人： Rolls-Royce Corporation

    发明人： John M. Roach, III

    IPC分类号： F01D25/30

    CPC分类号： F01D25/30 ,  F01D9/023 ,  F02C3/145 ,  Y10T137/0318 ,  Y10T137/0536

    摘要： A fluid plenum including a body defining an internal cavity having an inlet and an outlet. The fluid plenum further includes at least one wall positioned in the internal cavity that divides the internal cavity into first and second passageways, and which also divides the inlet into first and second inlet portions, and divides the outlet into first and second outlet portions. The first passageway receives fluid through the first inlet portion and directs fluid to the first outlet portion, and the second passageway receives fluid through the second inlet portion and directs fluid to the second outlet portion. The first and second passageways extend first and second lengths that are different from one another, and also generate a substantially common back-pressure at the first and second inlet portions during flow of a fluid stream through the inlet, including a first sub-stream of the fluid stream through the first passageway and a second sub-stream of the fluid stream through the second passageway.

    摘要翻译： 流体增压室包括限定具有入口和出口的内部空腔的主体。 流体增压室还包括定位在内腔中的至少一个壁，其将内腔分成第一和第二通道，并且还将入口分成第一和第二入口部分，并将出口分成第一和第二出口部分。 第一通道通过第一入口部分接收流体并将流体引导到第一出口部分，并且第二通道接收通过第二入口部分的流体并将流体引导到第二出口部分。 第一和第二通道延伸彼此不同的第一和第二长度，并且还在流体流通过入口的流动期间在第一和第二入口部分处产生基本上常见的背压，包括第一和第二子流 通过第一通道的流体流和通过第二通道的流体流的第二子流。

    Gas Turbine Engine with Stream Diverter
    10.
    发明申请
    Gas Turbine Engine with Stream Diverter 有权
    燃气轮机发动机与流转向器

    公开(公告)号：US20140260180A1

    公开(公告)日：2014-09-18

    申请号：US13937670

    申请日：2013-07-09

    申请人： United Technologies Corporation

    发明人： Daniel Bernard Kupratis ,  Francis R. Moon

    IPC分类号： F02K3/075

    CPC分类号： F02K3/075 ,  F02C3/13 ,  F02C3/145 ,  F02C9/18 ,  F02K1/80 ,  F02K3/06 ,  F02K3/077 ,  F05D2210/40 ,  F05D2250/311

    摘要： In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.

    摘要翻译： 根据本公开的一个方面，公开了一种用于燃气涡轮发动机的液流分流器。 流分流器可以包括第一空气管道，第二空气管道，第三空气管道和与燃气涡轮发动机的第二和第三空气管道可操作地相关联的门。 门可以具有至少一个打开位置，允许来自第二空气管道的空气流入第三空气管道和封闭位置，防止空气在管道之间流动。