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234 条记录 (耗时 0.017 秒)

    Gas turbine combustor
    1.
    发明授权
    Gas turbine combustor 有权

    公开(公告)号：EP2725301B1

    公开(公告)日：2018-12-05

    申请号：EP13188698.8

    申请日：2013-10-15

    申请人： Ansaldo Energia Switzerland AG

    发明人： Ciani, Andrea ,  Wood, John Philip ,  Pennell, Douglas Anthony ,  Freitag, Ewald ,  Benz, Urs ,  Theuer, Andre

    IPC分类号： F23R3/16 ,  F23R3/20 ,  F23R3/28 ,  F23R3/34 ,  F23R3/36 ,  F23R3/46

    CPC分类号： F23R3/16 ,  F02C6/003 ,  F02C9/26 ,  F02C9/32 ,  F02C9/34 ,  F05B2260/222 ,  F23R3/20 ,  F23R3/286 ,  F23R3/34 ,  F23R3/346 ,  F23R3/36 ,  F23R3/46 ,  F23R2900/03341

    摘要： The present invention relates to a burner for a combustion chamber of a gas turbine with a mixing and injection device (43), wherein the mixing and injection device (43) is comprising a limiting wall (44) that defines a gas-flow channel (440) and at least two streamlined bodies (22), each extending in a first transverse direction (49) into the gas-flow channel (440). Each streamlined body (22) has two lateral surfaces that are arranged essentially parallel to the main-flow direction (14), the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body (22). Each streamlined body (22) has a cross-section perpendicular to the first transverse direction (49) that is shaped as a streamlined profile. At least one of said streamlined bodies (22) is provided with a mixing structure and with at least one fuel nozzle (15) located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction (14) into the flow channel (440), wherein at least two of the streamlined bodies (22) have different lengths along the first transverse direction (49) such that they may be used for a can combustor.

    JET ENGINE AND FLYING OBJECT
    2.
    发明公开
    JET ENGINE AND FLYING OBJECT 审中-公开

    公开(公告)号：EP3396145A1

    公开(公告)日：2018-10-31

    申请号：EP16894474.2

    申请日：2016-06-22

    申请人： Mitsubishi Heavy Industries, Ltd.

    发明人： HIROKANE, Mariko ,  ANDO, Keisuke ,  UENO, Yoshihiko

    IPC分类号： F02K7/10 ,  F02C7/00 ,  F02C7/26

    CPC分类号： F23R3/28 ,  F02C7/00 ,  F02C7/26 ,  F02K7/10 ,  F05D2220/10 ,  F05D2240/35 ,  F23R3/10 ,  F23R3/20 ,  F23R3/42 ,  F23R2900/00015

    摘要： A jet engine is provided with an inlet 11 and a combustor 12 having a fuel injection port 30a. The combustor 12 has a wall part 16 that defines an air flow path FA. The wall part 16 has a ramp part 60, which has an inclined face 62, and a first wall face 17 extending to the front-side end of the inclined face 62. The fuel injection port 30a is positioned at the ramp part 60. The inclination angle θ relative to the first wall face 17 of the inclined face 62 is at least 13.5 degrees. The height by which the ramp part 60 protrudes from the first wall face 17 does not exceed one fifth of the height of the inlet of the combustor 12. Thus provided are a jet engine and a flying object in which the inclination angle of the inclined face of a ramp is made larger so as to promote the mixing of fuel and air and to allow for stable flame holding at the rear of the ramp.

    INJECTOR DEVICE AND METHOD FOR MANUFACTURING AN INJECTOR DEVICE
    5.
    发明公开
    INJECTOR DEVICE AND METHOD FOR MANUFACTURING AN INJECTOR DEVICE 审中-公开
    注射装置和用于制造注射装置的方法

    公开(公告)号：EP3285006A1

    公开(公告)日：2018-02-21

    申请号：EP17185270.0

    申请日：2017-08-08

    申请人： Ansaldo Energia Switzerland AG

    发明人： STYTSENKO, Alexey ,  MYLNIKOV, Sergey ,  BAIBUZENKO, Igor ,  MAURER, Michael

    IPC分类号： F23R3/20 ,  F02C7/22 ,  F23R3/28

    CPC分类号： F23R3/36 ,  F02C3/04 ,  F02C7/22 ,  F05D2220/32 ,  F05D2230/31 ,  F23C2900/07001 ,  F23R3/20 ,  F23R3/28 ,  F23R2900/00018

    摘要： The injector device (1) comprises an elongated body (2) with a leading edge (3) and a trailing edge (4), gas nozzles (7) and oil nozzles (8), an oil supply duct (10) housed within the elongated body (2) and connected to the oil nozzles (8), a gas supply duct (11) housed within the elongated body (2) and connected to the gas nozzles (7). The oil supply duct (10) is connected to the gas supply duct (11) only between one or more oil nozzles (8) and one gas nozzles (7), and the gas supply duct (11) is connected to the elongated body (2) only via bridges (13).

    摘要翻译： 该注射器装置（1）包括具有前缘（3）和后缘（4），气体喷嘴（7）和油喷嘴（8）的细长主体（2），容纳在 （2）连接并且与油喷嘴（8）连接;气体供应导管（11），容纳在细长主体（2）内并连接到气体喷嘴（7）。 供油管道10仅在一个或多个油喷嘴8与一个气体喷嘴7之间与供气管道11连接，供气管道11与伸长体连接， 2）只能通过桥梁（13）。

    A COMBUSTION CHAMBER
    7.
    发明公开
    A COMBUSTION CHAMBER 审中-公开
    燃烧室

    公开(公告)号：EP3276263A1

    公开(公告)日：2018-01-31

    申请号：EP17178733.6

    申请日：2017-06-29

    申请人： Rolls-Royce plc

    发明人： HUCKER, Paul ,  HARDING, Stephen

    IPC分类号： F23R3/00 ,  F23R3/60

    CPC分类号： F23R3/20 ,  F23R3/002 ,  F23R3/08 ,  F23R3/44 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00005

    摘要： A gas turbine engine combustion chamber (15) comprises upstream and downstream ring structures (43, 54, 56) and a plurality of circumferentially arranged combustion chamber segments (58, 60). Each segment (58, 60) extends the full length of the combustion chamber (15) and each segment (58, 60) is secured to the upstream ring structure (43) and is mounted on the downstream ring structure (54, 56). The upstream end of each combustion chamber segment (58, 60) comprises a surface having a plurality of circumferentially spaced radially extending holes (118) and the upstream ring structure (43A, 43B) having a plurality of circumferentially spaced holes (116A, 116B) extending radially through a portion abutting the surface of the upstream end of each combustion chamber segment (58, 60). Each combustion chamber segment (58, 60) being removably secured to the upstream ring structure (43A, 43B) by a plurality of fasteners (120) locatable in the holes (118) in the combustion chamber segment (58, 60) and corresponding holes (116A, 116B) in the upstream ring structure (43A, 43B).

    摘要翻译： 燃气涡轮发动机燃烧室（15）包括上游和下游环形结构（43,54,56）和多个沿圆周布置的燃烧室段（58,60）。 每个节段58,60延伸燃烧室15的整个长度，并且每个节段58,60固定在上游环形结构43上并安装在下游环形结构54,56上。 每个燃烧室区段（58,60）的上游端包括具有多个周向间隔的径向延伸孔（118）的表面，并且上游环结构（43A，43B）具有多个沿周向间隔开的孔（116A，116B） 径向延伸穿过邻接每个燃烧室段（58,60）的上游端的表面的部分。 每个燃烧室区段58,60通过可位于燃烧室区段58,60中的孔118中的多个紧固件120可拆卸地固定到上游环形结构43A和43B， （116A，116B）位于上游环形结构（43A，43B）中。

    BURNER FOR A SEQUENTIAL COMBUSTION CHAMBER
    8.
    发明公开
    BURNER FOR A SEQUENTIAL COMBUSTION CHAMBER 审中-公开

    公开(公告)号：EP3184899A8

    公开(公告)日：2017-12-13

    申请号：EP16207652.5

    申请日：2013-10-15

    申请人： General Electric Technology GmbH

    发明人： CIANI, Andrea ,  WOOD, John Philip ,  PENNELL, Douglas Anthony ,  FREITAG, Ewald ,  BENZ, Urs ,  THEUER, Andre

    IPC分类号： F23R3/20 ,  F23R3/28 ,  F23R3/46

    CPC分类号： F23R3/16 ,  F05B2260/222 ,  F23R3/20 ,  F23R3/286 ,  F23R3/34 ,  F23R3/346 ,  F23R3/36 ,  F23R3/46 ,  F23R2900/03341

    摘要： A streamlined body (22) having two lateral surfaces that are arranged essentially parallel to a main-flow direction with a central plane therebetween, wherein the lateral surfaces are joined to one another at upstream sides of the lateral surfaces to form a leading edge of the body and are joined at downstream sides of the lateral surfaces to form a trailing edge (24) of the body,
    the streamlined body (22) extending perpendicularly to the main-flow direction and along a first transverse direction, and having a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile, and being provided with a mixing structure and with at least one fuel nozzle located at the trailing edge,
    wherein the mixing structure is provided in form of a plurality of lobes located at the trailing edge (24) of the body, wherein each lobe extends substantially perpendicular to said central plane in a second transverse direction or a third transverse directions, wherein the second and third transverse directions run oppositely to one another, wherein the lobe side walls comprise straight sections such that a lobing trailing edge (24) is provided which comprises straight sections.

    AFTERBURNER AND AIRCRAFT ENGINE
    9.
    发明公开
    AFTERBURNER AND AIRCRAFT ENGINE 审中-公开
    NACHBRENNER UND FLUGZEUGTRIEBWERK

    公开(公告)号：EP3101259A4

    公开(公告)日：2017-10-04

    申请号：EP15785388

    申请日：2015-04-27

    申请人： IHI CORP

    发明人： TANAKA SHINJI ,  TAKAHASHI KATSUYOSHI ,  HOSOI JUN

    IPC分类号： F02K3/10 ,  F23R3/20

    CPC分类号： F23R3/18 ,  F01D25/24 ,  F01D25/305 ,  F02K1/822 ,  F02K3/10 ,  F05D2220/323 ,  F05D2240/35 ,  F23R3/20 ,  F23R3/28 ,  F23R3/286 ,  Y02T50/675

    摘要： The present embodiment sufficiently ensures the ignition stability and the flame-holding property of an afterburner 25 while suppressing a reduction in the engine efficiency of an aircraft engine 1. A flame holder 45 is disposed directly downstream of an injection hole 41 of a fuel injector 39 in a liner 31. The flame holder 45 comprises: a ring-shaped annulus flame-holding member 49 which is provided on the inner circumferential surface of the liner 31 and is capable of propagating a flame in the circumferential direction; and a plurality of radial flame-holding members 51 which are radially disposed inwards of the annulus flame-holding member 49 and are capable of propagating the flame in the radial direction. A guide ring 53 is provided inwards of the radial flame-holding members 51, and a ring-shaped guide channel 57 that guides a fuel-containing mixed gas in the downstream direction is formed between the outer peripheral surface of the guide ring 53 and the inner peripheral surface of the annulus flame-holding member 49.

    摘要翻译： 在抑制飞机发动机1的发动机效率降低的同时，本实施例充分确保了后燃器25的点火稳定性和火焰稳定性。火焰稳定器45直接布置在燃料喷射器39的喷射孔41的下游 火焰保持器45包括：环形的环形火焰保持构件49，其设置在衬套31的内周表面上并且能够在周向方向上传播火焰; 以及多个径向框架构件51，其径向地设置在环形框架构件49的内部并且能够沿着径向传播火焰。 导向环53设置在径向火焰保持部件51的内部，在导向环53的外周面与导向环53的外周面之间形成有向下游方向引导含燃料混合气体的环状的导向通道57。 环形火焰保持部件49的内周面。