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    • 21. 发明授权
    • Premixing direct injector
    • 预混喷射器
    • US08157189B2
    • 2012-04-17
    • US12417896
    • 2009-04-03
    • Thomas Edward JohnsonChristian Xavier StevensonWilliam David YorkWilly Steve Ziminsky
    • Thomas Edward JohnsonChristian Xavier StevensonWilliam David YorkWilly Steve Ziminsky
    • B05B15/00
    • F23D14/62F23R3/10F23R3/286F23R2900/00002
    • A fuel injection nozzle comprises a body member having an upstream wall opposing a downstream wall, a baffle member having an upstream surface and a downstream surface, a first chamber, a second chamber, a fuel inlet communicative with the first chamber operative to emit a first gas into the first chamber, and a plurality of mixing tubes, each of the mixing tubes having a tube inner surface, a tube outer surface, a first inlet communicative with an aperture in the upstream wall operative to receive a second gas, a second inlet communicative with the tube outer surface and the tube inner surface operative to translate the first gas into the mixing tube, a mixing portion operative to mix the first gas and the second gas, and an outlet communicative with an aperture in the downstream wall operative to emit the mixed first and second gasses.
    • 燃料喷射喷嘴包括主体构件,其具有与下游壁相对的上游壁,具有上游表面和下游表面的挡板构件,第一腔室,第二腔室,与第一腔室连通的燃料入口,其操作以发射第一 气体进入第一室,以及多个混合管,每个混合管具有管内表面,管外表面,与上游壁中的孔连通的第一入口,用于接收第二气体,第二入口 与管外表面和管内表面通信,其可操作以将第一气体平移到混合管中,混合部分可操作以混合第一气体和第二气体,以及与下游壁中的孔连通的出口,其可操作地发射 混合的第一和第二气体。
    • 26. 发明申请
    • Insulator bushing for combustion liner
    • 燃烧衬套绝缘套管
    • US20090235668A1
    • 2009-09-24
    • US12076385
    • 2008-03-18
    • Thomas Edward JohnsonMarcus B. Huffman
    • Thomas Edward JohnsonMarcus B. Huffman
    • F02C7/12F02C1/00
    • F01D9/023F23R3/06
    • A combustor for a turbine including: a combustor liner, a first flow sleeve surrounding the combustor liner to define a first flow annulus, the first flow sleeve having cooling holes for directing compressor discharge air as cooling air into the first flow annulus, a transition piece body connected to the combustor liner to carry hot combustion gases to the turbine; a second flow sleeve surrounding the transition piece body, the second flow sleeve having cooling holes for directing compressor discharge air as cooling air into a second flow annulus between the second flow sleeve and the transition piece body; at least one dilution hole in the combustor liner for flowing compressor air into a combustion chamber defined by the combustor liner; and a bushing seated in at least one of the cooling or dilution holes and secured with respect thereto for defining a flow passage for compressor discharge air through the hole.
    • 一种用于涡轮机的燃烧器,包括:燃烧器衬套,围绕所述燃烧器衬套以限定第一流动环空的第一流动套筒,所述第一流动套筒具有用于将压缩机排出的空气作为冷却空气引导到所述第一流动环空中的冷却孔, 连接到燃烧器衬套以将热燃烧气体携带到涡轮机; 围绕所述过渡件本体的第二流动套筒,所述第二流动套筒具有用于将压缩机排出空气作为冷却空气引导到所述第二流动套筒和所述过渡件本体之间的第二流动环空中的冷却孔; 在燃烧器衬套中的至少一个稀释孔,用于使压缩机空气流入由燃烧器衬套限定的燃烧室; 以及衬套,其位于冷却或稀释孔中的至少一个中并且相对于其固定,以限定用于压缩机排出空气的流动通道。
    • 28. 发明授权
    • Method and apparatus for cooling combustor liner and transition piece of a gas turbine
    • 一种用于冷却燃气轮机的燃烧器衬套和过渡件的方法和装置
    • US07493767B2
    • 2009-02-24
    • US10907866
    • 2005-04-19
    • Ronald Scott BunkerJeremy Clyde BaileyStanley Kevin WidenerThomas Edward JohnsonJohn C Intile
    • Ronald Scott BunkerJeremy Clyde BaileyStanley Kevin WidenerThomas Edward JohnsonJohn C Intile
    • F02C1/00F02G3/00
    • F23R3/002F23R3/06F23R2900/03042F23R2900/03044
    • A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
    • 一种用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个湍流器的燃烧器衬套,该多个湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 围绕所述燃烧器衬套的第一流动套筒,其间具有第一流动环空,所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔,用于将冷却空气从所述压缩机排出口引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒,用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50%的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。