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    • 11. 发明申请
    • COMPRESSOR AND METHOD FOR COMPRESSING GASEOUS FUEL
    • 压缩机和压缩气体燃料的方法
    • WO2009109429A1
    • 2009-09-11
    • PCT/EP2009/050998
    • 2009-01-29
    • SIEMENS AKTIENGESELLSCHAFTKAY, PeterNILSSON, UlfSENIOR, Peter
    • KAY, PeterNILSSON, UlfSENIOR, Peter
    • F01C1/344F01C11/00F04C18/344F02B29/00F02C3/22F02M37/06
    • F01C11/008F01C1/3442F04C18/3442F04C25/00
    • A method for compressing gaseous fuel is disclosed, which comprises the steps: a) ingesting gaseous fuel into a chamber; b) ingesting air into the chamber and mixing the gaseous fuel with the air; c) igniting and partially combusting the resulting mixture of gaseous fuel and air in a confined space such that a predominant fraction of the gaseous fuel is not combusted, causing an increased temperature and therefore an increased pressure of the fraction of the gaseous fuel which is not combusted; and d) discharging the resulting compressed gaseous fuel. Moreover, a compressor (1) is provided, comprising a casing (2), a rotor (3) with at least three vanes (6), at least one inlet (7) for gaseous fuel, at least one outlet (11) for gaseous fuel, at least one air inlet (9) and at least one igniter (14). The rotor (3) is placed in the casing (2) such that at least three variable-volume chambers (15, 16, 17) part-bounded by the vanes (6) are formed during a rotor revolution, the inlet (7) for gaseous fuel is placed in the casing (2) such that the inlet (7) for gaseous fuel is connected to a first location where a chamber (15) has an increasing volume during a revolution of the rotor (3), the air inlet (9) and the igniter (14) are placed in the casing (2) in a second location where a chamber (16) has an increasing, decreasing or constant volume during a revolution of the rotor (3), and the outlet (11) for gaseous fuel is placed in the casing in a third location where a chamber (17) has a decreasing volume during a revolution of the rotor (3). Furthermore, a gas turbine comprising an inventive compressor (1) is disclosed.
    • 公开了一种压缩气体燃料的方法,其包括以下步骤:a)将气体燃料吸入室中; b)将空气吸入室内并将气体燃料与空气混合; c)点燃和部分燃烧所产生的气态燃料和空气的混合物在密闭空间中,使得主要部分的气体燃料不燃烧,导致升高的温度,因此不增加气态燃料部分的压力 燃烧; 和d)排出所得到的压缩气体燃料。 此外,提供了一种压缩机(1),包括壳体(2),具有至少三个叶片(6)的转子(3),用于气体燃料的至少一个入口(7),至少一个用于 气体燃料,至少一个空气入口(9)和至少一个点火器(14)。 转子(3)被放置在壳体(2)中,使得在转子旋转期间形成由叶片(6)部分界定的至少三个可变容积的室(15,16,17),入口(7) 气体燃料被放置在壳体(2)中,使得用于气体燃料的入口(7)连接到在转子(3)的转动期间室(15)具有增加的体积的第一位置,空气入口 (9)和点火器(14)在转子(3)的转动期间在室(16)具有增加的,减小的或恒定的体积的第二位置处放置在壳体(2)中,并且出口(11) )用于气体燃料的第三位置放置在壳体内,在第三位置,在转子(3)的转动期间室(17)具有减小的体积。 此外,公开了一种包括本发明的压缩机(1)的燃气涡轮机。
    • 17. 发明申请
    • PRE-MIX COMBUSTION SYSTEM FOR A GAS TURBINE AND METHOD OF OPERATING THE SAME
    • 一种用于气体涡轮机的预混合燃烧系统及其运行方法
    • WO2007122110A1
    • 2007-11-01
    • PCT/EP2007/053546
    • 2007-04-12
    • SIEMENS AKTIENGESELLSCHAFTSENIOR, PeterWILBRAHAM, Nigel
    • SENIOR, PeterWILBRAHAM, Nigel
    • F23R3/28F23R3/34
    • F23R3/286F23C2900/03003F23R3/34
    • A gas turbine pre-mix combustion system is provided which comprises : - at least one combustor (1) with a combustor wall (3) which partly surrounds a combustion zone; - at least one mixing duct (9) including an air passage which leads to an outlet opening (11) being open towards the combustion zone (5); and - one or more fuel injection openings (17) leading into the air passage and connecting it to one or more fuel supply passages (13) so as to allow the injection of fuel into air flowing through the air passage (21). The locations of at least two outlet openings (11) and the orientation of downstream sections of the respective air passages (21) are chosen such that fuel/air mixtures flowing out of the outlet openings (11) show opposed flow paths so as to impinge on each other in the combustion zone (5, 305).
    • 提供了一种燃气轮机预混合燃烧系统,其包括: - 至少一个具有部分地围绕燃烧区的燃烧器壁(3)的燃烧器(1); - 至少一个混合管道(9),包括通向朝向所述燃烧区域(5)打开的出口开口(11)的空气通道; 以及 - 一个或多个燃料喷射开口(17),其通向空气通道并将其连接到一个或多个燃料供应通道(13),以便允许将燃料喷射到通过空气通道(21)的空气中。 选择至少两个出口(11)的位置和相应空气通道(21)的下游部分的取向,使得从出口(11)流出的燃料/空气混合物显示相对的流动路径,以便撞击 在燃烧区(5,305)中彼此相对。
    • 18. 发明申请
    • GAS TURBINE COMBUSTOR
    • 气体涡轮搅拌机
    • WO2007115989A1
    • 2007-10-18
    • PCT/EP2007/053281
    • 2007-04-04
    • SIEMENS AKTIENGESELLSCHAFTNILSSON, UlfSENIOR, Peter
    • NILSSON, UlfSENIOR, Peter
    • F23R3/12F23R3/36F23R3/34F23C7/00
    • F23C7/002F23D2900/14701F23R3/12F23R3/34F23R3/36
    • A gas turbine combustor (1) is provided, which comprises: - a combustion chamber (5, 105, 205, 305) having an axial direction and a radial direction; - air passages (17, 127, 128, 217, 317) for feeding an air stream into the combustion chamber (5, 105, 205, 305) which are oriented such that the flowing direction of each air stream flowing into the combustion chamber (5, 105, 205, 305) includes an angle with the combustion chamber's radial direction so as to introduce a swirl in the in-flowing air and an angle of at least 60° with the combustion chamber's axial direction; and - fuel injection openings (19, 21, 261, 263) which are located in the air passages (17, 127, 128, 217, 317). Each air passage (17, 127, 128, 217, 317) defines a turning flow path with a turning between 70° and 150° in a radial direction of the combustion chamber (5, 105, 205, 305) and a turning between 0° and 235° in an axial direction of the combustion chamber (5, 105, 205, 305).
    • 提供一种燃气轮机燃烧器(1),其包括: - 具有轴向和径向方向的燃烧室(5,105,205,305); - 空气通道(17,127,128,217,317),用于将空气流供给到燃烧室(5,105,205,305)中,其被定向成使得流入燃烧室的每个空气流的流动方向 5,105,205,305)包括与燃烧室的径向方向的角度,以便在流入的空气中引入漩涡,并且与燃烧室的轴向方向至少为60°的角度; 和 - 位于空气通道(17,127,128,217,317)中的燃料喷射开口(19,21,261,263)。 每个空气通道(17,127,128,217,317)限定了在燃烧室(5,105,205,305)的径向方向上在70°和150°之间转动的转向流动路径,并且在0 °和235°在燃烧室(5,105,205,305)的轴向方向上。