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    • 2. 发明专利
    • Combustion device for gas turbine
    • 燃气涡轮机燃烧装置
    • JP2011169582A
    • 2011-09-01
    • JP2011036247
    • 2011-02-22
    • Alstom Technology Ltdアルストム テクノロジー リミテッドALSTOM Technology Ltd
    • HUBER ANDREASNICOLAS NOIRAYBENZ URSREINERT FELIXLAUFFER DIANE
    • F23R3/42F23R3/18
    • F23R3/002F23M20/005F23R2900/00014
    • PROBLEM TO BE SOLVED: To provide a combustion device wherein a smaller air mass flow rate is made to flow from a plenum to decay volume. SOLUTION: The combustion device 1 for a gas turbine comprises a portion 6 including an inner wall 7 and an outer wall 8. The inner wall 7 comprises first passages 9 connecting a zone between the inner and outer walls 7, 8 to the inner side 10 of the combustion device 1. The outer wall 8 comprises second passages 2 for cooling the inner wall 7. Between the inner and outer walls 7, 8, an intermediate layer 17 is provided defining a plurality of chambers 18, each connected to at least one first passage 9 and the plurality of second passages 12 and defining Helmholtz dampers. The second passages 12 open in third passages 22 connected to the chambers 18 and have outlets 23 facing to each other. COPYRIGHT: (C)2011,JPO&INPIT
    • 要解决的问题:提供一种燃烧装置,其中使得较小的空气质量流量从充气室流动至衰减体积。 解决方案:用于燃气轮机的燃烧装置1包括包括内壁7和外壁8的部分6.内壁7包括将内壁7和外壁8之间的区域连接到第一通道9的第一通道9 外壁8包括用于冷却内壁7的第二通道2。在内壁7和外壁8之间设置有中间层17,其限定多个室18,每个室18连接到 至少一个第一通道9和多个第二通道12,并限定亥姆霍兹阻尼器。 第二通道12在连接到腔室18的第三通道22中打开并且具有彼此面对的出口23。 版权所有(C)2011,JPO&INPIT