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    • 1. 发明专利
    • Gas turbine combustor
    • 气体涡轮搅拌机
    • JP2005106351A
    • 2005-04-21
    • JP2003339045
    • 2003-09-30
    • Hitachi Ltd株式会社日立製作所
    • SASAO TOSHIBUMITAKEHARA ISAOWATANABE YASUYUKIYAMANOBE TAKUMIAKATSU FUMIHIKOITO KAZUYUKI
    • F23R3/08F02C7/18
    • PROBLEM TO BE SOLVED: To reduce an air flow rate slipping through from a fitting and connecting part of a combustion chamber liner and a transition piece, to approximately uniformize distribution in a circumferential direction of a cooling air flow rate on the combustion chamber liner, thus to increase a fuel air flow rate, leading to reduction in NOx discharge amount, and to suppress increase in metal temperature at a terminal of the combustion chamber liner.
      SOLUTION: The combustion chamber liner 2 is connected with the transition piece 3 in a fitting structure, and an air flow passage is formed outside the combustion chamber liner 2 and the transition piece 3. At the fitting and connecting position, flow passage width in a radial direction of the air flow passage is set small in the transition piece 3 side, and is set large in the combustion chamber liner 2 side, creating a step 300. A partition wall (ring) 100 serving as resistance to an air flow is provided on an outer wall of the combustion chamber liner 2 in the vicinity of a terminal of the transition piece 3 at the fitting and connecting position.
      COPYRIGHT: (C)2005,JPO&NCIPI
    • 要解决的问题为了减少从燃烧室衬套和过渡件的装配和连接部分滑过的空气流量,大致均匀化在燃烧室上的冷却空气流量的圆周方向上的分布 从而增加燃料空气流量,导致NOx排出量的降低,并且抑制燃烧室衬套的端子处的金属温度升高。 解决方案:燃烧室衬套2与过渡件3以配合结构连接,并且在燃烧室衬套2和过渡件3之外形成空气流动通道。在配合和连接位置,流动通道 空气流路的径向的宽度在过渡件3侧被设定得较小,并且在燃烧室衬垫2侧被设定得较大,形成了台阶300.用作空气阻力的隔壁(环)100 在装配和连接位置处在过渡件3的端子附近在燃烧室衬套2的外壁上设置有流动。 版权所有(C)2005,JPO&NCIPI
    • 5. 发明专利
    • CONTROL METHOD OF GAS TURBINE
    • JPH08158893A
    • 1996-06-18
    • JP30059794
    • 1994-12-05
    • HITACHI LTD
    • ENDO TOMOYOSHIHIROSE FUMIYUKISHIMURA AKIRAYAMANOBE TAKUMISATO ISAOIKEDA HIROSHI
    • F02C9/00F23N5/00F23R3/30F23R3/34F23R3/46
    • PURPOSE: To continue driving without stopping a gas turbine by speedily detecting abnormality of combustion and transferring to individual combustion of only a first stage combustion part even in the case when abnormal combustion is taken place in a second stage combustion part of a large number of combustors simultaneously. CONSTITUTION: Change of each combustor metal temperature 1 is monitored, and a rate of change 3 as time passes is taken out by a rate of change enumerator 2. In the case when the rate of change 3 still exceeds an allowable value even when time set by a timer 5 passes, a monitor relay 4 regards the combustor is abnormal and transmits a signal 6. The number of the combustors regarded as combustion abnormality is found out by an adder 7 in accordance with this signal 6, in the case when it exceeds the majority of the total number of the combustors, a monitor relay 8 regards it as multiple combustor simultaneous combustion unstability and transmits a signal 9. By transmission of this signal 9, a transferring command to individual driving of the first stage combustion part is transmitted. Consequently, it is possible to continue driving while maintaining a stable combustion state without stopping a gas turbine.