发明名称 COMBUSTOR FOR GAS TURBINE
摘要 <p>PURPOSE:To improve ignition property and reduce pressure loss by a method wherein a catalyst bearing part is constituted by three-stage structure consisting of first stage, a ceramic honeycomb structure bearing a precious meral series catalyst, second structure, a refractory honeycomb structure bearing the same catalyst and third structure, a honeycomb structure catalyst body of composite oxide. CONSTITUTION:The ceramic, constituting the first stage of ceramic honeycomb structure, is alpha-alumina, zirconia or the like while the refractory alloy, constituting the second stage of the refractory alloy honeycomb structure, is the alloy of hastelloy, inconel or the like. The precious metal series catalyst, born by the structures of the first and second stages, begins combustion reaction from a comparatively low temperature. The composite oxide honeycomb structural catalyst body, constituting the third stage, has the effect of the catalyst by itself at a high temperature and is made of titanic acid, zirconate or the like of Ba, Mn, Ni, Co, Cu, Fe, Ca or the like added with alumina of high purity or the like, and it is prepared by mixing and forming into the honeycomb shape, thereafter, calcining under a pressure.</p>
申请公布号 JPS5924122(A) 申请公布日期 1984.02.07
申请号 JP19820132031 申请日期 1982.07.30
申请人 TOKYO SHIBAURA DENKI KK 发明人 FURUYA TOMIAKI;HAYATA TERUNOBU;YAMANAKA CHIKAU;HIZUKA JIYUNJI
分类号 F23C13/00;F23R3/40;(IPC1-7):23R3/40 主分类号 F23C13/00
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