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Cross fire tube with guide ring and angled cooling holes

机译:带有导向环和倾斜冷却孔的交叉火管

摘要

The present invention provides a multi-can type gas turbine combustor including a plurality of combustors that mix and burn fuel and the air, the combustors being connected by a crossfire tube assembly. The gas turbine cools the crossfire tube assembly without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly and prevents thermal deformation and fire damage of the crossfire tube assembly. In a gas turbine according to the present invention, a guide ring that guides a current of the air is provided in a position opposed to air holes. One side end portion of an annular space configured between the guide ring and a crossfire tube assembly is opened to a space on the inside of the crossfire tube assembly. The other end portion is a closed end connected to a partition wall configuring the crossfire tube assembly. The length of an annular space between the air holes and the closed end is set to three times or more as large as the diameter of the air holes. Further, a part of the air holes is drilled to tilt to the closed end of the annular space to cool the crossfire tube assembly including the guide ring with a small cooling air amount.
机译:本发明提供了一种多罐式燃气轮机燃烧器,其包括多个混合并燃烧燃料和空气的燃烧器,所述燃烧器通过交叉火管组件连接。燃气轮机在不降低穿过交叉火管组件的燃烧废气的温度的情况下冷却了交叉火管组件,并防止了交叉火管组件的热变形和火灾损坏。在本发明的燃气轮机中,在与气孔相对的位置设有引导空气流的引导环。在导向环和交叉火管组件之间配置的环形空间的一侧端部通向交叉火管组件内部的空间。另一端部是封闭端,该封闭端连接到构成交叉火管组件的分隔壁。气孔与封闭端之间的环形空间的长度被设置为气孔直径的三倍或更大。此外,钻出一部分气孔以倾斜到环形空间的封闭端,从而以较少的冷却空气量冷却包括引导环的交叉火管组件。

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