Patent attributes
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.
