To provide a system for cooling a crossfire tube without reduction of the amount of combustion air premixable with fuel, whereas continuation of gas and flame flow passing the crossfire tube can be promoted in a specific gas turbine engine, and the crossfire tube can be permanently damaged, in such a case, due to heating of metal to its melting point.
The crossfire tube assembly 22 includes a first tube segment 24 and a second tube segment 30, in which an overlap region is provided between a female end 28 and a male end 34. Opposed first and second impingement sleeves 44, 55 extend from the female end 28 of the first tube segment 24 to the respective first ends 46, 52 of the tube segments. Combustion cooling air is directed through metering holes 56 in the impingement sleeves 44, 50 and flows axially along concentric cavities 58 defined between the impingement sleeves 44, 50 and the first and second tube segments 24, 30.
Hirokazu Ogura
Toshihisa Kurokawa
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