| 摘要 |
PROBLEM TO BE SOLVED: To prevent the deterioration in ignition performance between adjacent combustor liners by a flame propagation pipe when restraining a flow speed of a compressed air flow from becoming spatially nonuniform since the flame propagation pipe intercepts the compressed air flow flowing between the combustor liner and a casing when arranging the flame propagation pipe for connecting combustion chambers inside of the adjacent combustor liners via a part between the combustor liner and the casing of a gas turbine combustor. SOLUTION: This gas turbine combustor is constituted so that a flow speed of a layer flowing along a surface of the flame propagation pipe 10 does not remarkably reduce among the compressed air flow by forming a cross-sectional shape of the flame propagation pipe 10, for example, in a flat shape like an ellipse having a long diameter in the compressed air flow direction. COPYRIGHT: (C)2005,JPO&NCIPI
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