PURPOSE: To improve the performance of a forced convection cooling operation and to enable a film cooling performance to be ensured by a method wherein an air flow passage communicated with the air side and the combustion gas side of a combustion device and a bypass flow passage communicated directly with the air side at a part where the air is communicated with the combustion gas side are arranged within a structured member constituting a gas turbine combustion equipment.
CONSTITUTION: Cooling air 103 at the air side 101 flows from a groove 3 into an air flow passage 2 and then flows toward a groove 4 along the air flow passage 2 while cooling a combustion device. The cooling air 103 reached to the groove 4 at the combustion gas 102 side is merged with the bypassing air 104 fed from the air side 101 through a bypath 6 and then expanded fully into the groove 4 while its direction being reversed. The cooling air 103 merged with the bypassing air 104 is fed out along the wall surface of a structure 1 by a flange-like lip 5 in the form of a uniform thickness film-like cooling air 105 and smoothly covers the surface of the combustion gas 102 side in the combustion device. In this case, the plate thickness of the structure member 1, the shape and the size of the air flow passage 2 are made to small sizes in such a way as the performance of the forced convection cooling caused by the air 101 and the cooling air 103 is increased.
TSUKAHARA SATOSHI
ISHIBASHI YOJI
URUSHIYA HARUO
