The invention relates to the technical field of gas
turbine combustion chambers, in particular to a gas
turbine combustion chamber
layout structure which comprises a gas inlet section, a
combustion section is arranged on the gas inlet section, five sets of combustors are arranged in the gas inlet section, and each
combustor comprises an outer shell, a middle shell and an inner shell which are sequentially arranged in a sleeving mode and coaxially arranged. A head
cyclone is arranged at the air outlet end of the middle shell; a first guide vane; a second guide vane; a
rotational flow assembly; and an assembling mechanism. Mixing of different components between air and
fuel gas flow can be promoted, the reaction efficiency is improved, the uniformity of gas is improved, dead zones in the gas flow are effectively reduced, the gas flow is more uniform in the whole
system, local accumulation or retention is avoided, the inlet direction of fluid can be optimized, the rotation effect of the fluid can be enhanced, and the service life of the fluid is prolonged. And
rotational flow fluid is guided to be smoothly discharged, a certain flow speed is maintained, various combustion organizations such as
diffusion,
diffusion and premixing, premixing and the like are achieved, and therefore air organization and
fuel distribution of each
combustor are controllable.