Dual fuel gas turbine combustor.

摘要

The combustor has a combustion zone and first and second concentrically arranged cylindrical liners encircling at least a portion of the combustion zone. The first liner encloses the second liner and forms an annular passage between having a passage outlet leading to the combustion zone and a passage inlet in flow communication with the compressor section. A first fuel introducing device introduces a gaseous fuel into the annular passage where the gaseous fuel mixes with the compressed air and enters the combustion zone through the passage outlet. A second fuel introducing device introduces a liq. fuel into the annular passage where the liq. fuel mixes with the compressed air and enters the combustion zone through the passage outlet.