ANNULAR COMBUSTION CHAMBER OF GAS TURBINE ENGINE

摘要

The fuel nozzles(12a) in the combustor of a gas turbine engine are concentrically disposed in two tiers about the circumference of the dome (10a) and are arranged in a triangular pattern with the air swirl orientation providing an increased intensity of combustion so as to enable a reduction in combustor size and weight while increasing temperature rise and the overall thrust-to-weight ratio of the engine.