| 摘要 |
Air and gaseous fuel for a gas turbine combustor are mixed within a nozzle prior to being introduced into the combustor. The fuel is introduced into an upstream end of an elongated passageway through the nozzle, while air entry ports are located in the throat of a venturi section at an intermediate portion of the elongated passageway. Each of the air passageways leading to the air entry ports is inclined at an acute angle to the longitudinal axis of the elongated passageway so that the direction of flow of air through the respective air passageway into the venturi section and the direction of fuel flow through the elongated passageway are both towards the downstream section of the elongated passageway. The venturi section allows mixing of low pressure air and high pressure gaseous fuel without excessive fuel pressure loss. Water can be injected into a mixing chamber downstream of the venturi section and upstream of nozzle outlet ports. The resulting gaseous fuel/air/water mixture is ejected into a combustion chamber through a plurality of nozzle outlet ports. Additional combustion air is introduced into the combustion chamber via inlets in the combustion chamber wall. The combustion chamber can be an annular chamber with a plurality of the nozzle structures spaced apart from each other about the outer circumference of the annular chamber.
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