| 摘要 |
A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction. |
| 主权项 |
1. A method of mixing combustion reactants for combustion for a gas turbine engine comprising the steps of:
providing a can annular combustor, the can annular combustor includes an outer liner enclosing a plurality of circumferentially spaced cans enclosed between two cylindrical liners, each of the plurality of circumferentially spaced cans define separate combustion zones and each of the plurality of circumferentially spaced cans has a can liner, the can liner of each of the plurality of circumferentially spaced cans has an upstream end, including a front wall, and a downstream end, the combustion zone of each of the plurality of circumferentially spaced cans has a can volume of the can liner of each of the plurality of circumferentially spaced cans, the can volume of each of the plurality of circumferentially spaced cans extends in a longitudinal direction from the front wall of the upstream end of the can liner to the downstream end of the can liner of each of the plurality of circumferentially spaced cans, a plurality of dilution holes through the front wall of each of the plurality of circumferentially spaced cans, first nozzles through the can liner of each of the plurality of circumferentially spaced cans, second nozzles through the can liner of each of the plurality of circumferentially spaced cans, the first nozzles of each of the plurality of circumferentially spaced cans are spaced apart and are arranged circumferentially around the combustion zone between the front wall and the downstream end of the can liner of each of the plurality of circumferentially spaced cans, the second nozzles of each of the plurality of circumferentially spaced cans are spaced apart and are arranged circumferentially around the combustion zone between the front wall and the first nozzles of each of the plurality of circumferentially spaced cans, the first nozzles are downstream of the second nozzles toward the downstream end of the can liner and reside in a first plane that is normal to the longitudinal direction of the can volume of each of the plurality of circumferentially spaced cans, and the second nozzles are upstream of the first nozzles toward the upstream end of the can liner and reside in a second plane that is normal to the longitudinal direction of the can volume of each of the plurality of circumferentially spaced cans and for each of the cans concurrently: injecting a first premixed fuel-air mixture into the can volume through all of the first nozzles with a first fuel-air ratio, the first nozzles each applying the first premixed fuel-air mixture into the annular volume in a direction that is angularly offset from a tangent line relative to the can liner of each of the plurality of circumferentially spaced cans; injecting a second premixed fuel-air mixture into the can volume through all of the second nozzles with a second fuel-air ratio, wherein the second fuel-air ratio is greater than the first fuel-air ratio, the second nozzles each applying the second premixed fuel-air mixture into the can volume in the direction that is angularly offset from the tangent line relative to the can liner of each of the plurality of circumferentially spaced cans; and injecting compressor discharge air through the plurality of dilution holes through the front wall into the can volume in the longitudinal direction of the can volume of each of the plurality of circumferentially spaced cans; the concurrent steps of injecting the first premixed fuel-air mixture into the can volume through all of the first nozzles, injecting the second premixed fuel-air mixture into the can volume through all of the second nozzles, and injecting compressor discharge air through the plurality of dilution holes through the front wall into the can volume of each of the plurality of circumferentially spaced cans creating fuel-air staging for enhancing combustion and reducing NOx and CO emissions. |
