FIELD: engines and pumps.
SUBSTANCE: combustion chamber for a gas turbine engine has a front end portion that supports at least one fuel-air nozzle. Each fuel-air nozzle comprises an auxiliary pre-mixing nozzle comprising pre-mixing lines that have concentric axes guiding the fuel-air mixture along the axis from the auxiliary pre-mixing nozzle. The auxiliary nozzle may have an annular channel located radially outwardly of it, and air jets that direct air radially outward from the pre-mixing lines. Also versions of the way of operation of the fuel-air nozzle for the gas-turbine engine are presented.
EFFECT: invention allows the premixing of fuel and air with simultaneous reduction of nitrogen oxides.
24 cl, 11 dwg
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RU2189478C2 |
