| 摘要 |
A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler having f irst and second endplates, the first endplate is spaced relation to the second endplate d efining a substantially cylindrical mixing zone therebetween, the second endplate having a combustor inlet port extending therethrough, providing a centerbody located with in the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously alon g the length thereof, introducing a first portion of fuel into the combustion air as t he combustion air is introduced into the mixing zone, mixing the combustion air and fuel by sw irling the combustion air and fuel about the centerbody while flowing the combustion air an d fuel towards the combustor inlet, flowing the first portion of combustion air into th e combustor inlet, introducing a second portion of combustion air into the first p ortion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.
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