The possibilities of influencing combustion stability during changeover to low-emission combustion and ways of extending the stable combustion range are analyzed. The flow velocity, temperature, and pressure in the low-emission combustor (LEC) are considered as influencing factors. A premixed swirl-stabilized combustor is considered. The burner unit consists of main and pilot burners. The main burner has two fuel channels that allow controlling the quality of the air-fuel mixture. The LEC developed for an aeroderivative gas turbine was tested at an inlet air pressure of 2 MPa and an inlet air temperature of 475°C and an exhaust gas temperature of up to 1320°C.
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L. A. Bulysova, A. G. Tumanovskii, M. N. Gutnik, V. D. Vasil’ev, A. M. Sipatov, and A. D. Nugumanov, “Low-emission operation of aeroderivative gas-turbine combustor over a wide range of ambient conditions,” Power Technol. Eng., 54(1), 93 – 95 (2020).
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Translated from Élektricheskie Stantsii, No. 6, June 2020, pp. 2 – 5.
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Bulysova, L.A., Tumanovskii, A.G., Gutnik, M.N. et al. Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors. Power Technol Eng 54, 537–540 (2020). https://doi.org/10.1007/s10749-020-01247-2
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DOI: https://doi.org/10.1007/s10749-020-01247-2