Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors: Fid-Bau Portal

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Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors

Bulysova, L. A. / Tumanovskii, A. G. / Gutnik, M. N. / Vasil’ev, V. D.

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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Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors

Bulysova, L. A. / Tumanovskii, A. G. / Gutnik, M. N. / Vasil’ev, V. D.

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.

Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors

Bulysova, L. A. / Tumanovskii, A. G. / Gutnik, M. N. / Vasil’ev, V. D.

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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Title:

Factors Determining the Flame Configuration and Affecting Combustion Stability in Gas-Turbine Combustors

Additional title:

Power Technol Eng

Contributors:

Bulysova, L. A. (author) / Tumanovskii, A. G. (author) / Gutnik, M. N. (author) / Vasil’ev, V. D. (author)

Published in:

Power Technology and Engineering ; 54 ; 537-540

Publication date:

2020-11-01

Size:

4 pages

ISSN:

1570-1468 , 1570-145X

DOI:

https://doi.org/10.1007/s10749-020-01247-2

Type of media:

Article (Journal)

Type of material:

Electronic Resource

Language:

English

Keywords:

low-emission combustor , gas turbine , air-fuel mixture , nitrogen oxide , stable combustion , experimental studies , control algorithm Energy , Energy Systems , Power Electronics, Electrical Machines and Networks , Renewable and Green Energy , Geoengineering, Foundations, Hydraulics

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