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Numerical Simulation of Combustion Processes and Analysis of Temperature Field Non-Uniformity in GTE-65 Gas Turbine Combustor

[+] Author Affiliations
Dmitry Tarasov, Alexander Lebedev, Nikolay Simin, Viktor Grinevich

OJSC “Power Machines”, Saint Petersburg, Russia

Paper No. GT2010-23798, pp. 1345-1353; 9 pages
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 2: Combustion, Fuels and Emissions, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4397-0 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME


Our company has tested annular combustion chamber, being one of main components of hot gas path for GTE-65 gas turbine in mid power class. In order to arrange gaseous fuel oxidation process a method of lean homogenized air-fuel mixture burning is realized in the combustor. The same type two-contour burner modules are installed on the combustor cap in two rows by 60 burners in a row (120 burners in all). To optimize control algorithm and confirm main performances a model compartment, representing 1/12 part (segment) of actual combustion chamber, was produced. The tests have been conducted with using GP “Ivchenko-Progress” and OJSC “Power Machines” test rigs on modes from ignition to full load. Stable firing mode and pollutant emissions have been determined and the liner temperature condition and temperature field unevenness have been checked. The combustor control algorithm was optimized. As a result of the conducted tests there were confirmed environmental requirements to the combustor NOx emissions (less than 25 ppm). Mathematical simulating machine was being used to predict the combustor operation performances at the gas turbine operating in field conditions. 3D numerical analysis was carried out to predict the temperature and NOx fields before the experiment preparation. In order to meet the numerical model with the test conditions after the experiment the boundary conditions were specified (fuel / air temperature and mass flow rate). Full and partial load calculations were performed for simulation and field operation conditions. The calculation results were compared with experimental data obtained in the course of bench test. Errors obtained by comparison with numerical and experimental data were as follows: • full model pressure drop: ∼ 3–4%; • ratio of peripheral and radial non-uniformities of temperature fields: ∼ 2%; • nitrogen oxides at various operation modes: maximum 25 ppm. The obtained results make it possible to go on the combustor testing in field conditions.

Copyright © 2010 by ASME



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