Adaptive technologies application in the issue of studying the flow structure formed by the burners in the GTE combustion chamber

Thermal engines, electric propulsion and power plants for flying vehicles


Baklanov A. V.1*, Vasil'ev A. A.2**

1. Kazan National Research Technical University named after A.N. Tupolev, 10, Karl Marks str., Kazan, 420111, Russia
2. Kazan Motor Production Association, 1, Dementyeva str., Kazan, 420036, Russia



In conventional practice, ensuring the necessary parameters of combustion chambers is achieved by studying several options of swirl burners to obtain the optimal design, acceptable for the combustion chamber. The swirl burners’ production is a labor intensive and expensive process. Modern additive technology application for the parts manufacturing is actually the technology allowing produce shortly the burner with necessary design and test it, obtaining the parameters of interest to the developer.

The article presents the result of designing and producing combustion chamber burners of gas turbine engine by the prototyping method. Printing of burners was performed with 3D Picaso printer, which operates by the plastic extrusion technology. In other words, the burner model is fabricated by layer-by-layer applying of extra fine layers of molten plastic. These layers, becoming a virtual cross-section in CAD model, are united or fused together to form an object of the adjusted form. The ABS and PLA plastics, which allowed machining, polishing and painting, are used for printing. Several burners with different blade angles were produced. The article presents the equipment and materials being used for the burners producing, the design of test bench, which was used to study the flow pattern in outlet of the produced burners.

Based on the performed studies, it was discovered that the near placed burners with various swirl directions of blades formed the short structure of turbulent jet. It is explained by mutual penetration of turbulent layers directed towards each other As result, the vortex energy content scale of is decreased as the jets energy is spent for collided layers interaction. The authors conclude that in modern low-emission combustion chamber the short residence time of gases of about 7 ms is provided. It is necessary to reduce the level of nitrogen oxides formation in combustion products. Thus, organizing the opposite twist between the burners in the upper and lower stages is may be useful to ensure the low-emission combustion.


combustion chamber, burner, gas-turbine engine, additive technologies, turbulent flow, flow swirling


  1. Danil’chenko V.P., Lukachev S.V., Kovylov Yu.L. et al. Proektirovanie aviatsionnykh gazoturbinnykh dvigatelei (Design of aircraft gas turbine engines), Samara, Izd-vo SNTs RAN, 2008, 620 p.

  2. Baklanov A.V., Markushin A.N. Vestnik Kazanskogo gosudarstvennogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2015, no. 6, pp. 101 – 105.

  3. Baklanov A.V., Neumoin S.P. A technique of gaseous fuel and air mixture quality identification behind the swirl burner of gas turbine engine combustion chamber, Russian Aeronautics, 2017, vol. 60, no. 1, pp. 90 – 96.

  4. Baeva L.S., Marinin A.A. Vestnik Moskovskogo gosudarstvennogo tekhnicheskogo universiteta im. N.E. Baumana, 2014, vol. 17, no. 1, pp. 7 – 12.

  5. Antonova V.S., Osovskaya I.I. Additivnye tekhnologii (Additive technologies), Saint Petersburg, VShTE SPbGUPTD, 2017, 30 p.

  6. Ganin N.B. Avtomatizirovannoe proektirovanie v sisteme KOMPAS-3D V12 (Automated design in the KOMPAS-3D V12 system), Moscow, DMK Press, 2010, 360 p.

  7. Chee Kai Chua, Chee How Wong, Wai Yee Yeong. Standards, Quality Control and Measurement Sciences in 3D Printing and Additive Manufacturing, Academic Press, 2017, 266 р.

  8. Valetov V.A. Additivnye tekhnologii (sostoyanie i perspektivy) (Additive technologies (state-of-the-art and prospects), Saint Petersburg, Universitet ITMO, 2015, 63 p.

  9. Zlenko M.A., Nagaitsev M.V., Dovbysh V.M. Additivnye tekhnologii v mashinostroenii (Additive technologies in mechanical engineering), Moscow, NAMI, 2015, 220 p.

  10. 10. Markushin A.N., Baklanov A.V. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta im. akademika S.P. Koroleva, 2013, no. 3-1 (41), pp. 131 – 138.

  11. Schlüter J., Schönfeld T., Poinsot T., Krebs W., Hoffmann S. Characterization of confined swirl flows using large eddy simulations, ASME Turbo Expo 2001: Power for Land, Sea, and Air (New Orleans, Louisiana, USA, June 4-7, 2001), 2001, vol. 2, pp. V002T02A027. DOI: 10.1115/2001-GT-0060

  12. Moses, C., Roets, P. Properties, Characteristics and Combustion Performance of Sasol Fully Synthetic Jet Fuel, ASME Journal of Engineering for Gas Turbines and Power, 2009, vol. 131, no. 4, pp. 1-17. DOI: 10.1115/1.3028234

  13. Harrison W.E., Zabarnick S. The OSD Assured Fuels Initiative – Military Fuels Produced from Coal, DoE Clean Coal Conference, Clearwater, FL, June 2007.

  14. Lieuwen T., McDonell V., Petersen E., Santavicca D. Fuel Flexibility Influences on Premixed Combustor Blowout, Flashback, Autoignition, and Stability, ASME Journal of Engineering for Gas Turbines and Power, 2008, vol. 130, 011506-011506-12.

  15. A.K. Gupta, D.G. Lilley, N. Syred. Swirl Flows, Kent, Abacus Press, 1984, 475 р.

  16. Lee S., Speight J.G., Loyalka S.K. Handbook of Alternative Fuel Technologies, CRC Press, Boca Raton, FL, 2007, 525 p.

  17. Lefebvre A.H., Ballal D.R. Gas Turbine Combustion: Alternative Fuels and Emissions, 2010, CRC Press, 537 p.

  18. Kiesewetter F., Konle M., Sattelmayer T. Analysis of Combustion Induced Vortex Breakdown Driven Flashback in a Premix Burner with Cylindrical Mixing Zone, ASME Journal of Engineering for Gas Turbines and Power, 2007, vol. 129, pp. 929 – 936.

  19. Lieuwen T.C., Yang, V. Combustion Instabilities in Gas Turbine Engines, Progress in Astronautics and Aeronautics, AIAA, 2005, vol. 210, pp. 657.

  20. Lubkov N.V, Spiridonov I.B, Stepanyants A.S. Trudy MAI, 2016, no. 85:

  21. Metechko L.B, Tikhonov A.I, Sorokin A.E, Novikov S.V. Trudy MAI, 2016, no. 85:

Download — informational site MAI

Copyright © 2000-2024 by MAI