Controlling fuel combustion process by burner design change in gas turbine engine combustion chamber

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Baklanov A. V.

Kazan Motor Production Association, 1, Dementyeva str., Kazan, 420036, Russia



Fuel burning in gas turbine engine combustion chamber entails toxic agents formation. Among them, nitrogen oxides and carbonic oxides, which prove deleterious effect upon a human and environment, present the special hazard. In this regard, the article solves the topical problem on upgrading the existing combustion chamber by changing the design of its burner.

At the first stage of the research, several types of burners, differing by nozzle extension geometry, were studied. The studies consisted in determining toxic agents' emissions concentration in the flame formed by the burner.

According to the results of the studies the inference was drawn that the most acceptable burner was the burner with convergent head piece, since it ensures minimum content of nitrogen and carbonic oxides in combustion products. The decision was made on continuing studies of both types of burners, namely, original with diffuser extension and the burner with convergent head-piece, which demonstrated minimum emission of toxic agents.

It was found that the residence time of the burner with converging nozzle extension in the reverse currents zone was 0.15 ms, and 0.025 ms for the burner with convergent head-piece, which is six times less. Testing results were colligated in the form of mathematical dependence of CO and NO from swirl parameter Sg, which characterizes the degree of the nozzle head-piece opening-out.

During the next stage, the studies on determining the throughput capacity of the burners, as well as the quality of air-fuel mixture preparation at their outlet were performed.

According to the results of the studies, it was revealed that due to the high velocity pressure there is no significant jet spreading behind the burner with convergent head-piece. The jet herewith has the high ejection capability and forms narrow flow core, in which intensive fuel and air mixing occurs. The burner with diffusion extension forms a wide concentration field and its low level, which is explained by volumetric recirculation zone.

The combustion chambers tests hereafter on determining thermal field   and obtaining hydraulic characteristics were performed. The measurements showed that at the outlet of the burner with convergent head-piece in the vicinity of thermocouple No 4 the temperature increase was observed compared to the burner variant with diffusion extension. But both cameras ensure temperature field regulated by general requirements.

While next stage the tests of the engines with the combustion chambers under study were performed. The tests data confirmed the reliability of air-fuel mixture ignition during the engine starting. They confirm also correspondence of NK-16ST throttle characteristic to the chambers with both convergent head-piece and diffusion extension in the burner.

The obtained data allowed conclude that employing the burner with convergent head-piece allowed reduce emission of nitrogen oxides by 20% and carbonic oxides by 75%. The main characteristics of the combustion chamber can be affected by changes in the design of the nozzle extension in the burner.


gas-turbine engine combustion chamber, flame tube disign, upgrading, hazardous substances emission, diffusion combustion, atomizer, burner


  1. Lefebvre A.H., Ballal D.R. Gas Turbine Combustion: Alternative Fuels and Emissions. Third Edition. CRC Press, 2010, 560 p.

  2. Rogero J-M., Rubini P.A. Optimisation of Combustor Wall Heat Transfer and Pollutant Emissions for Preliminary DesignUsing Evolutionary Techniques. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2003, vol. 217, no. A6, pp. 605-614.

  3. Agulnik A.B, Onishchik I.I, Khtai T.M. Vestnik Moskovskogo aviatsionnogo instituta, 2009, vol. 16, no. 6, pp. 74-81.

  4. Ninomiya H., Kobayashi M., Kinoshita Y., Kimura H., Hyogo A. The Development of LPP Low NOx Emissions Combustor Under the ESPR Programme in Japan. ISABE-2001-1180.

  5. Shiotani H., Takagi T., Okamoto T., Kinoshita S., Teraoka H. Construction of Low NOx and High Stability Flames Aiming at Micro Gas Turbine Combustion. ASME Turbo Expo 2002: Power for Land, Sea, and Air. 2002, vol. 1, pp. 731-737. DOI: 10.1115/GT2002-30463

  6. Maughan J.R., Luts A., Bautista P.J. A Dry Low NOx, Combustor for the MS3002 Regenerative Gas Turbine. ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. 1994, vol. 3, pp. V003T06A010, 8 p. DOI: 10.1115/94-GT-252

  7. Jochen R.K., Sattelmayer T. Lean Blowout Limit and NOx-Production of a Premixed SUB-ppm NOx Burner With Periodic Flue Gas Recirculation. ASME Turbo Expo 2004: Power for Land, Sea, and Air. 2004, vol. 1, pp. 261-270. DOI: 10.1115/GT2004-53410

  8. Rizk N.K., Chin J.S. Modeling of NOx formation in diffusion flame combustors. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 2002. DOI: 10.2514/6.2002-3713.

  9. 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

  10. Kutsenko Yu.G. A combined turbulent combustion model in studying a lean flameout process. Russian Aeronautics, 2009, vol. 52, no. 2, pp. 208-213. DOI: 10.3103/S1068799809020123

  11. Danilchenko V.P., Lukachev S.V., Kovylov Yu.L., Postnikov A.M., Fedorchenko D.G., Tsybizov Yu.I. Proektirovanie aviatsionnykh gazoturbinnykh dvigatelei (Design of aircraft gas turbine engines), Samara, SNTs RAN, 2008, 620 p.

  12. Koutsenko I.G., Onegin S.F. Application of CFD-based analysis tool to the PS-90A/A2 combustors to achieve low NO emission level. 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (Fort Lauderdaly, Florida, July 11-14, 2004). Paper AIAA-2004-3878, 8 p. DOI: 10.2514/6.2004-3878

  13. Markushin A.N., Baklanov A.V. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2013, no. 3-1(41), pp. 131-138. DOI: 10.18287/1998-6629-2013-0-3-1(41)-131-138

  14. Baklanov A.V., Markushin A.N. Vestnik Kazanskogo gosudarstvennogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2017, vol. 73, no. 2, pp. 12-17.

  15. Feitelberg A.S., Starkey M.D., Schiefer R.B., Pavri R.E., Bender M., Booth J.L., Schmidt G.R. Performance of a Reduced NOx Diffusion Flame Combustor for the MS5002 Gas Turbine. ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition (Indianapolis, Indiana, USA, June 710, 1999). Vol. 2, no. 2, pp. 301-306. DOI: 10.1115/99-GT-058

  16. Lanskii A.M., Lukachev S.V., Kolomzarov O.V. Vestnik Moskovskogo aviatsionnogo instituta, 2016, vol. 23, no. 3, pp. 47-57.

  17. Baklanov A.V. Vestnik Moskovskogo aviatsionnogo instituta, 2017, vol. 24, no. 3, pp. 13-22.

  18. Baklanov A.V. Vestnik Moskovskogo aviatsionnogo instituta, 2017, vol. 24, no. 2, pp. 57-68.

  19. Markushin A.N., Baklanov A.V., Tsyganov N.E. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta im. akademika S.P. Koroleva (natsionalnogo issledovatelskogo universiteta), 2011, no. 3-1(27), pp. 35-38.

  20. Agregaty gazoperekachivayushchie s gazoturbinnym privodom. Obshchie tekhnicheskie usloviya. GOST 28775-90 (Gas pumping units with gas turbine drive. General specifications. State Standard 28775-90), Moscow, Standartinform, 2005, 12 p. — informational site of MAI

Copyright © 1994-2023 by MAI