Pressure losses in combustion chamber fuel system of the natural gas running gas turbine engine

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



Pressure losses computing in the fuel system of the stationary gas turbine engine is an integral part for solving a number of engineering and operational tasks. For example, such calculation is necessary to determine a minimum required gas pressure at the inlet of the engine to ensure the engine reaching its operational modes. Likewise, this calculation may come in handy at the fuel gas composition changing, since gas properties change, which means the pressure loss change too that can require to make changes in control equipment. It is well known that fuel nozzles are carbonized while a combustion chamber operation process. Very often, it leads to the resistance increasing of the fuel system, and therefore the of pressure losses rising. Besides, any discrepancies in the dosing equipment can be detected by a hydraulic calculation.

The article considers a fuel system of a stationary converted aircraft engine intended for driving the gas pumping unit supercharger. The pressure losses computing technique for the fuel system of such engine is presented in the article. A relevance of the topic and the necessity of such techniques forming are disclosed. To check the adequacy of the developed technique the NK-16ST engine rig test was performed with pressure measuring in the fuel supply pipelines to the nozzles and in the gas doser. The results of the studies revealed that the gas fuel pressure level measured in the eight gas-extraction from collector to nozzles pipelines differed insignificantly, which confirmed the fuel distribution uniformity along the pipelines. Experimental results comparison with the computational studies confirms that their discrepancy does not exceed 6%.


Pressure losses in combustion chamber fuel system of the natural gas running gas turbine engine


  1. Lefebvre A.H., Ballal D.R. Gas Turbine Combustion: Alternative Fuels and Emissions. 3rd edition. CRC Press, 2010, 557 p.

  2. Lefebvre A.H. Fuel effects on gas turbine combustion- ignition, stability, and combustion efficiency. Journal of Engineering for Gas Turbines and Power, 1985, vol. 107, no. 1, pp. 24-37. DOI: 10.1115/1.3239693

  3. Gritsenko E.A., Danil’chenko V.P., Lukachev S.V., Reznik V.E., Tsybizov Yu. I. Konvertirovanie aviatsionnykh GTD v gazoturbinnye ustanovki nazemnogo primeneniya (Aviation gas turbine engines conversion into ground application gas turbines), Samara, SNTs RAN, 2004, 266 p.

  4. Idel’chik I.E. Spravochnik po gidravlicheskim soprotivleniyam (Hydraulic resistance reference book), Moscow, Mashinostroenie, 1992, 672 p.

  5. Baklanov A.V. Raschet poter’ davleniya v toplivnoi sisteme kamery sgoraniya i gazoturbinnoi ustanovki (Pressure losses computing in the fuel system of combustion chamber and gas turbine installation), Kazan, KNITU-KAI, 2020, 52 p.

  6. Gritsenko E.A., Danil’chenko V.P., Lukachev S.V. et al. Nekotorye voprosy proektirovaniya aviatsionnykh gazoturbinnykh dvigatelei (Some issues of aircraft gas turbine engines designing), Samara, SNTs RAN, 2002, 527 p.

  7. Baklanov A.V. Controlling fuel combustion process by burner design change in gas turbine engine combustion chamber. Aerospace MAI Journal, 2018, vol. 25, no. 2, pp. 73-85.

  8. Richerson D.W. Ceramics for Turbine Engines. Mechanical Engineering, 1997, vol. 119, no. 9, pp. 80–83.

  9. Shterenlikht D.V. Gidravlika (Hydraulics), Moscow, Energoatomizdat, 1991. Book 1, 351 p.

  10. Baklanov A.V. The impact of the of fuel supplying method to the combustion chamber on carbon oxides formation in combustion products of the gas turbine engine. Aerospace MAI Journal, 2019, vol. 26, no. 1, pp. 111-125.

  11. Lanskii A.M., Lukachev S.V., Kolomzarov O.V. Small gas turbine engines combustion chambers geometric resizing and integral parameters changing trends. Aerospace MAI Journal, 2016, vol. 23, no. 3, pp. 47-57.

  12. Rosen R., Facey J.R. Civil Propulsion Technology for the Next Twenty Five Years. 8th International Symposium on Air Breathing Engines, 1987. Paper no. 87-7000, AIAA, Washington, DC.

  13. Dodds W.J., Ekstedt E.E. Broad specification fuel combustion technology program: Phase II. NASA Final Technical Reports Server (NTRS), 1989.

  14. Dodds W.J., Bahr D.W. Combustion System Design. In: A.M. Mellor (ed.) Design of Modern Gas Turbine Combustors. New York, Academic Press, 1990, pp. 343-476.

  15. Taylor S.C. Burning velocity and the influence of flame stretch. PhD. Thesis. University of Leeds, 1991, 332 p. URL:

  16. Baklanov A.V., Markushin A.N., Tsyganov N.E. Vestnik Kazanskogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2014, no. 3, pp. 13-18.

  17. Zheng H., Zhang Z., Li Y., Li Z. Feature-Parameter- Criterion for Predicting Lean Blowout Limit of Gas Turbine Combustor and Bluff Body Burner. Mathematical Problems in Engineering, 2013. Article ID 939234, 17 p. DOI: 10.1155/2013/939234

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

  19. Sadiki A., Repp S., Schneider C., Dreizler A., Janicka J. Numerical and experimental investigations of confined swirling combusting flows. Progress in Computational Fluid Dynamics, an International Journal, 2003, vol. 3, no. 2-4, pp. 78-88. DOI: 10.1504/PCFD.2003.003778

  20. Markushin A.N., Baklanov A.V. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2016, vol. 15, no. 3, pp. 81-89. DOI: 10.18287/2541-7533-2016-15-3-81-89 — informational site of MAI

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