Multilevel modelling application in the gas turbine engine low-emission combustion chamber design process

DOI: 10.34759/vst-2020-4-159-172

Аuthors

Baklanov A. V.

Kazan National Research Technical University named after A.N. Tupolev, 10, Karl Marks str., Kazan, 420111, Russia

e-mail: andreybaklanov@bk.ru

Abstract

Despite the variety of the existing approaches, as of today, no universal technique, allowing accounting for the set of complex chemical and gas dynamic process while developing and modeling low-emission combustion chambers of gas turbine engines (GTE) accomplished in the framework of the LPP (Lean Prevaporized Premixed) concept has been developed. The LPP-chamber operation is based on low-temperature combustion of a pre-prepared “poor” air-fuel mixture with excess-air factor of 1.8-2.0.

The presented article proposes a method for the multilevel modelling implementation in the GTE low-emission combustion chamber design process. Combustion chamber accomplished in the framework of the LPP concept was selected as the object of the study. This concept is based on the combustion of pre-prepared “poor” air-fuel mixture.

Multilevel modeling includes three stages of computing: designing calculation, one-dimensional modelling, and gas dynamic processes modeling. The article presents the formed appearance of the combustion chamber and its elements in accordance with the proposed technique. Parameters computing along the flame tube length of the three chambers, where burner devices with different swirl angles of the swirl vanes were installed, was performed.

The calculations were being performed in the ideally gas approximation of the incompressible homogeneous environment in the adiabatic statement of the stationary problem.

The two-parameter RNG k- ε model with standard wall functions was used as the turbulence model.

Combustion was being modelled by the aggregate of laminar flamelets in the turbulent flow of unmixed components. The Kee58 mechanism, including eighteen mixture components and fifty-eight chemicalreactions was considered as a set of methane oxidation chemical reaction.

The NOx content computing in combustion products was based on thermal and super equilibrium mechanisms of NOx formation.

Analysis of the obtained results revealed that increasing of the twist angle in the blade swirl of the burner device leads to fundamental changes in the flow structure in the primary zone of the combustion chamber, which affects the change in emission characteristics as well. The chamber with the burner device with the twist angle of 45° ensures the best optimal emission characteristics on nitrogen oxides.

Keywords:

gas turbine engine, combustion chamber, in-chamber processes simulation, low-emission combustion, burner device

References

1. Schluter J., Schonfeld T., Poinsot T., Kreds W., Hoffmann S. Characterization of confined swirl flows using large eddy simulations. ASME Turbo Expo 2001: Power for Land, Sea, and Air (4–7 June 2001; New Orleans, Louisiana, USA). GT2001-0060. DOI: 10.1115/2001-GT-0060

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

3. Lieuwen T., McDonell V., Petersen E., Santavicca D. Fuel Flexibility Influences on Premixed Combustor Blowout, Flashback, Autoignition, and Stability. Journal of Engineering for Gas Turbines and Power, 2008, vol. 130, no. 1. DOI: 10.1115/1.2771243

4. Orlov M.Yu., Anisimov V.M., Kolomzarov O.V. Design refinement of combustion chamber of gas turbine engine with toroid recirculation zone. Aerospace MAI Journal, 2018, vol. 25, no. 3, pp. 97-106.

5. Orlov M.Yu., Anisimov V.M. Computational study of compressor operation mode effect on gas turbine engine combustion chamber processes. Aerospace MAI Journal, 2017, vol. 24, no. 2, pp. 50-56.

6. Gritsenko E.A., Danil’chenko V.P., Lukachev S.V. et al. Konvertirovanie aviatsionnykh GTD v gazoturbinnye ustanovki nazemnogo primeneniya (Aviation gas turbine engines conversion to ground-based gas turbine installations), Samara, SNTs RAN, 2004, 266 p.

7. Baklanov A.V., Markushin A.N. Vestnik Kazanskogo gosudarstvennogo tekhnicheskogo universiteta im. A.N. Tupoleva, 2017, vol. 73, no. 2. pp. 56-61.

8. Lokai V.I., Bodunov M.N., Zhuikov V.V., Shchukin A.V. Teploperedacha v okhlazhdaemykh detalyakh gazoturbinnykh dvigatelei (Heat transfer in cooled parts of gas turbine engines). 2^nd ed. Moscow, Mashinostroenie, 1993, 288 p.

9. Lefebvre A.H., Ballal D.R. Gas Turbine Combustion: Alternative Fuels and Emissions. Third Edition. CRC Press. Taylor & Francis Group, LLC, 2010, 557 p.

10. Yankovskii V.M., Shalaev G.M., Sychenkov V.A. Osnovy avtomatizirovannogo proektirovaniya kamer sgoraniya gazoturbinnykh dvigatelei (Fundamentals of computer-aided design of combustion chambers for gas turbine engines), Kazan, KAI, 1989, 80 p.

11. 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

12. Danil’chenko V.P., Kovylov Yu.L., Postnikov A.M. et al. Proektirovanie aviatsionnykh gazoturbinnykh dvigatelei (Aircraft gas turbine engines designing), Samara, SNTs RAN, 2008, 620 p.

13. Markushin A.N., Baklanov A.V., Tsyganov N.E. Improvement of aircraft GTE emission characteristics by using the microflame fuel combustion in a shortened combustion chamber. Russian Aeronautics, 2013, vol. 56, no. 4, pp. 401-406. DOI: 10.3103/S1068799813040132

14. 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. DOI: 10.3103/S1068799817010135

15. Sabirzyanov A.N., Baklanov A.V., Markushin A.N., Tikhonov O.A. Materialy Vserossiiskoi nauchno-prakticheskoi konferentsii s mezhdunarodnym uchastiem “Novye tekhnologii, materialy i oborudovanie rossiiskoi aviakosmicheskoi otrasli”. In 2 vols. Kazan, Akademiya nauk Respubliki Tatarstan, 2016, pp. 412-418.

16. Lieuwen T.C., Yang V. (eds) Combustion Instabilities In Gas Turbine Engines: Operational Experience, Fundamental Mechanisms, and Modeling. Progress in Astronautics and Aeronautics, 2005, vol. 210, 657 p. DOI: 10.2514/5.9781600866807.0000.0000

17. Kiesewetter F., Konle M., Sattelmayer T. Analysis of Combustion Induced Vortex Breakdown Driven Flashback in a Premix Burner with Cylindrical Mixing Zone. Journal of Engineering for Gas Turbines and Power, 2007, vol. 129, no. 4, pp. 929–936. DOI: 10.1115/1.2747259

18. Taylor S.C. Burning Velocity and the Influence of Flame Stretch. PhD thesis, University of Leeds, Department of Fuel and Energy, 1991, 332 p.

19. Yi T., Gutmark E.J. Real-time prediction of incipient lean blowout in gas turbine combustors. AIAA journal, 2007, vol. 45, no. 7, pp. 1734-1739. DOI: 10.2514/1.25847

20. Sabirzyanov A.N., Markushin A.N., Baklanov A.V. Materialy Mezhdunarodnoi nauchno-tekhnicheskoi konferentsii (22-24 June 2016; Samara) “Problemy I perspektivy razvitiya dvigatelestroeniya”, Samara, Samarskii natsional’nyi issledovatel’skii universitet imeni akademika S.P. Koroleva, 2016, pp. 215-217.

21. Agregaty gazoperekachivayushchie s gazoturbinnym privodom. Obshchie tekhnicheskie usloviya. GOST 28775-90 (Gas pumping units driven with gas turbine. General specifications, State Standard 28775-90), Moscow, Standartinform, 2005, 12 p.

22. Gokulakrishnan P., Fuller C.C., Klassen M.S. et al. Experiments and modeling of propane combustion with vitiation. Combustion and Flame, 2014, vol. 161, no. 8, pp. 2038-2053. DOI: 10.1016/j.combustflame.2014.01.024

23. Moses C.A., Roets P.N.J. Properties, Characteristics and Combustion Performance of Sasol Fully Synthetic Jet Fuel. Journal of Engineering for Gas Turbines and Power, 2009, vol. 131, no. 4, 041502-041502-17. DOI: 10.1115/1.3028234

24. Zubrilin I.A., Didenko A.A., Dmitriev D.N., Gurakov N.I., Hernandez M.M. Combustion process effect on the swirled flow structure behind a burner of the gas turbine engine combustion chamber. Aerospace MAI Journal, 2019, vol. 26, no. 3, pp. 124-136.