Computational study of an aerodynamic flow through a micro-turbine engine combustor
Abstract
The study presents 3-D numerical simulations of aerodynamic flow inside micro-turbine engine combustion chamber. The process of creation of a numerical grid and its properties are described, and then on the basis of gas-dynamic calculation of the theoretical engine cycle boundary conditions were specified. For the assumed boundary conditions, numerical simulations of aerodynamics of “cold” air flow through the combustion chamber (without fuel supply to the interior) were performed. Numerical experiment was also conducted, allowing the investigation of the influence of thermal energy supply into the combustion chamber on the aerodynamic flow through the chamber. The work ends with discussion of the results, in particular concerning the loss of pressure in the combustion chamber and possible design changes to minimize them.References
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[16] A. H. Lefebvre, Gas Turbine Combustion, Taylor & Francis, Ann Arbor, 1999.
[17] K. Hunecke, Fundamentals of Theory, Design and Operation, Motorbooks, International Publishers and Wholesalers, 1997.
[18] R. Łapucha, Komory spalania silników turboodrzutowych, Wydawnictwa Naukowe Instytutu Lotnictwa, Warszawa, 2004.
[19] J. D. Mattingly, Aircraft Engine Design, American Institute of Aeronautics and Astronautics, 2002.
[2] Home Built Model Turbines, Traplet Publications Ltd, 2005, K. Schreckling.
[3] Gas Turbines for Model Aircraft, Traplet
Publications Ltd, 2003, K. Schreckling,
[4] Guide to Microturbines, Fairmont Press, 2004, B. F. Kolanowski
[5] G. Bouldier, L. Y. M. Gicquel, T. Poinsot, D. Bissieres and C. Berat, Comparison of LES, RANS and experiments in aeronautical gasturbine combustion chamber. Proceedings of the Combustion Institute. Vol. 31, No. 2, (2007), 3075-3082.
[6] C. A. Gonzales, K. C. Wong and S. Armfield, Computational study of a micro-turbine engine combustor using large eddy simulation and Reynolds average turbulence models, ANIZAM J. 49, (2008), 407-422.
[7] P. D. Marsh, RCU Review: Twenty Years of Micro-turbojet Engines, Magazine “Horizon, (2003), 1-8
[8] M. D. Agrawal and S. Bharani, Performance Evaluation of a Reverse-flow Gas Turbine Combustor using Modified Hydraulic Analogy. The institute of Engineers India. Journal MC, (2004), 34-44.
[9] H. S. Lee and J. J. Yoon, The Study on Development of Low NOx Combustor with Lean Burn Characteristics for 20 kW class Microturbine, Proceedings of ASME Turbo Expo, 14-17 June, Viena, Austria, 2004.
[10] R. Tuccillo and M. C. Cameretti, Comparing different solutions for the micro-gas turbine combustor, Proceedings of ASME Turbo Expo, 14-17 June, Viena, Austria, 2004.
[11] S. Adahia, A. Iwamotoa, S. Hayashib, H. Yamadab and S Kaneko, Emissions in combustion of lean methane-air and biomass-air mixtures supported by primary hot burned gas in multi-stage gas turbine combustor, Proceedings of the Combustion Institute. Vol. 31, No. 2, (2007), 3131-3138.
[12] S. Antas and P. Wolański, Obliczenia
termogazodynamiczne lotniczych silników
turbinowych, Wydawnictwo Politechniki
Warszawskiej, Warszawa, 1989.
[13] P. Dzierżanowski, Turbinowe silniki odrzutowe, Wydawnictwa Łączności i Komunikacji, Warszawa, 1983.
[14] S. James, J. Zhu and M. Anand, Large-Eddy Simulation as a gas turbine combustor at different pressure and swirl conditions, Applied Thermal Engineering, Vol. 19, No. 19, 1999, pp. 949-967.
[15] M. Gieras, Komory spalania silników turbinowych, organizacja procesu spalania, Oficyna wydawnicza Politechniki Warszawskiej, Warszawa, 2010.
[16] A. H. Lefebvre, Gas Turbine Combustion, Taylor & Francis, Ann Arbor, 1999.
[17] K. Hunecke, Fundamentals of Theory, Design and Operation, Motorbooks, International Publishers and Wholesalers, 1997.
[18] R. Łapucha, Komory spalania silników turboodrzutowych, Wydawnictwa Naukowe Instytutu Lotnictwa, Warszawa, 2004.
[19] J. D. Mattingly, Aircraft Engine Design, American Institute of Aeronautics and Astronautics, 2002.
Published
2012-06-30
How to Cite
GIERAS, Marian Mirosław; STAŃKOWSKI, Tomasz.
Computational study of an aerodynamic flow through a micro-turbine engine combustor.
Journal of Power Technologies, [S.l.], v. 92, n. 2, p. 68--79, june 2012.
ISSN 2083-4195.
Available at: <https://papers.itc.pw.edu.pl/index.php/JPT/article/view/317>. Date accessed: 19 apr. 2024.
Issue
Section
Aircraft Engines
Keywords
aerodynamic flow, engine combustor, pressure loss
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