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ABSTRACT
Presented paper is focused on the influence of additional combustor chamber named inter turbine burner on turbofan engine unit parameters. Investigation has been made how changing selected engine parameters affect its performance. A comparison has been made between the baseline turbofan engine and the engine with ITB. Engine thermodynamics model was prepared in MATLAB software. Main combustion chamber was fueled by kerosene, commmonly used in aviation transport, while inter turbine burner by alternative fuel. As an alternative fuel were choose liquid hydrogen and methane. Numerical researches were carried out for take-off conditions. Engine specific thrust and specific fuel consumption were obtained as a function of bypass ratio, turbine inlet temperature, fan pressure ratio, HPC and LPC pressure ratio. The results of the study indicate that hybrid engine with additional combustion chamber fueled by hydrogen fuel is more efficient than other studied cases.
 
REFERENCES (20)
1.
AL-BAGHDADI, M. An overview of hydrogen as an alter-native fuel. Encyclopedia 2020. https://doi.org/10.32545/encyc....
 
2.
BURSTON, M., CONROY, T., SPITERI, M. et al. Concep-tual design of sustainable liquid methane fuelled passenger aircraft. 20th ISPE International Conference on Concurrent Engineering. 2013. https://doi.org/10.3233/978-1-....
 
3.
EL-SAYED, A.F. Aircraft propulsion and gas turbine engines. CRC Press. 2017.
 
4.
YIN, F., RAO, A.G., van Buijtenen J.P. Performance characteristic of a multi-fuel hybrid engine. Volume 2: Aircraft Engine; Coal, Biomass and Alternative Fuels; Cycle Innovations. ASME 2012.
 
5.
GUTHE, F., HELLAT, J., FLOHR, P. The reheat concept: the proven pathway to ultra-low emissions and high efficiency and flexibility. ASME Turbo Expo 2007: Power for Land, Sea and Air. May 14-17, 2007, Montreal.
 
6.
LEVY, Y., ERENBURG, V., SHERBAUM, V. et al. Development of combustor for a hybrid turbofan engine. International Journal of Turbo and Jet Engines. December 2019, https://doi.org/10.1515/tjj-20....
 
7.
LIEW, K.H., URIP, E., YANG, S.L. et al. Performance cycle analysis of turbofan engine with interstage turbine burner. Journal of Propulsion and Power. 2006, 22(2). https://doi.org/10.2514/1.1339....
 
8.
LIU, F., SIRIGNANO, W.A. Turbojet and turbofan engine performance increase through turbine burners. Journal of Propulsion and Power. 2001, 17(3). https://doi.org/10.2514/2.5797.
 
9.
BOYCE, M.P. Gas turbine engineering hand-book. Butterworth-Heinemann. Fourth edition, 2012.
 
10.
MARSZAŁEK, N. Performance analysis of turbofan engine with additional combustion chamber fueled by alternative fuel. Combustion Engines. 2019, 179(4), 249-253. https://doi.org/10.19206/CE-20....
 
11.
PERPIGNAN, A.A.V., RAO, A.G. Effects of chemical reaction mechanism and NOx formation pathways on an inter-turbine burner. The Aeronautical Journal. 2019, 123(1270), 1898-1918. https://doi.org/10.1017/aer.20....
 
12.
RAO, A.G., YIN, F., van BUIJTENEN, J.P. A hybrid en-gine concept for multi-fuel blended wing body. Aircraft En-gineering and Aerospace Technology. 2014, 86(6), 483-493. https://doi.org/10.1108/AEAT-0....
 
13.
SARAVANAMUTTO, H., ROGERS, G., COHEN, H. et al. Gas turbine theory. Pearson Prenticle Hall. England 2009.
 
14.
SIRIGNANO, W.A., LIU, F. Performance increases for gas-turbine engines through combustion inside the turbine. Journal of Propulsion and Power. 1999, 15(1), 111-118. https://doi.org/10.2514/2.5398.
 
15.
TANG, K., RAO, A.G., van BUIJTENEN, J.P. Conceptual study of a hybrid turbofan engine with inter turbine burner. Proceedings of the ASME Turbo Expo 2010. ASME. 2010, 239-248. ASME. https://doi.org/10.1115/GT2010....
 
16.
VOGELER, K. The potential of sequential combustion for high bypass jet engines. Proceedings of the International Gas Turbine and Aeroengine Congress and Exhibition. 1998. https://doi.org/10.1115/98-GT-....
 
17.
YIN, F., RAO, A.G. Off-design performance of an interstage turbine burner turbofan engine. Journal of Engineering for Gas Turbines and Power. 2017. https://doi.org/10.1115/1.4035....
 
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