Two-combustor turbofan engine performance analysis

• Autorzy: Jakubowski R.

Identyfikatory

DOI

10.5604/12314005.1133191

• Języki publikacji: EN

Abstrakty

EN

A conception of a two-combustor turbofan engine is the main scope of this paper. At the beginning, the problems of turbofan engines development are briefly discussed as a background of this work. In this part the turbofan engines innovation activities are presented. It is mentioned the engine’s innovations consists of many aspects but some important ones are: lowering of production operation cost, maintenance, reduction of noise and exhaust gases emission while engine reliability should stay on the same level or event increase. Next, the conception of turbofan engine with two combustors is presented in this context. Some positive aspects for environment, production and maintenance of such engine are discussed. Then the thermodynamic cycle of two-combustor engine is presented and analysed. On this basis, the engine numerical model is prepared. Next, some information about the model simplifications and calculations done to determine performance of the engine is presented. Then the results of the simulation calculations of the engine performance are presented and discussed. The relationship of engine thrust and specific fuel consumption vs. engine flight conditions are shown. Based on the results there were discussed the advantages and disadvantages of two combustors engine as an airplane propulsion are specified. The conclusions are formulated and presented in the last part of the paper.

Słowa kluczowe

EN

jet engine; turbofan engine; engine performance; airplane engine development

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2014
• Tom: Vol. 21, No. 3
• Strony: 141--148
• Opis fizyczny: Bibliogr. 10 poz., rys.

Twórcy

autor

Jakubowski R.

• Department of Aircrafts and Aircraft Engines Rzeszow University of Technology Powstancow Warszawy Av. 8, 35-959 Rzeszow, Poland tel.: [phone]fax [phone]

Bibliografia

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• [4] Lefebvre, A. H., Gas Turbine Combustion, 3th ed., Taylor and Francis Group, LLC. 2010.
• [5] Liew, K. H., Urip, E., Yang, S. L., Parametric Cycle Analysis of a Turbofan with Interstage Turbine Burner, Journal of Propulsion and Power, Vol. 21, No. 3, 2005.
• [6] Liew, K. H., Urip, E., Yang, S. L., Mattingly, J. D., Marek, C. J., Performance Cycle Analysis of a Two-spool Separate-exhaust Turbofan with Interstage Turbine Burner, Journal of Propulsion and Power, Vol. 22, No. 2, pp. 411-416, 2006.
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• [9] Walsh, P. P., Fletcher, P., Gas Turbine Performance, 2nd ed., Blackwell Publishing and ASME, Fairfield, pp. 227 and 282, NJ 2004.
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