Study of bypass ratio increasing possibility for turbofan engine and turbofan with inter turbine burner

• Autorzy: Jakubowski Robert

Identyfikatory

DOI

10.2478/kones-2019-0033

• Języki publikacji: EN

Abstrakty

EN

Current trends in the high bypass ratio turbofan engines development are discussed in the beginning of the paper. Based on this, the state of the art in the contemporary turbofan engines is presented and their change in the last decade is briefly summarized. The main scope of the work is the bypass ratio growth analysis. It is discussed for classical turbofan engine scheme. The next step is presentation of reach this goal by application of an additional combustor located between high and low pressure turbines. The numerical model for fast analysis of bypass ratio grows for both engine kinds are presented. Based on it, the numerical simulation of bypass engine increasing is studied. The assumption to carry out this study is a common core engine. For classical turbofan engine bypass ratio grow is compensated by fan pressure ratio reduction. For inter turbine burner turbofan, bypass grown is compensated by additional energy input into the additional combustor. Presented results are plotted and discussed. The main conclusion is drawing that energy input in to the turbofan aero engine should grow when bypass ratio is growing otherwise the energy should be saved by other engine elements (here fan pressure ratio is decreasing). Presented solution of additional energy input in inter turbine burner allow to eliminate this problem. In studied aspect, this solution not allows to improve engine performance. Specific thrust of such engine grows with bypass ratio rise – this is positive, but specific fuel consumption rise too. Classical turbofan reaches lower specific thrust for higher bypass ratio but its specific fuel consumption is lower too. Specific fuel consumption decreasing is one of the goal set for future aero-engines improvements.

Słowa kluczowe

EN

aero engine; turbofan engine; combustion engines; aero engine development; turbine inter stage burner

• 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: 2019
• Tom: Vol. 26, No. 2
• Strony: 61--68
• Opis fizyczny: Bibliogr. 20 poz., rys.

Twórcy

autor

Jakubowski Robert

• Department of Aircrafts and Aircraft Engines Rzeszow University of Technology Powstańców Warszawy Av. 8, 35-959 Rzeszow, Poland tel.: [phone] fax: [phone]
• MTU Aero Engines Poland Tajęcina 108, 36-002 Tajęcina, Poland tel.: [phone]

Bibliografia

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Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).