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Wyszukujesz frazę "inter turbine burner" wg kryterium: Temat


Wyświetlanie 1-3 z 3
Tytuł:
The impact of thermodynamics parameters of turbofan engine with ITB on its performance
Autorzy:
Marszałek, Natalia
Powiązania:
https://bibliotekanauki.pl/articles/2097464.pdf
Data publikacji:
2020
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
inter turbine burner
turbofan engine
liquid hydrogen
alternative fuels
ITB
silnik turbowentylatorowy
ciekły wodór
paliwa alternatywne
Opis:
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.
Źródło:
Combustion Engines; 2020, 59, 3; 16--22
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Performance analysis of turbofan engine with additional combustion chamber fueled by alternative fuel
Autorzy:
Marszałek, Natalia
Powiązania:
https://bibliotekanauki.pl/articles/133315.pdf
Data publikacji:
2019
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
alternative fuels
liquid hydrogen
liquid methane
inter turbine burner
ITB
turbofan engine
paliwa alternatywne
ciekły wodór
ciekły metan
silnik turbowentylatorowy
Opis:
Presented paper is focused on the performance analysis of turbofan engine with additional combustion chamber fueled by alternative fuel. Additional combustion chamber was situated between high pressure turbine and low pressure turbine. Such configuration is also know under the name inter turbine burner (ITB). As an alternative fuels burn in additional combustion chamber were selected cryogenics fuels: liquid hydrogen and liquid methane. The main combustion chamber was supplied by conventional aviation fuel - kerosene. Thermodynamic model of turbofan engine with ITB was implemented in MATLAB environment. The problem of modeling an additional combustion chamber was presented. Analysis was carried out for take-off conditions. Obtained results indicate that implementation of ITB exert a positive influence on engine performance result in thrust increase.
Źródło:
Combustion Engines; 2019, 58, 4; 249-253
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Study of bypass ratio increasing possibility for turbofan engine and turbofan with inter turbine burner
Autorzy:
Jakubowski, Robert
Powiązania:
https://bibliotekanauki.pl/articles/244907.pdf
Data publikacji:
2019
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aero engine
turbofan engine
combustion engines
aero engine development
turbine inter stage burner
Opis:
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.
Źródło:
Journal of KONES; 2019, 26, 2; 61-68
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
    Wyświetlanie 1-3 z 3

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