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Wyszukujesz frazę "turbine cooling" wg kryterium: Temat


Wyświetlanie 1-3 z 3
Tytuł:
Preliminary analysis of thermodynamic cycle of turbofan engine fuelled by hydrogen
Autorzy:
Marszalek, N.
Powiązania:
https://bibliotekanauki.pl/articles/247482.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
liquid hydrogen
turbofan engine
turbine cooling
engine thermodynamic cycle
engine performance
Opis:
Presented article is focus on analysis of the effect of hydrogen fuel on turbofan engine performance. Selected properties of hydrogen and possibility of introduction in civil aviation were discussed. Hydrogen implementation as aviation fuel offers obvious advantages such as low emission of combustion product, higher payload, lower fuel consumption, general availability but also poses great technical challenges. The most important aspect is to ensure engine operational safety at very high level. Hydrogen implementation would eliminate the aviation dependence of exhausting sources of fossil fuels especially of crude oil. The thermodynamic model of turbofan engine was implemented in MATLAB environment. Accepted assumptions have been discussed. Turbine cooling process has been included in the numerical model. Working fluid was modelled as semi-perfect gas. Analysis was carried out for take-off and design point conditions. Engine performances were compared for two kinds of applied fuels: liquid hydrogen and commonly used in turbine engines kerosene. Combustion heat of hydrogen is about three time higher than in comparison with conventional turbine engine fuel, what exert significant influence on engine performance. The results of engine thermodynamic cycle analysis indicate the increase in specific thrust and significant reduction of specific fuel consumption. The results are presented in tabular form and on the graphs. Obtained results have been discussed and the direction of further research was indicated.
Źródło:
Journal of KONES; 2018, 25, 3; 347-354
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Modeling and analysis of jet engine with cooling turbine
Autorzy:
Jakubowski, R.
Powiązania:
https://bibliotekanauki.pl/articles/247838.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet engine
modelling of jet engine
modelling of jet engine with cooling turbine
Opis:
The problems of the turbojet engines with a cooling turbine modelling are discussed in the paper. The cooling systems of the contemporary jet engines are briefly described in the first part of the paper. Than the models of various turbine, cooling systems are presented and discussed. The main scope of the paper is the turbine cooling system consisted of internal convection cooling and external film cooling of turbine blades. This cooling system is commonly used in contemporary military and civil turbojet engines. The model of the internal-external cooling turbine incorporated in the overall jet engine model is presented and discussed. Some simplifying assumptions are discussed. Then the results of the jet engine calculation taking into account the proposed model are presented in the tables. The results are compared with results obtained by simple model of the jet engine with cooling turbine. The simple model is commonly applied for 1D turbojet engine analysis. Based on this analysis, some aspects of the turbojet engine calculation with reference to different models applied for description of the turbine cooling process are presented and discussed. The analysis allowed formulating some conclusions, which are presented in the final part of the paper. One of them is that proposed model of cooling turbine allows to calculate of coolant mass flow, while the simple models of cooling turbine require the assumption of coolant mass. By this way the calculation results accuracy by the use of simple model, strictly depend on the proper assumption of coolant mass flow.
Źródło:
Journal of KONES; 2012, 19, 2; 235-243
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical simulation of thermally loaded aircraft engine turbine blade covered with thermal barrier coating - TBC
Autorzy:
Łazarczyk, M.
Domański, R.
Powiązania:
https://bibliotekanauki.pl/articles/246553.pdf
Data publikacji:
2012
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
aircraft engines
turbine
TBC
coating
blade cooling
Opis:
The objective of this thesis is to present the impact of the turbine blade cooling on blade material temperature as well as to assess advantages and disadvantages of applied cooling method (TBC coating combined with internal cooling). To calculate the conjugated heat transfer analysis generating 3d model and mesh of the blade and its cooling was required. Model mesh was covered with boundary layer in order to properly simulate conditions near the blade walls and obtain accurate results. Calculated blade was put in the canal simulating hot combustion gasses flow. Geometry of model described above was created using Unigraphics NX5 program based on drawings obtained from available literature, and data acquired from the Internet. The discretization was done in commercial pre--processor GAMBITŽ. Conjugated heat transfer analysis was conducted in program FLUENTŽ for two different cases, where the TBC material properties were changed. The goal of this thesis was to obtain temperature fields and distribution in the turbine blade airfoil and to evaluate if applied cooling is sufficient to cool down this thermally loaded part of the engine. Calculated results show that proposed blade heat protection with TBC and internal cooling canal is insufficient during steady state condition, especially on the blade leading and trailing edge. In these two locations, the TBC coating is overheated, and the high temperature level of blade material is unacceptable for materials used in jet engine turbine industry.
Źródło:
Journal of KONES; 2012, 19, 3; 271-277
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
    Wyświetlanie 1-3 z 3

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