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Wyszukujesz frazę "turbine jet engine" wg kryterium: Temat


Tytuł:
Experimental determination of compressor map of the DGEN 380 engine compressor using the WESTT CS/BV turbine engine simulator
Autorzy:
Pazura, Karolina
Orkisz, Marek
Powiązania:
https://bibliotekanauki.pl/articles/2097512.pdf
Data publikacji:
2021
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
compressor map
engine bench
turbofan jet engine
turbine engine
mass flow rate
mapa kompresora
ława silnika
silnik turbowentylatorowy
silnik turbinowy
masowy wskaźnik szybkości płynięcia
Opis:
Currently aviation focuses mainlly on increasing the economy and ecology of engines. Production of NOx, CO2 and SO2 adversaly impacts the environment. Parallel goal to minimize SFC to achieve both lower: emission and mission costs. The optimization of components is thus very important. One of the ways of optimizing cycle is doing that based on compressor maps. However it is very expensive to plot one since experimental work needs to be done. The aim of this article is to present a methodology of creating compressor map based on ENGINE ANALOGY. There was used the virtual bench WESTT CS/BV for tests to receive pressure ratio and mass flow of DGEN 380 for three different values of flight speed and altitude, while the rotational speed was changed. The construction similarity of CFM 56-5B and APS 3200 gives the opportunity to plotted compressor maps using the engine analogy without the need for an experiment or using the virtual bench.
Źródło:
Combustion Engines; 2021, 60, 2; 26--31
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
The assessment of the technical condition of SO-3 engine turbine blades using an impulse test
Autorzy:
Milewicz, Julia
Mokrzan, Daniel
Szymański, Grzegorz M.
Powiązania:
https://bibliotekanauki.pl/articles/2097507.pdf
Data publikacji:
2021
Wydawca:
Polskie Towarzystwo Naukowe Silników Spalinowych
Tematy:
jet engine
turbine
modal analysis
resonance
silnik odrzutowy
turbina
analiza modalna
rezonans
Opis:
The paper presents the effects of the application of an experimental impulse test as a method of diagnosis of the technical condition of an SO-3 engine turbine blade fitted in a TS-11 Iskra aircraft. The aim of the test was to investigate the frequency characteristics of the blades and discuss differences between the frequency spectrum of the investigated component before and after its damage. The acoustic response measurements were performed to the signal generated by an impact hammer on the fully functional and intentionally damaged blades. The recorded signals were converted from the domain of time to the domain of frequency using the Fast Fourier Transform (FFT). The results of the FFT were the Frequency Response Functions (FRF) of the sound of the blades, based on which the statistical analysis of the resonance frequencies was carried out. The influence of the mechanical damage of the blade on the shape and characteristics of the frequency spectrum was confirmed, which substantiated the effectiveness of the impulse test in the diagnostic assessment of jet engine components.
Źródło:
Combustion Engines; 2021, 60, 1; 24--29
2300-9896
2658-1442
Pojawia się w:
Combustion Engines
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of Impact of Gust Angle and Velocity on the Position of Stagnation Point
Autorzy:
Frant, Michał
Kozakiewicz, Adam
Kachel, Stanisław
Powiązania:
https://bibliotekanauki.pl/articles/102313.pdf
Data publikacji:
2020
Wydawca:
Stowarzyszenie Inżynierów i Techników Mechaników Polskich
Tematy:
inlet vortex
numerical fluid mechanics
turbine jet engine
wir wlotowy
numeryczna mechanika płynów
turbinowy silnik odrzutowy
Opis:
This paper presents the selected issues regarding the design of a complex object of a turbine jet engine inlet duct model for the purposes of numerical analysis related to the phenomenon of inlet vortex formation. The authors described the process of discretisation in the matter in question and presented certain guidelines for preparing and conducting discretisation of the computational area. The authors presented an exemplary test findings analysis to verify the accuracy of the object’s shape, computation grid as well as the selection of the boundary conditions and solution algorithm. The main part of the paper regards the analysis of changes in the location of the vortex (point of stagnation) based on an examination of the impact related to the changes in the velocity and inlet and gust angles. The authors sought to determine the areas and regularity of points of stagnation.
Źródło:
Advances in Science and Technology. Research Journal; 2020, 14, 4; 49-57
2299-8624
Pojawia się w:
Advances in Science and Technology. Research Journal
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Impact of work of turbine adaptive engines for the natural environment
Autorzy:
Ćwik, D.
Kowalski, M.
Steżycki, P.
Powiązania:
https://bibliotekanauki.pl/articles/246614.pdf
Data publikacji:
2018
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
noise of aircraft engines
environmental impact
jet engine turbine
emission of toxic compounds
aircraft engines
turbine jet engine
Opis:
The article describes the problem of the operation of turbine jet, adaptive engine work on the natural environment. In particular, the analysis of noise generated by turbine jet engines has been made. It points out possible directions of noise decrease with particular emphasis upon structural changes within the engines, the task of which is to reduce the noise mission. The example of the modernization is based upon the “bypass” type of one-flow turbine jet engine. The essay contains theoretical basis of calculation of the noise emission level and the results, which graphically indicate a relative level of noise of this type of engine depending upon the amount of discharged air and the diameter of the discharge nozzle and the radius, upon the basis of which the noise level is determined. This work also includes a comparison of the relative noise level of this type of engine with regard to one-flow turbine engine equipped with the function of air discharge to the environment and with regard to two-flow turbine jet engine equipped with air stream flow mixing device. The use of low-emission combustion chambers in the "bypass" turbine engine was indicated. This allowed addressing the problem of emissions of toxic exhaust components by this type of aircraft engines. At the same time, the dependence of this emission related to the mass of fuel used on the engine's thrust range was indicated. The article was concluded with a short summary.
Źródło:
Journal of KONES; 2018, 25, 4; 509-516
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
A method of assessing the tendency of aviation fuels to generate thermal degradation products under the influence of high temperatures
Autorzy:
Sarnecki, J.
Gawron, B.
Powiązania:
https://bibliotekanauki.pl/articles/246718.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet fuel
turbine engine
thermal stability
test rig
non-standard method
Opis:
The subject of the article concerns the issues associated with thermal degradation of aviation fuels under high temperature conditions. Due to the intensive development towards increasingly higher thermal loads for both, turbine aviation engines, as well as the used fuels, the issue of thermal stability of the fuel itself is extremely important. In aviation, the fuel, apart from direct participation in energy generation during the combustion process of a fuel-air mixture, also takes part in the heat transfer in many aircraft systems. As a result, requirements in terms of the fuel’s thermal potential are increasingly higher. The standard method for determining the thermal stability of fuel executed on a JFTOT device proves to be insufficient in the context of the appearing issues in current operation. The article presents a non-standard approach to the assessment of aviation fuel thermal degradation with the use of a specialist test rig. The authors believe that the presented methodology and the measurement capabilities of the test rig are valuable supplementary material for the standardized thermal stability test. It allows more thoroughly understanding the phenomena undergoing in the fuel impacted by high temperatures. The article has been prepared within the research project no. 2011/01/D/ST8/06567 funded by the National Science Centre in Poland.
Źródło:
Journal of KONES; 2017, 24, 4; 377-384
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Influence of selected parameters on micro gas turbine compressor design
Autorzy:
Czarnecki, M.
Olsen, J.
Powiązania:
https://bibliotekanauki.pl/articles/243625.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet engine
gas turbine
design
trend prediction
centrifugal compressor
Opis:
The design a micro gas turbine engine is a process that requires analysis of a number of parameters. The initial stage requires consideration of more than 40 parameters [3]. The whole analysis can be made with analytical tools. However, these kinds of tools are limited to preliminary designs. After 1D-calculations and the establishment of the first CAD model, it is recommended to identify the sensitivity of the design. With a modern numerical environment such as ANSYS CFX, it is possible to predict a trend that gives the designer a 3D feedback about the initial design behaviour. For presented centrifugal compressor case, the selected parameters are vaneless diffuser space, design angle and number of stator blades. For qualitative evaluation – important results that influence design are mass flow rate, total pressure and isentropic efficiency. These results are important to turbojet engine performance and efficiency. All chosen parameters respond to given criteria. Validation and verification is still required due numerical errors that are included in CFD modelling. The advantage of 3D prediction is the possibility to eliminate gross errors before parts are sent into production.
Źródło:
Journal of KONES; 2017, 24, 3; 45-52
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Korozja wysokotemperaturowa w transporcie
High-temperature corrosion in transport
Autorzy:
Włodarkiewicz, A.
Rokosz, K.
Powiązania:
https://bibliotekanauki.pl/articles/311048.pdf
Data publikacji:
2017
Wydawca:
Instytut Naukowo-Wydawniczy "SPATIUM"
Tematy:
silnik odrzutowy
turbiny gazowe
korozja wysokotemperaturowa
jet engine
gas turbine
high-temperature corrosion
Opis:
Rozwój transportu samochodowego, kolejowego, morskiego jak i lotniczego jest jednym z ważniejszych wyzwań inżynierskich i logistycznych teraźniejszych czasów. Świat stając się "globalną wioską" wymusił rozwój głównie transportu lotniczego, ze względu na możliwość zwiększenia szybkości przewożenia ludzi oraz towarów na bardzo duże odległości, co w istotny sposób wpłynęło również na rozwój produkcji silników odrzutowych. Z tego względu korozja gazowa, która występuje w tych silnikach jest tematem nadal aktualnym zarówno dla przemysłu jak i nauki. W artykule omówiono między innymi zastosowanie silników odrzutowych w transporcie lądowym i powietrznym, materiały używane do ich produkcji, jak i mechanizmy korozji wysokotemperaturowej oraz metody jej zapobiegania.
The development of car, rail, maritime and air transport are among the most important engineering and logistical challenges of modern times. The world's "global village" reality is accelerating the development of mainly air transport in the pursuit of developing high speed transfer of people and goods over very long distances, and this in turn has significantly contributed to the development of jet engines. Therefore, the gas corrosion that occurs in jet engines is a topic that is still relevant for both industry and science. In this paper, among other things, the use of jet engines in land and air transport, the materials used to produce them, as well as the mechanisms of high temperature corrosion and methods of preventing it, are discussed.
Źródło:
Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 7-8; 442-445
1509-5878
2450-7725
Pojawia się w:
Autobusy : technika, eksploatacja, systemy transportowe
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Modern methods of identification design conditions for single stage micro scale centrifugal compressor
Autorzy:
Czarnecki, M.
Olsen, J.
Powiązania:
https://bibliotekanauki.pl/articles/243293.pdf
Data publikacji:
2017
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet engine
gas turbine
design
off design
trend prediction
centrifugal compressor
Opis:
Micro scale gas turbine engines are low cost engines. They share their compressor impeller with automotive turbochargers. An identified design condition for the selected impeller is a critical stage of the design process. This process is had difficulties due the large number of manufacturers that provide OEM parts. It is common practice that one OEM part number provides the same impeller at different design revision. In general, parts are interchangeable but in detail, they differ slightly in terms of dimensions and performance. To avoid under predict or over predict inputs data, it is important to check the design parameters with as many methods as possible. In practice, the designer could rely on analytical methods, which are straightforward limited to the applied design. When shared its (compressor operation) it is recommended additional information be provided by computational fluid dynamics that produces a three-dimensional look into the predesign. That allows avoidance of future design failure and reduces both design time and prototype manufacturing costs.
Źródło:
Journal of KONES; 2017, 24, 2; 73-84
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Estymacja punktu pracy sprężarki i jego parametrów w oparciu o charakterystyki sprężarek
Estimating the compressors works point and its parameters based on performance of compressors
Autorzy:
Kozakiewicz, A.
Powiązania:
https://bibliotekanauki.pl/articles/212550.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
sprężarka osiowa
opływ palisady sprężarki
pompaż
turbinowe silniki odrzutowe
axial compressor
flow around grid of blades
surge
turbine jet engine
Opis:
W artykule przedstawiono problematykę związaną z estymacją punktu pracy sprężarki w oparciu ojej charakterystykę. Analizowano problematykę związaną z pracą poszczególnych stopni zespołu ze względu zmiany kąta natarcia strumienia w wyniku zmian prędkości obrotowych. Przedstawiono wyniki analizy numerycznej opływu stopnia sprężarki. Zanalizowano zmianę położenia linii pracy silnika w wyniku wyboru kąta natarcia na zakresie obliczeniowym. Zaprezentowano problematykę ze zmianą warunków pracy poszczególnych stopni sprężarki.
This paper presents problems concerning the estimation of the point works of the compressor and its parameters based on its characteristics. Problems connected with the work of individual compressor stages regarding the change of the angle of attack stream as a result of changes in rotating velocities were analysed Results of the numerical analysis of the stage compressor's round flow were demonstrated. The- dislocation of the work line of the engine as a result of the choice of the angle of attack on the computational range were presented. Problems with modifying work conditions for individual compressor stages were presented.
Źródło:
Prace Instytutu Lotnictwa; 2016, 3 (244); 363-372
0509-6669
2300-5408
Pojawia się w:
Prace Instytutu Lotnictwa
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Parametry określające wejście lotniczego silnika turbinowego w niestateczną pracę sprężarki
Parameters defining entry of the turbine engine into the unstable work of the compressor
Autorzy:
Kozakiewicz, A.
Kowalski, M.
Powiązania:
https://bibliotekanauki.pl/articles/213610.pdf
Data publikacji:
2016
Wydawca:
Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:
sprężarka osiowa
pompaż
lotnicze silniki turbinowe
portret fazowy
axial compressor
surge
turbine jet engine
phase portrait
Opis:
W artykule przedstawiono przyczyny generowania nierównomiernego pola parametrów na wejściu do sprężarki lotniczego silnika turbinowego i ich wpływ na kinematykę strumienia powietrza przy obniżającej się wytrzymałości zmęczeniowej łopatki sprężarkowej. Dokonano analizy przebiegu zmian momentu obrotowego wirnika jako funkcji czasu. Przedstawiono przebiegi podstawowych parametrów pracy silnika turbinowego podczas wchodzenia w zakres niestatecznej pracy. Określono istotną rolę w tej ocenie zmian pierwszej pochodnej momentu obrotowego w relacji do zmian przyspieszeń wirnika, która może być istotnym sygnałem o możliwości wystąpienia pompażu w sprężarce. Parametr ten może być sygnałem dla układu sterowania do eliminowania tego szkodliwego zjawiska. Przedstawiono także dynamikę silnika wspartą badaniem podczas pompażu poprzez opracowanie portretów fazowych podstawowych parametrów jego pracy. Artykuł zawiera analizę dynamiki zmian temperatury spalin.
This paper presents reasons for generating non uniform area of parameters on the entry to the compressor of the turbine engine and their influence on the air stream kinematics at the decreasing fatigue strength of the compressor blade. Analysis of the course of the torque rotor changes as the function of time was presented. Courses of basic parameters of the turbine engine work during the ingress into the range of unstable work were presented. The crucial role in this estimation of changes of the first differential of the torque in relation to changes in acceleration of the rotor which can be a significant signal of the possibility of surge occurrence in the compressor were defined. This parameter can be a signal for the control system to eliminate this bad phenomenon. The dynamics of the engine supported with the research during surge through the study of parameters'phase portraits of its work were also presented. The article contains analysis of the dynamics of changes in temperature of combustion gas.
Źródło:
Prace Instytutu Lotnictwa; 2016, 3 (244); 373-384
0509-6669
2300-5408
Pojawia się w:
Prace Instytutu Lotnictwa
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Aircraft fuel consumption and emissions during cruise, effect of the jet stream
Autorzy:
Głowacki, P.
Kawalec, M.
Powiązania:
https://bibliotekanauki.pl/articles/242826.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
turbine engine
cruise
jet stream
exhaust emissions
Opis:
Article presents the results of fuel consumption calculation during cruise compared to remaining aircraft flight phases. Based on fuel consumption, methodology of pollutants quantitative estimation emitted by turbine engines has been developed. Material provides evaluation results of aircraft CO2, CO and NOx effusion using fuel consumption data taken from aircraft Flight Data Recorder (FDR) during cruise of various aircraft types. Knowledge of the amount of aircraft emissions on high altitudes is very important for climatologists in order to understand eventual changes in the Earth atmosphere due to aviation activities. The authors would like to draw attention of the aviation professionals to the fact that aircraft fuel consumption during cruise; thereby amount of toxic content in the exhaust from the turbine engine is significantly higher especially during flights against jet stream. Thousands flights of two operators were processed using algorithms developed by authors. The article gives an example of fuel consumption and thereby CO2, CO and NOx emission estimation based on engine performance taken from their test cell results. Calculations were performed with the consideration of the factor for engines deterioration through operation time provided by its manufacturer.
Źródło:
Journal of KONES; 2015, 22, 2; 63-70
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Analysis of turbofan engine design modification to add inter-turbine combustor
Autorzy:
Jakubowski, R.
Powiązania:
https://bibliotekanauki.pl/articles/244764.pdf
Data publikacji:
2015
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
jet engine
turbofan engine
turbofan engine design
airplane engine development
inter turbine combustor turbofan
Opis:
An inter turbine combustion is one of modern direction of turbofan engine cycle modification. It is possible to reduce gas temperature in high-pressure turbine inlet section and reduce NOX emission by an additional combustor placed between high and low pressure turbines. The analysis of engine cycle modification and its performance are a scope of many scientific investigations, but it is not any work about engine dimension change due to cycle modification. By these way problems of two combustor engine components and dimensions, change with comparison to conventional turbofan engine is a goal of this work. The structure of a turbofan engine with inter turbine combustor is shown and results of evaluation temperature and pressure in specified engine cut sections are presented and discussed. Then the gas density is calculated and by mass continuity equation application, the specified cross section areas are determined. The results of two-combustor turbofan engine are compared with conventional high bypass turbofan engine. The comparison of engines parameters allow to predict how engine components should be modified in two-combustor turbofan when the base of modification is classic turbofan engine. The analyse contain determination of compressor and turbine stage numbers, prediction of areas of cross section and diameters in specified engine sections and overall engine axial dimensions. The results are used to formulate conclusion about the turbofan engine structure modification by additional combustor implementation between turbines.
Źródło:
Journal of KONES; 2015, 22, 3; 75-82
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Low temperature properties of fuel mixtures of kerosene and fame type used to supply turbine engines in marine and other non-aeronautical applications
Autorzy:
Dzięgielewski, W.
Gawron, B.
Kulczycki, A.
Powiązania:
https://bibliotekanauki.pl/articles/260024.pdf
Data publikacji:
2015
Wydawca:
Politechnika Gdańska. Wydział Inżynierii Mechanicznej i Okrętownictwa
Tematy:
jet fuel
biocomponents
marine turbine engine
low temperature properties
Opis:
A worldwide trend to popularise gradually increasing use of biofuels in various applications was a motivation for gaining interest in FAME as a commonly available biocomponent to fuels combusted in turbine engines. These engines are mainly used in aeronautics, but many of them are also used in other, non-aeronautical areas, including marine navigation. Specific conditions in which fuels are combusted in turbine engines used in these applications are the reason why fuel mixtures of kerosene and FAME type should reveal relevant low temperature characteristics. The article presents results of tests of low temperature properties of mixtures of the jet fuel Jet A-1 and methyl esters of higher fatty acids (FAME). The prepared mixtures contained different contents of FAME. The obtained results present changes of: viscosity, cloud point, pour point, crystallising point, and cold filter plugging point, depending on the percentage by volume of FAME. They also prove that the course of changes of low temperature properties of these mixtures is affected by chemical structure of the biocomponent.
Źródło:
Polish Maritime Research; 2015, 2; 101-105
1233-2585
Pojawia się w:
Polish Maritime Research
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
Numerical analysis of the intake vortex formation in the case of a double fuselage shielded inlet
Autorzy:
Kozakiewicz, A.
Frant, M.
Powiązania:
https://bibliotekanauki.pl/articles/281631.pdf
Data publikacji:
2014
Wydawca:
Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:
turbine jet engine
inlet intake vortex
computational fluid Dynamics
Opis:
The paper raises a very important problem, concerning the work of turbine-jet engines, that is the intake vortex. A phenomenon which is relevant to all engines of this type. The article demonstrates literature data determining the influence of the airflow direction and zone on the possibility of vortex formation, taking into consideration the influence of basic geometrical data. The outcomes of calculations related to the formation of the inlet vortex for a given fuselage shielded inlet constructional system are shown. The studies are concerned with determination of the influence of angles and the gust speed value on forming of the vortex in this kind of intake.
Źródło:
Journal of Theoretical and Applied Mechanics; 2014, 52, 3; 757-766
1429-2955
Pojawia się w:
Journal of Theoretical and Applied Mechanics
Dostawca treści:
Biblioteka Nauki
Artykuł
Tytuł:
On the need to maintain homogenous temperature field within the working agent at the intake of a jet engine turbine
Autorzy:
Pawlak, W. I.
Błachnio, J.
Powiązania:
https://bibliotekanauki.pl/articles/245331.pdf
Data publikacji:
2014
Wydawca:
Instytut Techniczny Wojsk Lotniczych
Tematy:
turbine jet engine
simulation model
working agent temperature field
Opis:
The paper presents results from numerical experiments with use of the computer model of the SO-3 engine designed for simulations. The model has been purposefully modified to take account of the assumed nonhomogeneity of the temperature field within the working agent at the turbine intake. It turned out that such nonhomogeneity substantially affects dynamic and static properties of the engine are considered as an object of control since it leads to a lag of the acceleration time and to increasing in fuel consumption. The summarized simulation results demonstrate that the foregoing properties of a jet engine are subject to considerable deterioration in pace with gradual increase of the assumed non-homogeneity of the temperature field, The simulations made it possible to find out that variations of the temperature field non-homogeneity within the working agent at the turbine intake lead to huge fluctuation of the turbine rpm for the idle run, which enables a new look to the role of the so-called idle run valve and importance of that component within the supply and control system of the SO-3 engine.
Źródło:
Journal of KONES; 2014, 21, 1; 205-213
1231-4005
2354-0133
Pojawia się w:
Journal of KONES
Dostawca treści:
Biblioteka Nauki
Artykuł

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