Temat: turbine jet engine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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

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Skocz do pozycji: 2.

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

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Skocz do pozycji: 3.

Tytuł:: Analiza porównawcza osiągów turbinowych silników odrzutowych samolotów bojowych obecnie użytkowanych w RP
Comparative analysis of turbojet performance of combat aircraft used in Polish Air Force
Autorzy:: Kozakiewicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/210410.pdf
Data publikacji:: 2009
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: turbinowe silniki odrzutowe
efektywność dopalacza
charakterystyka obrotowa silnika
jet turbine engine
effectiveness afterburner
rotated characteristic engine
Opis:: Artykuł przedstawia analizę osiągów zespołów napędowych samolotów wielozadaniowych, obejmuje ona między innymi współczynniki strat samolotów jedno i dwusilnikowych. Dokonano oceny silników eksploatowanych w Siłach Powietrznych RP na samolotach F-16C, MiG-29 i Su-22. Wykonano obliczenia charakterystyki obrotowej silnika RD-33 i uzyskano charakterystyki ciągu silnika, jednostkowego zużycia paliwa, temperatury przed turbiną i stopnia podziału masowego natężenia w funkcji prędkości obrotowej wirnika wysokiego ciśnienia. Przedstawiono również obliczoną charakterystykę prędkościowo-wysokościową, która jest istotna z punktu możliwości wykonywania zadań przez każdy samolot - w tym szczególnie samoloty wielozadaniowe.
This paper presents the analysis of performance of combat aircraft engines, including losses coefficients for single and double engines. Assessment of the engines used in the aircraft F-16C, MiG-29, and Su-22 engines in Polish Air Force has been made. Some rotated characteristic of RD-33 engine and characteristics of engine trust, specific fuel consumption, temperature before a turbine and a bypass ratio were calculated. Also the calculated speed-altitude characteristic, very important for each plane tasks and especially combat aircraft tasks, was presented.
Źródło:: Biuletyn Wojskowej Akademii Technicznej; 2009, 58, 2; 65-83
1234-5865
Pojawia się w:: Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

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

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Skocz do pozycji: 5.

Tytuł:: Analysis of the gust impact on inlet vortex formation of the fuselage-shielded inlet of an jet engine powered aircraft
Autorzy:: Kozakiewicz, A.
Frant, M.
Powiązania:: https://bibliotekanauki.pl/articles/279399.pdf
Data publikacji:: 2013
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: turbine jet engine inlet
intake vortex
numerical fluid dynamics
Opis:: Selected problems of a complex structure, namely the fuselage-shielded inlet model of a turbine jet engine for numerical analysis purposes of the intake vortex formation phenomenon are presented in this paper. As a result of numerical analysis, an intake vortex has been developed. The analysis of the impact of changes in speed, angle and the direction of gust on vortex development has been conducted. Also, consequences of ingestion of foreign objects by the inlet and relevant statistics concerning damage to turbine engines have been presented.
Źródło:: Journal of Theoretical and Applied Mechanics; 2013, 51, 4; 993-1002
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

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

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Skocz do pozycji: 7.

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

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Skocz do pozycji: 8.

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

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Skocz do pozycji: 9.

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

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Skocz do pozycji: 10.

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

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Skocz do pozycji: 11.

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

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Skocz do pozycji: 12.

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

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Skocz do pozycji: 13.

Tytuł:: Method of regulation condition assessment of turbine jet engine in flight basing on signals recorded during ground tests
Autorzy:: Golak, K.
Powiązania:: https://bibliotekanauki.pl/articles/246520.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: regulation
computer simulation
turbine jet engine
parametric diagnostics
ground tests
Opis:: During exploitation process operation quality differences may be observed between each particular machine and occurring in exploitation of one machine. These differences result from deviations of realized service process. Turbine jet engine regulation process was realized during ground tests. However, due to varying reactions of engines to external distortions, such as rocket launching, air swirl from another plane etc. as well as lack of possibility of simulation of in-flight conditions on ground (e.g. by partial choking of air intake), a situation may occur in which engine properly regulated on ground may not present sufficient efficiency in flight. Hence, the necessity to assess turbine jet engine regulation condition in flight basing on its ground tests. Research realized on computer models presenting engine operation both in flight and during ground tests indicated that real possibility of engine in flight regulation condition assessment based on its ground tests does exist. As was also noticed, with known input signal “w” and output signal “yW” recorded during engine ground tests as well as input “e” and output “u” signals from regulator during given test spectral powers and cross spectral powers of signals Swyw, Sww, See, Seu may be calculated and thus HW transfer function describing engine operation during ground test and GR transfer function describing regulator operation during given test and hence obtain transfer function HZ describing engine in flight. This grants possibility of regulation condition assessment of turbine jet engine in flight using signals recorded during ground tests.
Źródło:: Journal of KONES; 2012, 19, 3; 125-134
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 14.

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

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Skocz do pozycji: 15.

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

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