Temat: turbine jet engine - Katalog OPAC zbiorów

Skocz do pozycji: 1.

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: 2.

Tytuł:: Turbinowe silniki odrzutowe jedno- i dwuprzepływowe w samolotach bojowych
Jet turbine engine and by-pass turbojet in combat aircrafts
Autorzy:: Kozakiewicz, A.
Powiązania:: https://bibliotekanauki.pl/articles/209996.pdf
Data publikacji:: 2010
Wydawca:: Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
Tematy:: turbinowe silniki odrzutowe jednoprzepływowe
dwuprzepływowe turbinowe silniki odrzutowe
parametry jednostkowe
parametry strumienia
jet turbine engine
by-pass turbojet
parameters of individual turbine-jet engines
parameters gas stream
Opis:: Artykuł przedstawia analizę parametrów jednostkowych turbinowych silników odrzutowych pod względem procesu realizowanego w tych silnikach. Zaprezentowano tendencje zmian ciągu jednostkowego i jednostkowego zużycia paliwa w zależności od roku wprowadzenia silnika do eksploatacji oraz schematy ideowe silników. Przeanalizowano przebiegi zmian obliczonych parametrów gazodynamicznych wzdłuż kanałów przepływowych turbinowych silników odrzutowych użytkowanych w lotnictwie wojskowym RP na samolotach bojowych oraz wpływ zakresu lotu na ich przebieg i zakres wartości.
This paper presents analysis of parameters of individual turbine-jet engines in respect of the process realized in these engines. There are introduced the tendencies of changes of the specific thrust and the specific fuel consumption depending on the year of the introduction of the engine to the exploitation and schematic diagrams of engines. The courses of changes of calculated parameters along tubes of flow turbine-jet engines used in combat aircrafts are analysed and the influence of the range of the flight on their course and the range of value.
Źródło:: Biuletyn Wojskowej Akademii Technicznej; 2010, 59, 3; 201-217
1234-5865
Pojawia się w:: Biuletyn Wojskowej Akademii Technicznej
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

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: 4.

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: 5.

Tytuł:: Noise emission level versus the structure of the aircraft turbine engine
Autorzy:: Kowalski, M.
Powiązania:: https://bibliotekanauki.pl/articles/241859.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: noise of aircraft engines
environmental impact of a jet engine turbine
Opis:: This article presents the problem of noise generated by turbine jet engines. 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 essay ends with short conclusions. In order to struggle with the air noise special "Environmental Protection Programmes" are prepared. Civil airports and military airports prepare new procedures for taking off and approaching planes as well as optimize the approach and take off airport flight zone corridors. Unfortunately, in the case of so big surfaces, acoustic screens would not bring desired effects, also due to costs.
Źródło:: Journal of KONES; 2012, 19, 4; 325-332
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Premises of Parametrical Assessment of Turbojet Engine in Flight Regulation Condition During Ground Test
Autorzy:: Lindstedt, P.
Golak, K.
Powiązania:: https://bibliotekanauki.pl/articles/387321.pdf
Data publikacji:: 2012
Wydawca:: Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
Tematy:: regulacja
symulacja komputerowa
silnik odrzutowy
diagnostyka
test
regulation
computer simulation
turbine jet engine
parametric diagnostics
ground tests
Opis:: The article presents the theoretical bases of method, engine technical condition is described by one (in other methods four are used) comprehensive model (binding engine input signals p2 and mp and engine output - n and p4 signals) with unique feature, that engine operation quality during ground tests will provide neccessary data on its performance in flight. The changes occurring in turbojet engine during its exploitation will be measure by comparision of standard model with parameters obtained from experiment (ground test).
Źródło:: Acta Mechanica et Automatica; 2012, 6, 1; 44-48
1898-4088
2300-5319
Pojawia się w:: Acta Mechanica et Automatica
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 7.

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: 8.

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

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Skocz do pozycji: 9.

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

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Skocz do pozycji: 10.

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: 11.

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: 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:: 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: 14.

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

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Skocz do pozycji: 15.

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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