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    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:
    The influence of the ignition control on the performance of an aircraft radial piston engine
    Autorzy:
    Czarnigowski, Jacek
    Jakliński, Piotr
    Powiązania:
    https://bibliotekanauki.pl/articles/132922.pdf
    Data publikacji:
    2019
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    aircraft engine
    ignition system
    power
    toxic emission
    silnik lotniczy
    układ zapłonowy
    moc
    emisja związków toksycznych
    Opis:
    Aircraft piston engines are built with compromise on performance and safety. The desire to achieve the highest power-to-weight ratio leads to the search for solutions that optimize the combustion process. On the other hand, the need for maximum reliability leads to the simplification of the design at the costs of performance. An example of such a compromise is the ignition system of the ASz-62IR engine. In this engine there is a double magneto ignition system with a fixed ignition advance angle. As part of the modernisation of this engine, an electronically controlled dual ignition system was developed, which allows for optimum control of the ignition advance angle in terms of power. This article discusses the results of bench tests of the ASZ-62IR-16X engine with fixed ignition timing and variable timing control. Functional parameters and toxicity of exhaust gases were analyzed.
    Źródło:
    Combustion Engines; 2019, 58, 2; 60-65
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Overview of low emission combustors of aircraft turbine drive units
    Autorzy:
    Fąfara, Jean-Marc
    Powiązania:
    https://bibliotekanauki.pl/articles/2097476.pdf
    Data publikacji:
    2020
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    aircraft
    engine
    low emission
    combustor
    design
    samolot
    silnik
    niska emisja
    komory spalania
    projekt
    Opis:
    It is important to notice that aircraft turbine drive units are commonly used in the modern aviation. The piston engines are often reserved for small and/or sportive aircraft. The turbine drive units are also combustion engine. This paper presents the most popular combustors used in the aeronautical turbine engines. Firstly there are listed the requirements that a combustor has to achieve. Then are presented the combustor designs that permit to achieve the firstly presented requirements. In this work are presented the LPP, TAPS, RQL, graduated combustion zone, VGC, exhaust recirculation system combustors. For each combustor design is enlighten its principle of work, described the etymology of the given name to this design and shown a scheme. The work is closed by a briefly conclusion about the described combustor.
    Źródło:
    Combustion Engines; 2020, 59, 4; 45--49
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of the ecological effectiveness of passenger transport by jets of various sizes
    Autorzy:
    Kardach, Monika
    Galant, Marta
    Fuć, Paweł
    Powiązania:
    https://bibliotekanauki.pl/articles/133210.pdf
    Data publikacji:
    2019
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    LTO cycle
    jet aircraft
    air transport emission
    cykl LTO
    samolot odrzutowy
    emisja z transportu lotniczego
    Opis:
    The article’s aim was to compare an ecological effectiveness of a common jetliner with 189 passenger capacity flying on two CFM engines and a very light jet business aircraft designed to carry up to 8 people on board. The carried-out analysis showed that the NOx emission per passenger in Very Light Jet (VLJ) is three times higher than in common jet airliner, furthermore there is 15 times difference in CO emission. Based on the results of the analysis, it can be stated that it is appropriate to extend the certification of engines to smaller units, as well as to adjust the LTO test beyond laboratory conditions.
    Źródło:
    Combustion Engines; 2019, 58, 3; 252-256
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Minimum emission unconventional MAGLEV assisted take-off
    Autorzy:
    Majka, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/246124.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    air transport
    green trajectory
    take-off
    aircraft emission
    magnetic levitation
    Opis:
    Among the most important problems faced by the air transport today there can be mentioned some negative influences of aircraft and airports on the environment and the increasing costs of air transport. One of the possibilities to improve the situation is to work out innovative solutions aimed at decreasing of the aircraft pollution and improving the transport effectiveness. Among the most innovative ideas is the use of magnetic levitation (MAGLEV) to aid the take-off and landing of the transport aircraft. The “Integrated Ground and on-Board system for Support of the Aircraft Safe Take-off and Landing” – GABRIEL, deals with radically new integration of the MAGLEV technology into the air transportation system that contains aircraft, airport, air traffic control, authority, logistic and operational support, maintenance, etc. GABRIEL idea includes operation of the aircraft without the conventional undercarriage system and using the ground based power and supporting systems for take-offs and landings. In case of using the GABRIEL system as a catapult, the aircraft on the track must be accelerated to the speed permitting to reach the altitude of 300 m or more. Such take-off and climb results in minimum noise and minimal emission of substances harmful for the environment. After reaching the altitude of 300 m, the aircraft may follow its flight with using different flight strategies. Different conditions of the unconventional take-off needs to shape other way the trajectory of the initial stage of the aircraft flight after the lift-off. The aim of the present work was to determine the optimal conditions of the lift-off and the optimal trajectory of the initial climb minimizing the emission. Simplified realization of the Ritz- Galerkin method was used in this work, which uses an approximate solution to boundary value problems for determining the optimal flight trajectory.
    Źródło:
    Journal of KONES; 2014, 21, 4; 335-342
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of the performance of an aircraft powered by hybrid propulsion
    Autorzy:
    Majka, Andrzej
    Muszyńska-Pałys, Jagoda
    Powiązania:
    https://bibliotekanauki.pl/articles/24202466.pdf
    Data publikacji:
    2023
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    air transport
    hybrid power unit
    electric aircraft
    Small Air Transport
    SAT
    aircraft emission
    transport lotniczy
    jednostka napędu hybrydowego
    samolot elektryczny
    emisja lotnicza
    Opis:
    Travel is an inseparable part of human life. It is connected not only with private life but also with business life. People want to travel more, farther and faster. That is why air transport is currently one of the fastest-growing areas of passenger transport, and airlines carry more and more passengers from year to year. Due to the growing negative impact of air transport on the natural environment, research aimed at the development of technologies to reduce the negative impact of air transport is becoming more and more important. One of the possibilities for improving the situation is the use of alternative energy sources, limiting the emission of greenhouse gases into the atmosphere. The paper aimed to analyze the meaningfulness of replacing the classic power unit in a light transport aircraft with a hybrid, combustion-electric power unit. Analyzes were made with the use of simulation methods for the PZL M-28 aircraft.
    Źródło:
    Combustion Engines; 2023, 62, 2; 45--51
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analiza porównawcza testów emisji związków szkodliwych spalin silnika turbinowego
    Comparative analysis of exhaust emission tests for a turbine engine
    Autorzy:
    Merkisz, J.
    Markowski, J.
    Ślusarz, G.
    Galant, M.
    Karpiński, D.
    Wirkowski, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/133551.pdf
    Data publikacji:
    2015
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    emisja
    samolot wielozadaniowy
    test LTO
    emission
    multipurpose aircraft
    LTO test
    Opis:
    Lotnicze silniki turbinowe o sile ciągu większej od 27,6 kN podlegają normom emisji związków szkodliwych spalin zgodnie z Aneksem 16 Konwencji Chicagowskiej ustalonymi przez ICAO. Normy emisji silników odrzutowych określone są wg przyjętego jako wzorcowy - cyklu startu i lądowania LTO (ang. Landing and take-off cycle). Normy te stosuje się również dla silników wykorzystywanych w wojskowych samolotach wielozadaniowych. Jednak eksploatacja samolotów wielozadaniowych różni się od eksploatacji cywilnych statków powietrznych. W związku z tym przeprowadzono analizę wyników emisji zanieczyszczeń uzyskanych w przeprowadzonych testach badawczych z wartościami emisji wynikających z wytycznych zawartych w normach.
    Aviation gas turbines with thrust greater than 27.6 kN are subject to exhaust emission norms and regulations for harmful compounds outlined in Annex 16 of the Chicago Convention as established by ICAO. Jet engine emission standards are defined with the use of an established takeoff and landing model known as the LTO cycle (Landing and take-off). These standards also apply to engines used in multi-role combat aircraft. However, multi-role combat aircraft operation differs from the operation of civilian aircraft. Therefore, the analysis of the emission results obtained in the carried out research was done with the use of emission values contained in the norm guidelines.
    Źródło:
    Combustion Engines; 2015, 54, 3; 449-455
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Wyznaczanie emisji związków toksycznych w spalinach turbiny gazowej do zastosowań morskich w oparciu o charakterystyki emisji turbinowego silnika lotniczego
    Determination of toxic exhaust emissions of a gas turbine for seagoing vessels based on a jet engine emission characteristic
    Autorzy:
    Pawlak, M.
    Kuźniar, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/316453.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Naukowo-Wydawniczy "SPATIUM"
    Tematy:
    turbina gazowa
    silniki okrętowe
    turbinowe silniki lotnicze
    współczynnik emisji
    porównanie silników
    gas turbine
    marine engines
    turbine aircraft engine
    emission factor
    engine comparison
    Opis:
    W artykule opisano metodykę wyznaczenia emisji wybranych szkodliwych związków do atmosfery przez turbinę gazową napędzającą morską jednostkę pływającą. Opisano konstrukcję takiego silnika, porównano go do spokrewnionego z nim silnika odrzutowego. Powiązano parametry obiegu silników używając do tego formuł gazodynamicznych, a na tej podstawie dobrano współczynniki emisji NOx, CO, HC. Wyniki zebrano w tabelach i przedstawiono na wykresach. Rezultaty analizy zostały omówione i są podstawą do dalszych, bardziej szczegółowych symulacji i analiz.
    The paper describes the methodology for determining the emission into the atmosphere of selected harmful compounds generated by a gas turbine that drives a seagoing vessel. The design of such an engine was described and compared to its related jet engine. The engine parameters were adjusted using gasodynamic formulas and the NOx, CO, HC emission coefficients were adjusted accordingly. The results are summarized in tables and graphed. The results of the analysis are discussed and are the basis for further, more detailed simulations and analyzes.
    Źródło:
    Autobusy : technika, eksploatacja, systemy transportowe; 2017, 18, 12; 345-350, CD
    1509-5878
    2450-7725
    Pojawia się w:
    Autobusy : technika, eksploatacja, systemy transportowe
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of the impact of changes in flight speed and altitude on emission indexes of pollutants in jet engine exhausts
    Autorzy:
    Pawlak, Małgorzata
    Kuźniar, Michał
    Powiązania:
    https://bibliotekanauki.pl/articles/244064.pdf
    Data publikacji:
    2019
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aircraft
    exhausts emission
    bypass engine
    emission index
    Opis:
    In currently implemented international aviation strategies and programs, including those realised under the European Union policy, such as Clean Sky, SES, SESAR and, CORSIA, the environmental aspect is particularly prominent – reducing the emission of all gaseous pollutants, and from 2020 also particulate matter. Therefore, it is important to know how the change in flight parameters (altitude, speed) affects the emission of pollutants in jet engine exhausts. Such information will enable to adjust the flight altitude of the aircraft when ecological aspect is taken into consideration. In addition to the operating condition (altitude, flight speed, range of power or thrust), the amount and type of pollutants emitted depends on the type of aircraft, its aerodynamic characteristics, engine type and as well as on the type of fuel used. The impact of changes in aircraft flight parameters (speed and altitude) on the performance of a bypass jet engine and the emission of pollutants in its exhausts is analysed in the paper. For this purpose, the speed-altitude characteristics of such an engine were determined. Next, the emission indexes (EI) for the LTO phase taken from the ICAO database were used to determine the emission indexes corresponding to given parameters of both the engine operation and the aircraft flight. For selected speeds and cruising altitudes, the value of thrust required for the flight of the aircraft was determined and to this value, the engine operation range was assigned as well the corresponding pollutant emission indexes. This allowed to calculate the mass of pollutants emitted per unit of time for given flight parameters. The results obtained are presented in the graphs and discussed.
    Źródło:
    Journal of KONES; 2019, 26, 2; 107-113
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Planning the flight trajectory of a passenger aircraft with regards to the aspect of pollutants emission
    Autorzy:
    Pawlak, Małgorzata
    Powiązania:
    https://bibliotekanauki.pl/articles/243971.pdf
    Data publikacji:
    2019
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aircraft
    emission
    cruise phase
    flight trajectory
    Opis:
    One of the ways to reduce the adverse impact of aircraft on the environment is through the determination of the trajectory of the flight on a given route that leads to reducing fuel consumption and, consequently, emission of pollutants in jet engines exhausts. Planning a flight in terms of minimizing emissions or fuel consumption is a complex task and difficult to implement due to the conditions in which the aircraft travels, but it is possible though. It is necessary to take into account the limitations resulting from the organization of the airspace and the rules therein, as well as the current weather conditions. The weather is one of the main factors determining the amount of fuel consumed, the time and cost of a particular flight on a given route. In addition to the main parameters, such as pressure and air density, it is extremely important to determine the air temperature, as well as the wind speed and direction. The temperature affects the speed of sound, based on which it is possible to determine the Mach number for a plane flying with a given true air speed (TAS). The speed and direction of wind, on the other hand, affect the speed of the aircraft relative to the ground (velocity over ground, VOG), and thus the duration of its flight. The article describes how the developed model of emission of pollutants in the exhausts of jet bypass engines can be useful for determining the trajectory of an aircraft in its cruise phase due to the criterion of pollutants emissions minimization. An exemplary analysis was carried out for selected aircraft moving along the route adopted for the research. The analysis covered various cruising altitudes and various meteorological conditions (wind speed and direction). The obtained results are illustrated graphically and discussed.
    Źródło:
    Journal of KONES; 2019, 26, 3; 145-153
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-10 z 10

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