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    Wyświetlanie 1-7 z 7
    Tytuł:
    Empirical Tests of Stress in Gyroplane Rotor During Flight
    Autorzy:
    Czarnigowski, Jacek
    Powiązania:
    https://bibliotekanauki.pl/articles/102254.pdf
    Data publikacji:
    2020
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    gyroplane
    rotor blade
    hub bar
    stress
    łopata wirnika
    pręt piasty
    naprężenie
    Opis:
    The paper presents the results of experimental investigations of total tensile stresses in a gyroplane’s rotor during flight. The research aimed to determine which flight maneuvers induce the greatest stress in the rotor blade and the hub bar. The object of research was an ultralight gyroplane Tercel by Aviation Artur Trendak equipped with a rotor by the same manufacturer. Measurements were taken a) at the root of the rotor blade in the longitudinal direction, at the rotor blade’s lower surface in the point where the blade is attached to the hub bar, and b) in the hub bar, on its lower surface also in the longitudinal direction. To measure the stress, the author constructed an original measuring system based on the strain gauge bridge circuit mounted on the rotor head. The tests were carried out in a wide range of maneuvers within the gyroplane’s flight envelope. The highest value of tensile stress was found to occur while rapidly reducing the horizontal velocity in steep descent.
    Źródło:
    Advances in Science and Technology. Research Journal; 2020, 14, 3; 107-117
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Aircraft piston engine load distribution in steady state operating conditions
    Autorzy:
    Czarnigowski, Jacek
    Trendak, Michał
    Powiązania:
    https://bibliotekanauki.pl/articles/24202454.pdf
    Data publikacji:
    2023
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    piston engine
    engine parameters
    statistic
    normal operating conditions
    silnik tłokowy
    parametry pracy silnika
    statystyka
    normalne warunki pracy
    Opis:
    The article presents the results of statistical analysis of aircraft piston engine operational parameters during normal operating conditions. Test was carried out on ultralight gyroplane Tercel produced by Aviation Artur Trendak equipped with CA 912 ULT piston engine. Research was conducted under normal operating conditions of the autogyro and data was collected from 15 independent tests including a total of 14 flight hours conducted during training flights. Engine and flight parameters were recorded at 9 Hz during each flight using on-board Flight Data Recorded system. The data collected was subjected to statistical analysis to determine the statistical distribution of parameters defining the engine's operating condition. The analysis covered engine speed, intake manifold pressure, oil temperature, head temperature and exhaust gas temperature. The results were presented in the form of histograms showing the characteristic ranges of the parameters in aviation engine operation. An analysis of the rate of change of the analysed parameters was then carried out. This was the basis for defining the engine's steady state. The results showed that the steady state of the engine under these operating conditions accounted for more than 78% of the total engine operating time. A Power Consumption Ratio indicating the load range of the engine was determined for steady states. It was shown that most of the time the motor operates at an average load of between 50% and 80% of the nominal value.
    Źródło:
    Combustion Engines; 2023, 62, 2; 29--35
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    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:
    Influence of oil service life on selected performance parameters of an aircraft piston engine
    Autorzy:
    Trendak, Michał
    Czarnigowski, Jacek
    Powiązania:
    https://bibliotekanauki.pl/articles/24202468.pdf
    Data publikacji:
    2023
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    remaining useful life
    engine oil
    gyrocopter
    gyroplane
    exploitation monitoring
    pozostały okres użytkowania
    olej silnikowy
    żyrokopter
    wiatrakowiec
    monitoring eksploatacji
    Opis:
    This article presents an analysis of the influence of oil service life on the performance parameters of an air-craft piston engine lubrication system used in an ultralight aircraft. The ageing of oil between oil changes causes a change in its parameters (such as density, viscosity...). These parameters have a strong influence on the level of protection of the lubricated components. Currently, in aircraft, oil changes are carried out according to a time schedule - oil is changed every fixed period (residual life) regardless of its actual condition. The task of this article is to test the possibility of an indirect assessment of oil condition based on analysis of changes in selected parameters of engine lubrication system operation during normal operation. The oil warm-up speed during the pre-start procedure and the dependence of oil pressure on engine speed were assumed for the analysis. The study was conducted on an ultralight rotorcraft during normal operation. Selected first daily flights directly after oil change, and after 17, 32, 50 and 66 hours of operation were analysed. It was shown that the warm-up rate changes in the samples analyzed, but that this change may also be due to factors other than oil operating time. In the case of the oil pressure vs. speed characteristics, different characteristics were shown for different operating time, but no specific dependencies were found.
    Źródło:
    Combustion Engines; 2023, 62, 3; 78--83
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Investigations of the temperature distribution in the exhaust system of an aircraft piston engine
    Autorzy:
    Czarnigowski, Jacek
    Skiba, Krzysztof
    Dubieński, Kamil
    Powiązania:
    https://bibliotekanauki.pl/articles/134051.pdf
    Data publikacji:
    2019
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    aircraft engine
    exhaust system
    temperature distribution
    silnik lotniczy
    układ wydechowy
    rozkład temperatury
    Opis:
    Ultralight aviation is based on piston engines requiring both performance and reliability. An important aspect is also the requirements for the installation of such an engine on an airframe, especially its heat emission. This is firstly because of the need to ensure proper engine cooling and secondly because composite elements of the airframe skin are not exposed to excessive overheating. For this purpose, bench tests of the temperature distribution of the exhaust system of ROTAX 912 engine were carried out. Measurements were taken at 6 points of the exhaust system, where the temperature of the exhaust gases and exhaust pipes were measured. The tests covered a wide range of engine operation. The paper presents the temperature distribution at selected points in relation to the engine speed and load.
    Źródło:
    Combustion Engines; 2019, 58, 2; 12-18
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Analysis of operating parameters of the aircraft piston engine in real operating conditions
    Autorzy:
    Czarnigowski, Jacek
    Rękas, Daniel
    Ścisłowski, Karol
    Trendak, Michał
    Skiba, Krzysztof
    Powiązania:
    https://bibliotekanauki.pl/articles/2097612.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    piston engine
    engine parameters
    statistic
    normal operating conditions
    silnik tłokowy
    parametry silnika
    statystyka
    normalne warunki pracy
    Opis:
    The article presents the results of analysis of operational parameters of piston engine CA 912 ULT which is a propulsion system of ultralight gyroplane Tercel produced by Aviation Artur Trendak. Research was conducted under normal operating conditions of the autogyro and data was collected from 20 independent tests including a total of 28 flight hours, divided into training flights and competition flights. Engine speed, manifold air pressure and temperature, fuel pressure, injection time, and head temperature were recorded at 9 Hz during each flight. Collective results were presented to show the statistical analyses of the individual parameters by determining the mean values, standard deviations and histograms of the distribution of these parameters. Histograms of operating points defined by both engine speed and manifold air pressure were also determined. Analyses of the engine dynamics as a distribution of the rate of change of the engine rotational speed were also carried out. It was shown that the engine operating points are concentrated mainly in the range of idle and power above 50% of nominal power. The most frequent range is 70-80% of nominal power. It was also shown that the dynamics of engine work in real operating conditions is small. It was also shown that the way of use significantly influences the distribution of operating points. During training flights, an increase in the number of take-offs and landings causes an increase in the amount of engine work at take-off and nominal power and at idle.
    Źródło:
    Combustion Engines; 2021, 60, 4; 83--89
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Bench Tests for Exhaust Gas Temperature Distribution in an Aircraft Piston Engine with and without a Turbocharger
    Autorzy:
    Czarnigowski, Jacek Andrzej
    Skiba, Krzysztof
    Rękas, Daniel
    Ścisłowski, Karol
    Jakliński, Piotr
    Powiązania:
    https://bibliotekanauki.pl/articles/2123277.pdf
    Data publikacji:
    2021
    Wydawca:
    Stowarzyszenie Inżynierów i Techników Mechaników Polskich
    Tematy:
    temperature distribution
    piston engine
    exhaust system
    turbocharging
    Rotax 912
    Opis:
    In ultralight aviation, a very important engine parameter is the power-to-weight ratio. On the one hand, there is a tendency to minimize the size and weight of engines, and on the other hand, there is a demand to achieve the highest possible power by using supercharging systems. Increasing power brings many benefits, but it also increases temperature in the exhaust system, posing a threat to delicate parts of the ultralight aircraft fuselage. Therefore, it is necessary to control temperature values in the engine exhaust system. This article presents the temperature distribution in the exhaust system of an aircraft engine by the example of a four-cylinder Rotax 912 engine with an electronic fuel injection system. The research was conducted in two stages: measurements were made first for the engine without a turbocharger with an original exhaust system and later for its modified version with an added turbocharger system. The paper presents a comparative analysis of exhaust gas temperatures measured at three points: 30, 180 and 1000 mm from the cylinder head. The tests were conducted for the same preset engine operating conditions at constant speed and manifold air pressure. It has been shown that the exhaust temperature in the exhaust manifold decreases with the distance from the cylinder head. The highest gradient, over three times higher than the gas temperature from 589.9 °C to 192.3 °C, occurred in the manifold with a turbocharger for 2603 RPM and 31 kPa of manifold air pressure. The introduction of turbocharging causes an increase in exhaust gas temperatures before the turbocharger by an average of 12%, with this increase being greater for operating points of higher inlet manifold pressure. Turbocharging also causes a significant decrease in exhaust gas temperatures behind the turbocharger and the silencer because the temperature drops there by an average of 25%.
    Źródło:
    Advances in Science and Technology. Research Journal; 2021, 15, 3; 155--166
    2299-8624
    Pojawia się w:
    Advances in Science and Technology. Research Journal
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-7 z 7

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