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    Wyświetlanie 1-6 z 6
    Tytuł:
    The influence of multi - role aircraft mission type on the low bypass engine performance parameters
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/242065.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    gas turbine engine design
    airplane-engine integration
    aircraft mission optimization
    Opis:
    The aim of the article is to find the relationship and dependencies between the mission parameters of the multi-role aircraft (altitude, flight velocity, thrust load) and the parameters that define the flow of the turbofan engine. The conclusions of these studies are relevant at the stage of preliminary engine design. There was built the model of thermal cycle of low bypass. The model of an airplane was simplified to its aerodynamic characteristics. The mission was divided into air tasks (stages) such as a take-off, a climb at a certain velocity, sub and supersonic flight and maneuvers (i.e. turn). Dimensionless energy criteria binding both the engine and aircraft parameters were introduced. There were conducted the simulation studies of the model airplane-engine mission to show the part of the mission that "dimensions " the engine. The results were limited to the presentation of the impact of circuit parameters such as T3, π, μ on the defined criteria. The calculations were carried out for a number of selected missions defined in the literature as Loll, HiLoHi and HiHiHi. The comparison of the energy requirements of these missions was done. There were pointed out these criteria of the mission evaluation that may affect making decisions at early design stages. There were designated the areas of design variability in an engine meeting the criteria for energy mission. The advantage of this model is universal character of dimensionless criteria, whereas the disadvantage is the need to build complex models of the engine and the assumption at the outset aerodynamic characteristics of the aircraft. The originality of the presented solution is to show an alternative, unconventional approach to the design process (not as so far) the engine itself but the entire aviation system.
    Źródło:
    Journal of KONES; 2013, 20, 3; 435-442
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Influence of the gas turbine engine design parameters on the energy consumption of the multirole aircraft missions
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/246706.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    gas turbine engine design
    simulation
    airplane-engine integration
    aircraft mission optimization
    Opis:
    In the article the analysis of the influence of design parameters of the engine on the performed by the multirole aircraft mission was performed. The problem is complex as a result of performing a series of manoeuvres in various conditions of flight. A special feature of multi-role aircraft mission is a sudden (even pulse) weight change and exactly its reduction as a result of the discharge of cargo bomb, rocket or due to the consumption of ammunition during air combat manoeuvring. Reducing the airplane mass by the weight of the fuel consumed (continuously) and the used weapons radically differ the demands on the energy required to overcome gravity and drag forces. The article shows how the reduction of the aircraft mass influences on the change of the thrust load factor. It was built the mathematical model of the system engine-aircraft-air job (taking into account the flight conditions, elements of the mission - subsonic and supersonic flight, flight time, the heat-and-gasdynamic and mass model of the engine). The model enables for the simulation research of the complex flight missions and their evaluation on the basis of the constructed criteria. The model includes a parametric description of physical processes in the turbofan engine, thus provides a direct assessment of the impact of selection of engine parameters on the effectiveness of the mission. The results of calculations according to classical criteria (e.g. kilometre fuel consumption, specific fuel consumption) were presented. The paper presents new criteria, which enable to analyze the energy consumption of the complex mission of the aircraft (e.g. energy consumption: the unit range, the degree of utilization of energy resources and the carried out the mission engine). Criteria were built in by combining the parameters necessary for the flight with disposable ones. On the basis of these parameters there was done an assessment of the "quantitative" adjustment of a power unit to various missions such as subsonic, supersonic and mixed (for different their proportion), for different levels and the plane range. The results were presented in a pictorial way on numerous charts.
    Źródło:
    Journal of KONES; 2012, 19, 2; 569-576
    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:
    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:
    Wyznaczenie charakterystyki współpracy okrętowego turbinowego silnika spalinowego z odbiornikiem energii z wykorzystaniem techniki planowania eksperymentu
    Determining co-operation characteristics of marine gas turbine engine with power receiver using methodology planning experiment
    Autorzy:
    Pojawa, B.
    Borsuk, K.
    Powiązania:
    https://bibliotekanauki.pl/articles/222044.pdf
    Data publikacji:
    2012
    Wydawca:
    Akademia Marynarki Wojennej. Wydział Dowodzenia i Operacji Morskich
    Tematy:
    charakterystyki okrętowych turbinowych silników spalinowych
    planowanie doświadczeń
    plan eksperymentu
    okrętowy turbinowy silnik spalinowy
    characteristics of marine gas turbine engine
    design of experiments
    experiment design
    marine gas turbine engine
    Opis:
    Proces eksploatacji okrętowych turbinowych silników spalinowych opiera się na ich charakterystykach, w tym na charakterystyce współpracy silnika z odbiornikiem energii, szczególnie jeżeli odbiornikiem energii jest śruba o skoku nastawnym. Dokumentacja okrętowa często nie zawiera tego rodzaju charakterystyk. Istnieje zatem potrzeba opracowania metody jej wyznaczania. Podejmując się próby wyznaczenia charakterystyki współpracy wybranego turbinowego silnika spalinowego z odbiornikiem energii, postanowiono dokonać tego w sposób analityczny, z wykorzystaniem techniki planowania eksperymentu. Mając na uwadze wstępny charakter badań, postanowiono je wykonać na stanowisku laboratoryjnym z turbinowym silnikiem spalinowym GTD-350 współpracującym z hamulcem wodnym Froude’a. W artykule przedstawiono podstawy teoretyczne planowania doświadczeń, sposób realizacji badań wstępnych oraz ich wyniki. Dla otrzymanych wyników badań przeprowadzono badanie adekwatności, w tym analizę statystyczną i merytoryczną. Na podstawie otrzymanych wyników badań adekwatności sformułowano wnioski.
    The process of operation of Marine turbine engines is based on their characteristics, including the characteristic of engine co-operation with the power receiver, especially if the receiver is a controllable pitch propeller. Ship documentation often does not cover this kind of characteristics. Therefore there is a need to work a method to determine it. Making an attempt to determine the co-operation characteristic of an engine with a power receiver it was decided to do it in an analytical way using experiment planning methodology. Bearing In mind the preliminary nature of the investigations it was decided to conduct them on a laboratory stand with a GTD-350 diesel engine co-operating with Froude water brake. The paper presents theoretical foundations for planning experiments, the way of conducting preliminary investigations and their results. The results obtained were checked for their adequacy, which included statistical and subject-matter analysis.
    Źródło:
    Zeszyty Naukowe Akademii Marynarki Wojennej; 2012, R. 53 nr 2 (189), 2 (189); 103-122
    0860-889X
    Pojawia się w:
    Zeszyty Naukowe Akademii Marynarki Wojennej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Development of Turboshaft Engine Adaptive Dynamic Model: Analysis of Estimation Errors
    Autorzy:
    Yepifanov, Sergiy
    Bondarenko, Oleksiy
    Powiązania:
    https://bibliotekanauki.pl/articles/36807197.pdf
    Data publikacji:
    2022
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    turbine engine
    turboshaft
    gas generator
    dynamic model
    engine time constant
    identification
    estimation error
    design of experiment
    Opis:
    One of the most perspective directions of aircraft engine development is related to implementing adaptive automatic electronic control systems (ACS). The significant elements of these systems are algorithms of matching of mathematical models to actual performances of the engine. These adaptive models are used directly in control algorithms and are a combination of static and dynamic sub-models. This work considers the dynamic sub-models formation using the Least Square method (LSM) on a base of the engine parameters that are measured in-flight. While implementing this function in the (ACS), the problem of checking the sufficiency of the used information for ensuring the required precision of the model arises. We must do this checking a priori (to determine a set of operation modes, the shape of the engine test impact and volume of recorded information) and a posteriori. Equations of the engine models are considered. Relations are derived that determine the precision of parameters of these models’ estimation depending on the precision of measurement, the composition of the engine power ratings, and durability of observations, at a stepwise change of fuel flow. We present these relations in non-dimensional coordinates that make them universal and ready for application to any turboshaft engine.
    Źródło:
    Transactions on Aerospace Research; 2022, 4 (269); 59-71
    0509-6669
    2545-2835
    Pojawia się w:
    Transactions on Aerospace Research
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-6 z 6

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