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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:
    The influence of on-design bypass turbine engine parameters on multipurpose aircraft missions energy-consuming
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/243880.pdf
    Data publikacji:
    2010
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    military gas turbine engine
    military aircraft mission analysis
    multipurpose aircraft
    energy consuming
    Opis:
    In the article there was presented a quality assessment of parameters selection of bypass turbine engine for a multipurpose aircraft. It was assumed that the assessment criterion results from the energy-consumption of a flight. The criteria of energy-consumption range were defined as the relation of sum ofenergy supplied to the aircraft on the driven stages to the distance during a mission. The second criterion of unitary energy-consumption is defined as the relation of the movement energy-consumption to the product of the aircraft mass and the route during the elementary stage of the flight. With the use of the already worked out models of the power unit (bypass turbine engine with jet mixer and afterburner) of an aircraft (already known mass and aerodynamic characteristics) there were determined the ranges of thrust which are indispensable for a flight and available for the engine at each stage of the mission: take off, climb, subsonic and supersonic flight and turn with different overload factor. On the example of three chosen aircraft missions (Lo-Lo-Lo, Hi-Lo-Hi and Hi-Hi-Hi) the models of mission energy-consumption were developed. For the accepted change ranges of the comparative cycle parameters of the turbine engine the run of energy-consumption was tested. It was stated that for the assumed data the most energy-consuming mission is Lo-Lo-Lo, wherefore the increase of the compression and the rate of bypass reduces the energy-consumption of the mission.
    Źródło:
    Journal of KONES; 2010, 17, 1; 499-506
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Thermodynamics and mass selection criterions of low bypass turbine engine parameters for multi-purpose
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/244019.pdf
    Data publikacji:
    2008
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    multi-purpose aircraft
    turbine engines
    airframe and engine integration
    thermal cycle
    Opis:
    Parameters of the turbofan engine comparative cycle (turbine inlet temperature, compression of compressors), by-pass ratio, fan compressor, (or low pressure compressor) are the most important engine parameters which determine their characteristics and construction. In order to fulfill the task there is a necessity for searching the optimum parameters for the system. The most important equation that binds airplane and engine characteristics is mass balance equation. The sum of engine mass and fuel mass was called total engine-fuel mass. In the paper specific total engine mass index was introduced (gamma 2). This index is equal to total engine-fuel mass divided by thrust in design point. Impact of the choice of the design point on the total mass index of the engine and the fuel used up was presented for different airplane mission. The next problem is to find those thermodynamics parameters (compression ratio, turbine inlet total temperature, bypass ratio) which give minimum of total mass of engine and consumed fuel for different airplane missions. A very important parameter that plays the part in fuel consumption is airplane flight time. The most important conclusion is that the best thermodynamics parameters from minimum mass criterion are less than for minimum specific fuel consumption.
    Parametry obiegu porównawczego dwuprzeplywowego turbinowego silnika odrzutowego determinują jego charakterystyki i schemat konstrukcyjny. W pracy przedstawiono problem poszukiwania optymalnych wartości parametrów termogazodynamicznych obiegu porównawczego silnika turbinowego. Do tych parametrów zaliczono: spręż całkowity sprężarki, temperaturę przed turbiną, stopień podziału strumieni. Przedstawiono wpływ wybranych warunków lotu, sprężu sprężarki i temperatury przed turbiną na zmianę ciągu jednostkowego i jednostkowego zużycia paliwa. Jako kryterium optymalizacji wybrano sumaryczną masę silnika i paliwa, wymaganą do wykonania zadania lotniczego. Wykorzystano, zbudowany na potrzeby innych prac, model silnika, który jest funkcją parametrów termogazodynamicznych. Wyprowadzono zależności pozwalające na optymalizację jednostkowej masy sumarycznej (jako kryterium bezwymiarowego). Przeprowadzono szereg obliczeń, których wyniki przedstawiono na wykresach. Wykazano, że na podstawie wybranego kryterium optymalizacji, jakim jest sumaryczna masa silnika i paliwa, można wyznaczyć wartości sprężu sprężarki, dla których wskazane kryteria oceny masy osiągają swoje minimum.
    Źródło:
    Journal of KONES; 2008, 15, 2; 543-551
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Criteria for the assessment of the engine efficiency of the multi-purpose aircraft missions
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/245198.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    multi-purpose aircraft
    turbine engines
    airframe and engine integration
    thermal cycle
    Opis:
    The problem of design parameters selection of the turbine engine is the most important task at the preliminary design stage of the multi-purpose aircraft. A special feature of the multi-purpose aircraft mission is a sudden (even pulse) weight change, especially its decrease as a result of discharge of cargo bombing or rockets due to the ammunition consumption during air combat manoeuvring. In this article the attempt to use economic and mass criteria to assess the impact of the type of air missions on the choice of the design parameters of the engine was done. As the design, parameters there were selected the following measures: compression ratio, the turbine temperature and the bypass ratio. A mathematical model of the engine – aircraft – air task system was built (taking into account the flight conditions, the mission elements – the subsonic and supersonic flight, flight time, thermo-gas-dynamic and mass model of the engine). The model enables to conduct the simulation research of the complex flight missions and their assessment on the basis of the constructed criteria. The model includes a parametric description of physical processes in the turbofan engine, thereby allowing a direct assessment of the impact of the selection of engine parameters on the effectiveness of the mission. The paper presents the results of calculations according to the classical criteria (e.g. kilometre fuel consumption, specific fuel consumption of the engine). New criteria for evaluation were presented; they are the energy efficiency of complex mission of an aircraft and the relative total and specific fuel consumption. The values of circuit parameters that need to be taken as design constraints for the engine to allow the implementation of the aviation missions were determined. The results are shown in an illustrative way on the number of graphs.
    Źródło:
    Journal of KONES; 2014, 21, 3; 301-307
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Criteria of aircraft engine parameters evaluation for multi-purpose aircraft
    Kryteria oceny parametrów silnika turbinowego stanowiącego napęd samolotu wielozadaniowego
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/243118.pdf
    Data publikacji:
    2007
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    samolot wielozadaniowy
    silniki turbinowe
    integracja samolotu i silnika
    multi-purpose aircraft
    turbine engines
    airframe and engine integration
    Opis:
    At the stage of a power unit selection for a multi-purpose aircraft the problem of mutual relations between the dimension of an aircraft and an engine should be solved. Starting from the motion equation of an aircraft and the theory of similarity the criteria and performance were determined which connect in a geometrical and power way the engine and the aircraft. The analysis of the influence of flight conditions and the parameters of an engine comparative cycle on the geometrical dimensions was conducted. In the paper it was shown that the fundamental flight stage which determines the relations between the geometrical parameters of the aircraft and the engine is the take-off or supersonic flight on the big altitude. Usually the parameters selection of the turbine engine thermal cycle is done on the basis of the internal characteristics of the engine, such as specific thrust and specific fuel usage. In case of the turbofan engine model with the mixer, afterburner, and the aircraft model (with simplified aerodynamic and mass characteristics) the influence of the cycle parameters on the performance and aerodynamic lift/drag ratio, the agreed range and the theoretical range was described. The next problem is to find those thermodynamics parameters (compression ratio, turbine inlet total temperature, bypass ratio) which give minimum of total mass of engine and consumed fuel for different airplane missions gamma Z. For long-lasting mission minimum gamma Z is occurs for compression ratio near his economic value (for specific fuel consumption). For short missions minimum of gamma Z occurs for smaller compression ratio (near 20-30), but greater than for those giving maximum specific thrust. A little change in minimum value of gamma Z gives a big difference in compression ratio. The most important conclusion is that the best thermodynamics parameters from minimum mass criterion are less than for minimum specific fuel consumption.
    Na etapie wyboru zespołu napędowego do samolotu wielozadaniowego należy rozwiązać problem wzajemnych relacji między wymiarami samolotu i silnika. Wychodząc z równań ruchu samolotu i teorii podobieństwa wyznaczono kryteria i wskaźniki wiążące geometrycznie i energetycznie silnik oraz samolot. Przeprowadzono analizę wpływu warunków lotu samolotu i parametrów obiegu porównawczego silnika na wybrane wymiary geometryczne. W pracy wykazano, że zasadniczym stanem lotu determinującym relacje między parametrami geometrycznymi samolotu i silnika jest start samolotu lub przelot naddźwiękowy na dużej wysokości. Zwykle doboru parametrów obiegu cieplnego silnika turbinowego dokonuje się w oparciu o charakterystyki wewnętrzne silnika- ciąg jednostkowy, jednostkowe zużycie paliwa. W oparciu o model silnika dwuprzepływowewgo, z mieszalnikiem strumieni, dopalaczem oraz model samolotu (przyjęto uproszczone charakterystyki aerodynamiczne i masowe) określono wpływ parametrów obiegu na podstawowe wskaźniki samolotu jak doskonałość aerodynamiczna, zasięg umowny i zasięg teoretyczny. Kolejnym problemem jest określenie parametrów termogazodynamicznych, które pozwalają minimalizować masę silnika i zużytego w trakcie misji samolotu paliwa. W trakcie misji tzw. długich parametr jednostkowej masy względnej silnika gamma Z osiąga minimum dla sprężu całkowitego sprężarki rzędu (20-30), ale większych niż wartości sprężu optymalnego. Niewielka zmiana w wartości minimum gamma Z powoduje znaczną zmianę w wartości sprężu sprężarki. Parametry termogazodynamiczne, które pozwalają minimalizować masę sumaryczną paliwa i silnika są mniejsze niż dla minimum jednostkowego zużycia paliwa i zbliżone do wartości charakterystycznych dla współczesnych silników lotniczych.
    Źródło:
    Journal of KONES; 2007, 14, 2; 571-578
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-6 z 6

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