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    Wyświetlanie 1-8 z 8
    Tytuł:
    Analysis of operational characteristics of aviation diesel and gas turbine engines for light passenger aircraft
    Analiza operacyjnych charakterystyk lotniczych silników diesla i silników turbin gazowych dla lżejszego samolotu pasażerskiego
    Autorzy:
    Loginov, V.
    Ukraintes, Y.
    Powiązania:
    https://bibliotekanauki.pl/articles/213016.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    parametric shape
    light passenger aircrafts
    local airlines
    aviation Diesel engines
    turboprop engine
    gas turbine engine
    airplane engine
    technical and economic characteristics
    operational characteristics
    life-cycle hour cost
    Opis:
    A comparative analysis of aviation diesel and gas turbine engines in the light passenger aircraft system was conducted. Aircraft operational characteristics were obtained with the help of developed modular software system „Integration-2.1". For the formation of 5-9 seater modifications of aircraft as a prototype was taken aircraft Diamond DA42 with the location of passengers without aisle, crew consisted of 1 person. For the formation of 10-20 sealer aircrafts modifications as prototypes were taken aircrafts EV-55 and L-410UVP, the crew consisted of 2 persons, was adopted the full completion of aircraft equipment, power plant consists of two engines was adopted. It shows the economic advisability of the aircraft gas turbine engines use for airplanes of local airlines (5-6 people). It was found that the life-cycle cost of the aircraft with more passengers become lower in modifications with gas turbine engines, therefore, the use of this type of engine is advisable for aircraft with greater passenger capacity. It was found that the main factors influencing the life-cycle cost of the aircraft, are the resource characteristics of the engine, the cost of its maintenance and repair, as well as the price of fuel.
    Przeprowadzono analizę porównawczą lotniczych silników diesla i silników turbinowych dla lekkich samolotów pasażerskich. Eksploatacyjne charakterystyki samolotu uzyskane przez rozwinięty modułowy system oprogramowania „Integracja-2.1". Do opracowania modyfikacij 5-9 miejscowych samolotów jako punkt wyjściowy wybrano samolot Diamond DA42 z kabiną pasażerską bez korytarza i jednoosobową załogą. Do opracowania 10-20 miejscowych modyfikacji samolotów jako punkty wyjścia wybrano-samoloty EV-55 i L-410UVP, z dwuosobową załogą, przyjęty przez pełny skład sprzętu lotniczego, punkt mocy składa się z dwóch silników. Wykazano wykonalność ekonomiczną wykorzystania lotniczych turbin gazowych dla samolotów miejscowych linii lotniczych (do 5-6 osób). Stwierdzono, że koszt cyklu życiowego samolotu z wielką ilością pasażerów staje się mniejsza u modyfikacji z turbiną gazową, więc, wykorzystanie tego typu silników jest wskazane na samolotach o większej liczbie miejsc pasażerskich. Stwierdzono, że głównymi czynnikami wpływającymi na koszt cyklu życia samolotu, są cechy silnika, koszt jego utrzymania i naprawy, a także ceny paliwa.
    Źródło:
    Prace Instytutu Lotnictwa; 2016, 4 (245); 103-115
    0509-6669
    2300-5408
    Pojawia się w:
    Prace Instytutu Lotnictwa
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    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
    Artykuł
    Tytuł:
    Determining of the optimum size of turbofan engine for obtaining the maximum range of multi-purpose airplane
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/247502.pdf
    Data publikacji:
    2010
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    airplane range
    airplane and engine integration
    engine cycle parameters
    Opis:
    Aircraft range is one of the most important criteria of the assessment of the performance properties of an aircraft. For the needs of the paper the mathematical model of an aircraft (multi-purpose aircraft) and the engine which propels the aircraft was built (turbofan, two-spool, with jet mixer). For the analysis it was chosen so-called typical Breguet model and the conventional range. The models were modified as they should consider the characteristics of the engine in the non-dimensional form. The aim of the simulation research was to discuss the influence of the engine parameters (geometrical and thermodynamic) on the aircraft range, realized mainly in the subsonic and supersonic conditions. The decision which of these conditions can have a significant influence on the selection of the calculating point (i.e. the point which determines the geometrical dimensions of the engine) is difficult as there is no clear direction which aircrafts make up the important share in a mission or missions. It was decided that the parameter which connects the engine geometry with the range model is so-called non-dimensional coefficient of engine geometry which is the relation of the area on the inlet to the engine related to the wing area of the aircraft. It was shown that for various parameters of the engine cycle it is possible to show such a value of the non-dimensional coefficient of geometry which maximizes the aircraft range. The results obtained show opposite requirements as for the engine geometry for the subsonic and supersonic flight. On this basis the compromise solution was proposed to fulfil the requirements of the multi-purpose aircraft.
    Źródło:
    Journal of KONES; 2010, 17, 2; 511-518
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Identyfikacja stanu dynamicznego turbinowych silników lotniczych
    Identification of dynamic state of the airplane turbine jet engine
    Autorzy:
    Żółtowski, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/327912.pdf
    Data publikacji:
    2001
    Wydawca:
    Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
    Tematy:
    diagnostyka techniczna
    identyfikacja
    silnik lotniczy
    eksploatacja
    airplane engine
    technical diagnostics
    identification
    exploitation
    Opis:
    W pracy tej przedstawiono zasady modelowania w identyfikacji stanu dynamicznego maszyn. Wskazano na możliwe sposoby modelowania stanu dla potrzeb diagnostyki technicznej. Jako przykład omówiono badania wstępne silników turbinowych, które pozwalają na ocenę i prognozowanie ich stanu technicznego oraz ustalenie polityki eksploatacyjnej silników, co jest bardzo istotne z punktu widzenia bezpieczeństwa i rachunku ekonomicznego.
    In this work one represented rules of fashioning identification state of dynamic machines. One showed on possible manners of fashioning of state for needs of technical diagnostics. As example one talk overed investigations initial reliabilities of turbine - engines, which permit on estimation and prognoses their of technical state and settlement of policy exploitation of engines, what is very essential from point of view safety and of economic bill.
    Źródło:
    Diagnostyka; 2001, 24; 23-30
    1641-6414
    2449-5220
    Pojawia się w:
    Diagnostyka
    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:
    Selection criteria of internal parameters of turbofan engine for the type of multi-task aircraft mission
    Kryteria doboru parametrów wewnetrznych silnika dwuprzepływowego do rodzaju misji samolotu wielozadaniowego
    Autorzy:
    Wygonik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/133911.pdf
    Data publikacji:
    2013
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    multi-task airplane
    turbofan engine
    engine parameters optimization
    samolot wielozadaniowy
    silnik przepływowy
    optymalizacja parametrów silnika
    Opis:
    The problem described in the paper concerns the selection strategy of the so-called calculation point of the turbofan engine of the multi-task aircraft already at the stage of preliminary design of the aircraft and aircraft engine as a system. A multi-task airplane during each mission needs to perform a series of tasks with different levels of power utilization, while changing the mass, at different altitudes and flight velocities. There was defined the criterion of the LoLoLo mission based on an assessment of mission energy consumption. The calculation results were presented from the point of view of the influence of thermo-gas-dynamic parameters of the comparative cycle circulation (such as compression, turbine inlet temperature, the degree of streams distribution) on the criterion of energy resources usage. The presented criterion allows to make a correct selection of parameters of thermodynamic cycle from the viewpoint of energy possibilities of an aircraft and a mission.
    Problem przedstawiony w artykule dotyczy strategii wyboru tzw. punktu obliczeniowego silnika systemu lotniczego. Samolot wielozadaniowy podczas każdej misji musi wykonać cały szereg zadań, różniących się poziomem wykorzystania mocy, przy zmieniającej się masie własnej, na różnych wysokościach i prędkościach lotu. Zdefiniowano kryterium oceny misji typu LoLoLo w oparciu o ocenę energochłonności misji. Wyniki obliczeń przedstawiono z punktu widzenia wpływu parametrów termogazodynamicznych obiegu porównawczego (jak spręż, temperatura przed turbiną, stopień podziału strumieni) na kryterium wykorzystania zasobów energetycznych. Przedstawione kryterium pozwala dokonac prawidłowości wyboru parametrów obiegu termodynamicznego z punktu widzenia możliwości energetycznych samolotu i misji.
    Źródło:
    Combustion Engines; 2013, 52, 3; 483-488
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    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:
    Two-combustor turbofan engine performance analysis
    Autorzy:
    Jakubowski, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/241903.pdf
    Data publikacji:
    2014
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    jet engine
    turbofan engine
    engine performance
    airplane engine development
    Opis:
    A conception of a two-combustor turbofan engine is the main scope of this paper. At the beginning, the problems of turbofan engines development are briefly discussed as a background of this work. In this part the turbofan engines innovation activities are presented. It is mentioned the engine’s innovations consists of many aspects but some important ones are: lowering of production operation cost, maintenance, reduction of noise and exhaust gases emission while engine reliability should stay on the same level or event increase. Next, the conception of turbofan engine with two combustors is presented in this context. Some positive aspects for environment, production and maintenance of such engine are discussed. Then the thermodynamic cycle of two-combustor engine is presented and analysed. On this basis, the engine numerical model is prepared. Next, some information about the model simplifications and calculations done to determine performance of the engine is presented. Then the results of the simulation calculations of the engine performance are presented and discussed. The relationship of engine thrust and specific fuel consumption vs. engine flight conditions are shown. Based on the results there were discussed the advantages and disadvantages of two combustors engine as an airplane propulsion are specified. The conclusions are formulated and presented in the last part of the paper.
    Źródło:
    Journal of KONES; 2014, 21, 3; 141-148
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-8 z 8

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