Temat: Design Optimization - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Multidisciplinary design and optimization of gas turbine engine low pressure turbine at preliminary design stage
Autorzy:: Bar, W.
Orkisz, M.
Moustapha, H.
Powiązania:: https://bibliotekanauki.pl/articles/246241.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: design and optimization
turbomachinery
turbines
Opis:: The gas turbine engine has evolved rapidly during past decades to provide a reliable and efficient business solution for global transportation. The engine design process is clearly a large contributor to this evolution. This process is highly iterative, multidisciplinary and complex in nature. The success of an engine depends on a carefully balanced design that best exploits the interactions between numerous traditional engineering disciplines such as aerodynamics and structures as well as lifecycle analysis of cost, manufacturability, serviceability and supportability. To take into account all of these disciplines and optimization should be used. Currently most of present state-of-art numerical modelling methods, which are used mainly at detailed design stage, are unsuitable for this task due to very high computational time. The solution to this problem can be found in multidisciplinary design and optimization at preliminary design stage with use of simple 1-2D models. This paper presents current aero engine design process and indicates possibilities of future improvements by utilization of proposed methodology, which take into account aerodynamic, thermodynamic and structures (blade, fixing and disc) calculations, connected in one multidisciplinary model, which is suited for optimization. All disciplinary models are presented and described in this paper as well as connection between them, with study over design variable, goal function and constrains that should be used. Moreover, a strategy of optimization is proposed as well as methods for acceleration of optimization process by use of surrogate. The presentation of methodology is followed by example optimization of low-pressure aero engine turbine.
Źródło:: Journal of KONES; 2014, 21, 3; 15-22
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Factors influencing the precision of optimizing the values of definite scalar quantities according to the accepted criteria used in designing heat exchangers
Autorzy:: Łukaszewski, K.
Powiązania:: https://bibliotekanauki.pl/articles/244118.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: optimization
heat exchangers
design
Opis:: The paper outlines the essential factors influencing the precision of optimizing the values of definite scalar quantities according to the criteria that are used in designing heat exchangers. The paper refers to the method of designing heat exchangers of technical power systems in view of the required reliability of these systems described in the work [1]. Optimization is used for the velocity values of the flow of definite fluids through the heat exchanger and for the cooling fluid temperature T2’’ at the output of the definite heat exchanger, as they occur in significant relationships with definite scalar quantities in designing heat exchangers. The paper emphasizes divergences in the results of calculations of the above mentioned optimized values of definite scalar quantities on the example of designing a shell and tube condenser of marine steam turbine. The criterion of optimizing the values of definite scalar quantities is the minimum of total costs min Σ n i=1 Ki τ in the time τ. The time is the set value τ z and constitutes the period, in which the optimization is considered. The paper presents the following factors: time assumption τ z of the period, in which optimization is considered, price assumption of electrical energy KCe consumed in order to pump the cooling water in time τ z, assumption of the values of efficiency τ p of the pump of the cooling water in time τ z, assumption of the values of the friction factor λ str2 of the inside surfaces of the condenser tube in time τ z, at the cooling water flow, the selection of a model of the function determining the Nusselt number Nu2 from the set of models that can be used in a given designing case, price assumption (the selection of a manufacturer) of heat exchanger area KCA of a shell and tube condenser, assumption of the forecasted thickness δos2 of fouling on the heat exchanger area from the side of the flow of the condenser cooling water in time τ z. Finally, the conclusions resulting from the paper’s contents are presented.
Źródło:: Journal of KONES; 2013, 20, 4; 237-244
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Rational moulding of constructional figure and the usable properties of the airplane
Racjonalne formowanie postaci konstrukcyjnej i cech użytkowych samolotu
Autorzy:: Klepacki, Z.
Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/242868.pdf
Data publikacji:: 2007
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
projektowanie samolotów
modelowanie
optymalizacja
airplane design
modelling
optimization
Opis:: The choice ofparameters of designed airplane should take place according to rational rules, allows to evaluate of project-variants. In spite of the evidence of this ascertainment, both the theory and the designing practice concentrates on the methods of seeking of solutions, and the problem of valuing is maximized simplified, and sometimes outright vulgarized. During that time, it is criteria and limitations determine the form of unknotting, and in the effect about the commercial success of all undertaking. The schema of the general designing of the airplane permits to restore approximate conditions for the real work of the airplane. Obtained results substantially are relative to "depths" of the modelling of the airplane characteristic (accuracy of partial models), the end result is a compromise. Authors worked out the software for different types of airplanes obtaining probable results of calculations. The main elements of the definition of the projects task, the full and reduced morphological board, the partial model, the mathematical model of the airplane are illustrated in the paper.
Wybór parametrów projektowanego samolotu powinien odbywać się według racjonalnych zasad, pozwalających wartościować warianty projektowe. Mimo oczywistości tego stwierdzenia, teoria i praktyka projektowania koncentruje się na technikach szukania rozwiązań, zaś problem wartościowania jest maksymalnie upraszczany, a czasem wręcz trywializowany. Tymczasem, to kryteria i ograniczenia stanowią o postaci rozwiązania, a w efekcie o sukcesie handlowym całego przedsięwzięcia. Schemat ogólnego projektowania samolotu pozwala odtworzyć warunki zbliżone do rzeczywistego funkcjonowania samolotu, Uzyskane wyniki w dużym stopniu zależą od "głębokości" modelowania właściwości samolotu (precyzji modeli cząstkowych), rezultat końcowy jest wynikiem kompromisu. Autorzy opracowali oprogramowanie dla różnych typów samolotów uzyskując prawdopodobne wyniki obliczeń. Główne elementy definicji zadania projektowego, pełna i zredukowana tablica morfologiczna, model cząstkowy oraz model matematyczny samolotu są zilustrowane w artykule.
Źródło:: Journal of KONES; 2007, 14, 3; 272-278
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Optimal cruise performance of light transport aircraft from fuel efficiency point of view
Optymalne osiągi przelotowe lekkiego samolotu transportowego z punktu widzenia zużycia paliwa
Autorzy:: Klepacki, Z.
Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/244209.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: transport
projektowanie samolotów
modelowanie
optymalizacja
airplane design
modelling
optimization
Opis:: The need for the increase of speed, range and the useful load of general air transport is presently more actual than ever. In direct conjunction with these factors is the aircraft fuel efficiency. Determination of the fuel quantities used up in aircraft motions both in the air and on the ground has very essential meaning in the analysis of economics of the air transport. Reducing the amount of fuel consumed involves knowing the effect of alternate profiles and procedures on fuel consumption or fuel flow for the various aircraft types operating in the system. The aviation community is striving to provide more fuel efficient operations in the system. Critical to many of the efforts is the ability to estimate fuel consumption. A methodology of SFC (specific fuel consumption) valuation relating to aircraft performance and actual flight profile is the main goal of the work. Aircraft fuel consumption model consist of two submodels. The first is the aircraft computational model, with several submodels: geometrical, aerodynamic, mass, power unit. The second is utilization model, namely transport operation model. The calculations were done for few different categories airplanes. Final results and recommendations based on the analysis of fuel consumption and transportation energy effectiveness are presented in conclusions.
Potrzeba zwiększania szybkości, zasięgu i ładunku użytecznego transportu lotniczego jest obecnie bardziej aktualna niż kiedykolwiek. Wiąże się z tym sprawność wykorzystania paliwa. Określenie ilości paliwa zużywanego przez samolot poruszający się zarówno w powietrzu jak i na ziemi ma bardzo istotne znaczenie w analizie ekonomiki transportu. Minimalizacja ilości zużytego paliwa wymaga przeprowadzenia analizy wpływu profilu i procedur wykonywania lotów na wymaganą ilość paliwa w zależności od typu samolotu funkcjonującego w systemie transportowym. Firmy lotnicze dążą do wykonywania zadań z maksymalną efektywnością z punktu widzenia zużycia paliwa. Dla wielu z nich najważniejszym zadaniem jest, więc możliwość wiarygodnego oszacowania zużycia paliwa. Głównym celem pracy było opracowanie metody wyznaczania zużycia paliwa w zależności od rodzaju samolotu i profilu lotu. Aby zrealizować ten cel opracowany został odpowiedni model matematyczny składający się z dwóch pod-modeli. Pierwszy z nich to kompleksowy model obliczeniowy samolotu, drugi zaś, model użytkowania. Z wykorzystaniem tych dwóch modeli wyznaczone zostały wskaźniki oceny efektywności samolotów różnych kategorii wykonujących typowe zadania transportowe. Na podstawie analizy porównawczej wyników, sformułowane zostały wnioski dotyczące optymalnych zakresów użytkowania samolotów z różnymi rodzajami napędu oraz optymalnych profilów przelotowych.
Źródło:: Journal of KONES; 2008, 15, 2; 173-182
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Multi - material design optimization of a bus body structure
Autorzy:: Korta, J.
Uhl, T.
Powiązania:: https://bibliotekanauki.pl/articles/247771.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: weight reduction
bus structure
structural optimization
multi-material design
Opis:: In the recent years the safety and eco-friendliness have gained much of attention of the automotive stakeholders. These two characteristics are especially important in the case of mass transportation vehicles, such as buses or coaches, which are in continues use for long periods of time, covering significant distances. In such situations, the economical aspects play major role for the transportation companies which try to minimize operational costs of their fleet, by choosing vehicles with reduced fuel consumption. In order to obtain improvements in all the mentioned areas and hence to strengthen their position on the market, bus manufacturers have recently turned their attention to multimaterial design strategies. Structures built in that manner consist not only of regular steel parts, but contain also a mix of components made from various lightweight materials like aluminum alloys or composites, which allow for significant reduction in vehicle curb weight. However, due to the differences in mechanical characteristics which are especially evident in the case of laminates, the material substitution is not a straightforward task. In order to find the material distribution pattern that meets all the requirements, a great number of prototypic numerical models must be prepared and tested. To ease the search for the final solution, optimization techniques can be applied into the design process, allowing for automatic design modifications and assessment of the obtained results. The paper presents an attempt of enhancing the operational characteristics of a bus body structure with simultaneous reduction in the structural weight. In order to find the optimal component configuration, a multimaterial optimization was employed and supplemented by sensitivity and robustness analyses. Such a technique helps to discriminate the over-optimized solutions that are often pointed out as the most desirable by the optimization algorithms which neglect the uncertainties of the analysed system.
Źródło:: Journal of KONES; 2013, 20, 1; 139-146
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 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

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Skocz do pozycji: 7.

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

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