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    Wyświetlanie 1-9 z 9
    Tytuł:
    Robotic assembly of aero-engine components
    Autorzy:
    Jayaweera, N.
    Webb, P.
    Ye, C.
    Johnson, C.
    Powiązania:
    https://bibliotekanauki.pl/articles/1429288.pdf
    Data publikacji:
    2008
    Wydawca:
    Wrocławska Rada Federacji Stowarzyszeń Naukowo-Technicznych
    Tematy:
    robotic assembly
    aero-engine components
    Opis:
    The VITAL (EnVIronmenTALly Friendly Aero Engines) project funded by the European Commission under Framework 6 aims to provide significant reductions in aero-engine fuel burn, noise and emissions through the development of innovative design and manufacturing techniques. One method of reducing the amount of fuel burnt, and hence CO2 produced, is to reduce the weight of the engine. A significant proportion of an engine's weight is due to the large castings used to form the main non-rotating structures; the replacement of these with fabricated structures could provide a significant weight reduction. This paper describes the design and implementation of a robotic assembly cell for complex aero-engine components. A series of experiments were performed to prove the feasibility of the automated assembly process. The results presented indicate that automated robotic assembly is feasible and cost effective.
    Źródło:
    Journal of Machine Engineering; 2008, 8, 3; 5-16
    1895-7595
    2391-8071
    Pojawia się w:
    Journal of Machine Engineering
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A Novel Approach for the Assembly of Fabricated Aero-Engine Components
    Autorzy:
    Jayaweera, N.
    Webb, P.
    Johnson, C.
    Powiązania:
    https://bibliotekanauki.pl/articles/971261.pdf
    Data publikacji:
    2009
    Wydawca:
    Wrocławska Rada Federacji Stowarzyszeń Naukowo-Technicznych
    Tematy:
    robotic assembly
    best-fit algorithm
    aero-engine components
    Opis:
    Currently the manufacturing of aero-engine intercase is primarily a single piece titanium casting and has slightly deteriorated material properties as compared to sheet metal parts and has long manufacturing lead time. As an alternative solution to above problems, the VITAL (Environmentally Friendly Aero Engines) project aims to design, manufacture and test the critical technologies required to develop new type of clean and low noise aero engines by developing innovative technical solutions to reduce the engine's weight, thereby reducing both fuel consumption and CO2 emission. This requires the fabrication of small and weight optimised parts which will be automatically manipulated, welded, assembled and inspected in a flexible fabrication cell. The paper introduces a novel techniques for compensating the deformation that occur in aero-engine fabricated components and potential component handling errors using standard industrial robots, an advanced end-effector, mathematical processing, non-contact metrology systems and cell control system. The system described in this paper uses in-process measurement sensors to determine the component's exact location prior to the assembly operation. The core of the system is a set of algorithms capable of best fitting measurement data to find optimal assembly of components.
    Źródło:
    Journal of Machine Engineering; 2009, 9, 4; 61-70
    1895-7595
    2391-8071
    Pojawia się w:
    Journal of Machine Engineering
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The effects of variable operational parameters on an aero engine labyrinth seals performance
    Autorzy:
    Szymański, A.
    Dykas, S.
    Majkut, M.
    Strozik, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/175364.pdf
    Data publikacji:
    2018
    Wydawca:
    Polska Akademia Nauk. Czytelnia Czasopism PAN
    Tematy:
    labyrinth seals
    experiment
    turbomachinery
    gas turbine
    validation
    Opis:
    The paper presents the accurate assessment of the amount of gas flowing through three types of aero-engine expander sealing. Structures consisting of straight-through labyrinth seals – with one, two and three fins are considered. The study deploys two independent approaches. The first one focuses on the experimental research using high-precision test section with non-rotating labyrinth seals specimen connected to a high capacity vacuum installation. Experimentally tested seals are of actual size (model to engine scale is 1:1). High accuracy hot-wire anemometry probes, and orifice plate are deployed to evaluate the flow indicators accurately, allowing for comparison of different sealing structures. The second approach uses quasi-two-dimensional axissymmetric, steady-state Reynolds averaged Navier Stokes (RANS) computations to simulate the flow field. Various meshes and turbulence models were tested, presenting capabilities as well as limitations of specific computational approaches. The experimental and computational results were compared with literature data, showing a good agreement regarding overall trends, yet underlining some local discrepancies. This paper brings two significant findings. The 2D RANS methods tend to overestimate the leakage when compared with experimental results, and the difference is more significant for advanced arrangements. There is a notable difference between the performance of labyrinth seal with one fin and structure with two and three fins. In some operational areas, one-finned seal performs better than more advanced ones, reducing the leakage more effectively. This feature of one finned seal is not intuitive, as one would expect it to perform worse than a seal with two or three fins.
    Źródło:
    Transactions of the Institute of Fluid-Flow Machinery; 2018, 140; 83-104
    0079-3205
    Pojawia się w:
    Transactions of the Institute of Fluid-Flow Machinery
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Early detection of fatigue cracks in turbine aero - engine rotor blades during flight
    Autorzy:
    Szczepanik, R.
    Powiązania:
    https://bibliotekanauki.pl/articles/245961.pdf
    Data publikacji:
    2013
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aero-engines
    diagnostic of aircraft engine
    non-contact blade-vibration measurement
    damage to the aircraft
    Opis:
    The author shows results of research done in the Air Force Institute of Technology concerning design, development and implementation of modern diagnostic systems for aero-engines. The papers gives brief description of a project of a new advanced monitoring system basing on non-contact blade-vibration measurement. Recent monitoring systems for engines offer a great potential to reduce the high maintenance costs of aircraft while increasing reliability and safety. These systems check for abnormal engine responses to detect failures, saving lives and reducing secondary damage to the aircraft. A phenomenon of dynamic change of an aero-engine compressor blades natural frequency in course of fatigue cracks propagation in their roots on the example of a Polish turbojet engine is described. On the ground of this phenomenon main working principles of a device, which measures vibrations of turbine engine rotor blades with application of the noninterfering discrete method (MDPh), used for early detection of first stage compressor blade cracks are discussed. Typical representation of the first stage compressor blades vibration during engine acceleration, representation of the first stage blades vibration during engine acceleration and deceleration with steady-state stator distortions, crack initiation and propagation symptoms in blades, comparison of blade vibration spectra of the same blades for different conditions are presented in the paper.
    Źródło:
    Journal of KONES; 2013, 20, 1; 337-342
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Silnik lotniczy jako obiekt badań tribologicznych
    Aero-engine as the object of tribological research
    Autorzy:
    Nidzgorska, Adrianna
    Witoś, Mirosław
    Perczyński, Jerzy
    Kułaszka, Artur
    Powiązania:
    https://bibliotekanauki.pl/articles/38933889.pdf
    Data publikacji:
    2023
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    lotnictwo
    tarcie
    diagnostyka
    badanie tribologiczne
    silnik lotniczy
    instalacja olejowa
    aviation
    friction
    diagnostics
    tribological testing
    aero-engine
    oil system
    Opis:
    Podczas pracy silników lotniczych (turbinowych i tłokowych) występują procesy zużycia w węzłach tribologicznych, które w znaczny sposób wpływają na niezawodność i bezpieczeństwo eksploatacji statków powietrznych. W artykule przedstawiono aspekty diagnostyki tribologicznej silników lotniczych bazującej na okresowych badaniach próbek środka smarnego w laboratoriach. Na początku przedstawiono obiekt badań z uwzględnieniem cech konstrukcyjnych, parametrów pracy i stosowanych środków smarnych oraz podstawy teoretyczne badań tribologicznych. Następnie opisano metody badań stosowane w diagnostyce tribologicznej silników lotniczych, uwzględniając procesy starzenia i zanieczyszczenia środków smarnych, normy, metodyki badawcze i doświadczenia eksploatacyjne opisane w literaturze, w tym krzywą podatności eksploatacyjnej. Możliwości metod badawczych zobrazowano wynikami z okresowych badań tribologicznych silników turbinowych, uzyskanymi w akredytowanym laboratorium diagnostyki systemów tribologicznych. W dalszej części wskazano rolę analizy trendu i kryteriów statystycznych w procesie diagnozowania i zarządzania ryzykiem eksploatacji silników lotniczych, eksploatowanych zarówno według stanu technicznego, jak i planowanych obsług technicznych (resursów). Zasygnalizowano możliwość poprawy wiarygodności diagnostyki tribologicznej silników lotniczych na bazie doświadczeń z przemysłu – monitorowania wybranych parametrów tribologicznych w czasie rzeczywistym. W podsumowaniu wskazano na wysoką efektywność i rolę diagnostyki tribologicznej w utrzymaniu bezpieczeństwa eksploatacji floty różnych typów statków powietrznych.
    During the operation of aero-engines (turbine and piston engines), wear processes occur in tribological nodes, which significantly affect the reliability and safety of flight operations. This paper presents aspects of tribological diagnostics of aircraft engines based on periodic testing of lubricant samples in laboratories. Firstly, the object of research with its design features, operating parameters and used lubricants is presented, as well as the theoretical basis of tribological testing. This was followed by a description of the testing methods used in tribological diagnostics of aero-engines, taking into account lubricant degradation and contamination processes, standards, testing methodologies and operating experience described in the literature, including the machine failure curve. Next, the capabilities of the testing methods are illustrated with results from periodic tribological testing of turbine engines, obtained at an accredited tribological systems diagnostics laboratory. In the following section, the role of trend analysis and statistical criteria in the process of diagnosing and managing the risk of operation of aero-engines, exploited according to both their technical condition and planned maintenance, was indicated. Then, the possibility of improving the reliability of tribological diagnostics of aero-engines on the basis of experience from industry - real-time monitoring of selected tribological parameters - was signalled. In conclusion, the high efficiency and role of tribological diagnostics in maintaining the operational safety of a fleet of different aircraft types is indicated.
    Źródło:
    Journal of KONBiN; 2023, 53, 3; 87-128
    1895-8281
    2083-4608
    Pojawia się w:
    Journal of KONBiN
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Study of bypass ratio increasing possibility for turbofan engine and turbofan with inter turbine burner
    Autorzy:
    Jakubowski, Robert
    Powiązania:
    https://bibliotekanauki.pl/articles/244907.pdf
    Data publikacji:
    2019
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    aero engine
    turbofan engine
    combustion engines
    aero engine development
    turbine inter stage burner
    Opis:
    Current trends in the high bypass ratio turbofan engines development are discussed in the beginning of the paper. Based on this, the state of the art in the contemporary turbofan engines is presented and their change in the last decade is briefly summarized. The main scope of the work is the bypass ratio growth analysis. It is discussed for classical turbofan engine scheme. The next step is presentation of reach this goal by application of an additional combustor located between high and low pressure turbines. The numerical model for fast analysis of bypass ratio grows for both engine kinds are presented. Based on it, the numerical simulation of bypass engine increasing is studied. The assumption to carry out this study is a common core engine. For classical turbofan engine bypass ratio grow is compensated by fan pressure ratio reduction. For inter turbine burner turbofan, bypass grown is compensated by additional energy input into the additional combustor. Presented results are plotted and discussed. The main conclusion is drawing that energy input in to the turbofan aero engine should grow when bypass ratio is growing otherwise the energy should be saved by other engine elements (here fan pressure ratio is decreasing). Presented solution of additional energy input in inter turbine burner allow to eliminate this problem. In studied aspect, this solution not allows to improve engine performance. Specific thrust of such engine grows with bypass ratio rise – this is positive, but specific fuel consumption rise too. Classical turbofan reaches lower specific thrust for higher bypass ratio but its specific fuel consumption is lower too. Specific fuel consumption decreasing is one of the goal set for future aero-engines improvements.
    Źródło:
    Journal of KONES; 2019, 26, 2; 61-68
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Platerowanie laserowe zaworów wylotowych silnika lotniczego wykonanych ze stali X53CrMnNiN 21-9
    Laser plating of outlet valves of aero-engine made of X53CrMnNiN 21-9 steel
    Autorzy:
    Bogdanowicz, Z.
    Napadłek, W.
    Grzelak, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/208455.pdf
    Data publikacji:
    2006
    Wydawca:
    Wojskowa Akademia Techniczna im. Jarosława Dąbrowskiego
    Tematy:
    stal zaworowa X53CrMnNiN 21-9
    proszki stellitowe
    platerowanie laserowe
    X53CrMnNiN 21-9 valvular steel
    stellit powders
    laser plating
    Opis:
    W pracy przedstawiono metodę laserowego napawania stali zaworowej oraz zaworów silnika spalinowego, zbadano morfologię stosowanych proszków do napawania oraz określono podstawowe właściwości użytkowe napawanych warstw.
    The paper presents a method of laser pad welding of a valve steel and a combustion engine valves. Morphology of the powders used for plating was examined as well as basic useful properties of the padded layers were determined.
    Źródło:
    Biuletyn Wojskowej Akademii Technicznej; 2006, 55, 4; 127-138
    1234-5865
    Pojawia się w:
    Biuletyn Wojskowej Akademii Technicznej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A brief overview and metallography for commonly used materials in aero jet engine construction
    Autorzy:
    Belan, J.
    Vasko, A.
    Kucharikova, L.
    Powiązania:
    https://bibliotekanauki.pl/articles/111670.pdf
    Data publikacji:
    2017
    Wydawca:
    Stowarzyszenie Menedżerów Jakości i Produkcji
    Tematy:
    aluminium alloy
    titanium alloy
    nickel-base alloys
    metallography procedures
    B/W and colour contrast
    stop aluminium
    stop tytanu
    stopy na bazie niklu
    odczynnik trawiący
    Opis:
    Aluminium, titanium, and nickel base alloys are mostly and widely used for aircraft jet engine construction. A proper evaluation of its microstructure is important from working safety point of view. To receive a well prepared sample of microstructure, some important steps have to be undertaken. Except for proper grinding and polishing of a sample, structure developing is a significant step, too. In order to develop microstructure various chemical reagents were used to achieve the best results for microstructure evaluation. The chemical reagents were used according to the previous knowledge and some new ones were also tested. Aluminium AK4-1č, titanium VT – 8, and nickel VŽL – 14 and ŽS6 – U alloys were used as an experimental materials. Alloy AK4-1č is used for fan blade production with working temperatures up to 300°C. It is a forged piece of metal machined down into final shape by five-axe milling machine. Alloy VT – 8 is used for high pressure compressor rotor blade production with working temperatures up to 500°C. Blades are forged as well and finally grinded. Finally nickel base alloys VŽL – 14 and ŽS6 – U are used for turbine blade production with working temperatures up 950°C. Blades for turbine are casted into mould with reducible models.
    Źródło:
    Production Engineering Archives; 2017, 17; 9-14
    2353-5156
    2353-7779
    Pojawia się w:
    Production Engineering Archives
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The quality assurance of cast and wrought aero jet engine components made from Ni-base superalloys with using of quantitative metallography methods and alloys lifetime prediction
    Autorzy:
    Belan, Juraj
    Kuchariková, Lenka
    Mazur, Magdalena
    Tillová, Eva
    Hanusová, Patrícia
    Powiązania:
    https://bibliotekanauki.pl/articles/104037.pdf
    Data publikacji:
    2019
    Wydawca:
    Stowarzyszenie Menedżerów Jakości i Produkcji
    Tematy:
    quality assurance
    cast Ni-base superalloys
    wrought Ni-base superalloys
    turbine blades
    turbine disc
    quantitative metallography
    zapewnienie jakości
    superstopy na bazie Ni
    łopatki turbin
    tarcza turbiny
    metalografia ilościowa
    Opis:
    The Ni-base superalloys are used in the aircraft industry for the production of aero engine most stressed parts, turbine blades or turbine discs. Quality of aero jet engine components has a significant influence on the overall lifetime of a jet engine as itself as well as the whole airplane. From this reason a dendrite arm spacing, grain size, morphology, number and value of γ' - phase are very important structural characteristics for blade or discs lifetime prediction. The methods of quantitative metallography are very often used for evaluation of structural characteristics mentioned above. The high-temperature effect on structural characteristics and application of quantitative methods evaluation are presented in this paper. The two different groups of Ni-base alloys have been used as experimental material: cast alloys ZhS6K and IN713LC, which are used for small turbine blades production and wrought alloys EI 698VD and EI 929, which are used for turbine disc production. Selected alloys have been evaluated in the starting stage and after applied heattreatment at 850°C for 24 hrs. This applied heat-treatment causes structural changes in all alloys groups. In cast alloy dendritic structure is degraded and gamma prime average size has grown what has a negative influence on turbine blade creep rupture life. Wrought alloys show partially grain boundary melting and grain size changed due to recrystallization what causes mechanical properties decreasing - ultimate tensile strength mainly.
    Źródło:
    Quality Production Improvement - QPI; 2019, 1, 1; 222-229
    2657-8603
    Pojawia się w:
    Quality Production Improvement - QPI
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-9 z 9

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