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    Wyświetlanie 1-7 z 7
    Tytuł:
    Experimental determination of compressor map of the DGEN 380 engine compressor using the WESTT CS/BV turbine engine simulator
    Autorzy:
    Pazura, Karolina
    Orkisz, Marek
    Powiązania:
    https://bibliotekanauki.pl/articles/2097512.pdf
    Data publikacji:
    2021
    Wydawca:
    Polskie Towarzystwo Naukowe Silników Spalinowych
    Tematy:
    compressor map
    engine bench
    turbofan jet engine
    turbine engine
    mass flow rate
    mapa kompresora
    ława silnika
    silnik turbowentylatorowy
    silnik turbinowy
    masowy wskaźnik szybkości płynięcia
    Opis:
    Currently aviation focuses mainlly on increasing the economy and ecology of engines. Production of NOx, CO2 and SO2 adversaly impacts the environment. Parallel goal to minimize SFC to achieve both lower: emission and mission costs. The optimization of components is thus very important. One of the ways of optimizing cycle is doing that based on compressor maps. However it is very expensive to plot one since experimental work needs to be done. The aim of this article is to present a methodology of creating compressor map based on ENGINE ANALOGY. There was used the virtual bench WESTT CS/BV for tests to receive pressure ratio and mass flow of DGEN 380 for three different values of flight speed and altitude, while the rotational speed was changed. The construction similarity of CFM 56-5B and APS 3200 gives the opportunity to plotted compressor maps using the engine analogy without the need for an experiment or using the virtual bench.
    Źródło:
    Combustion Engines; 2021, 60, 2; 26--31
    2300-9896
    2658-1442
    Pojawia się w:
    Combustion Engines
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Unstable operation of the turbine aircraft engine
    Autorzy:
    Kozakiewicz, A.
    Kowalski, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/280192.pdf
    Data publikacji:
    2013
    Wydawca:
    Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
    Tematy:
    turbine engine
    engine dynamics
    compressor stall
    Opis:
    The article presents reasons for generating a non-uniform field of parameters in the compressor inlet of a turbine aircraft engine and its influence on the air jet kinematics at lowering fatigue strength of the compressor blade. Analysis of the engine torque in function of the engine operation time has been performed. Courses of the basic turbine engine operations parameters during compressor stall have been presented. The significant role of changes of the first torque derivative in relation to variation of the rotor acceleration in that assessment has been determined, which may be an important signal of the compressor surge occurring in the compressor. That parameter may be a signal for the control system to eliminate the negative phenomenon. The engine dynamics during the compressor surge has also been presented by developing the phase images of the engine operation basic parameters. The article includes analysis of dynamical changes in temperature of the combustion gases.
    Źródło:
    Journal of Theoretical and Applied Mechanics; 2013, 51, 3; 719-727
    1429-2955
    Pojawia się w:
    Journal of Theoretical and Applied Mechanics
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Impact of the vibration amplitude on the fatigue life of compressor blades with mechanical defects
    Autorzy:
    Witek, L.
    Bednarz, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/245666.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    turbine engine
    compressor blade
    v-notch
    resonant vibrations
    fatigue life
    Opis:
    In this paper, the results of an experimental fatigue analysis of the compressor blades with the mechanical defects were presented. Before the fatigue test, the blades were damaged in order to simulate the foreign object damage. In this operation, the v-notch was created by hitting the hard object into leading edge of the blade. The similar kind of damage occurs when the small particles as stones or sandy grains are sucked to the engine inlet and next have a collision with the rotated blade. As a result of the impact, both the plastic strains and also the initial stresses occur in the vicinity of the notch. These stresses have a large influence on the number of load cycles to crack initiation. During the experiment, the blades were entered into transverse vibration with the use of Unholtz-Dickie TA-250 vibration system. The crack propagation process was conducted in resonance conditions. During the fatigue test the blades were periodically bent. In investigations, the different vibration amplitudes of the blade were considered. During the fatigue test, the crack length was monitored with the use of non-destructive fluorescent penetrant method. The amplitude of the blade tip displacement was controlled using the Polytec PSV H-400S laser scanning vibrometer. The main aim of this work is analysis of influence of the vibration amplitude on the fatigue life of the compressor blade of the turbine engine. The results of presented investigations are important from the research and also from the practical point of view and have an influence on safety and reliability of the turbine engine.
    Źródło:
    Journal of KONES; 2016, 23, 3; 571-576
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Influence of the crack propagation velocity on heat release in compressor blades during fatigue tests
    Autorzy:
    Bednarz, A.
    Kuźniar, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/244568.pdf
    Data publikacji:
    2016
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    crack propagation velocity
    notch
    thermovision
    turbine engine
    heat distribution
    Opis:
    In this work, the influence of the crack propagation velocity on heat release in blade was shown. Research was be performed during fatigue test of the compressor blade. In the investigations, the blade with the V-notch was examined. The blades during experiment were entered into transverse vibration by a vibration system Unholtz-Dickie UDCO-TA-250. The crack propagation process was conducted in resonance condition. The blades were periodically bended what simulates geometry changes during operation of the engine. The main part of the work is based on research of fatigue. During investigations both the amplitude of the crack length and also the blade tip displacement were controlled. Additional velocity of crack propagation was measured by change of a crack length in time. In the same time temperature, distribution pictures were observed. The taken picture was used to exhibit the phenomenon and shown the heat propagation direction. The main results of presented investigation are both the parameters of a crack and the crack growth dynamics in the compressor blade subjected to vibrations. An additional original result of the work is connection between velocity of crack propagation and temperature distribution taken from picture. The result of above analysis can be used in determining the amount of energy released during the cracking process and evaluate the amount of energy required for the growth of a gap. In this work, the capabilities of the proposed method and the problems associated with it were defined. The results presented in this paper have theoretical and practical value.
    Źródło:
    Journal of KONES; 2016, 23, 1; 67-73
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badania wstępne możliwości oceny stanu technicznego układów cylindrowych silnika na podstawie analizy procesu sprężania
    Preliminary tests able to assess the condition of the engine cylinder layouts based on the analysis of the compression process
    Autorzy:
    Łutowicz, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/222374.pdf
    Data publikacji:
    2004
    Wydawca:
    Akademia Marynarki Wojennej. Wydział Dowodzenia i Operacji Morskich
    Tematy:
    sprężarka
    silnik turbinowy
    tłoki
    compressor
    turbine engine
    pistons
    Opis:
    W niniejszym opracowaniu przedstawiono koncepcję obróbki wykresów indykatorowych polegającą na dopasowaniu modelu procesu sprężania do zarejestrowanego przebiegu ciśnienia wewnątrzcylindrowego tłokowego silnika spalinowego. W procesie dopasowania modelu można odtworzyć nieznane lub niepewne parametry wejściowe dla tego modelu, które doprecyzują jakość stawianej diagnozy o stanie technicznym przestrzeni roboczych silnika pod względem jakościowym i ilościowym.
    The paper presents an initial concept of processing indicator diagrams which consists in matching the compression process model to the recorded inside-cylinder pressure distribution in an internal combustion engine. In the model matching process it is possible to recreate unknown or uncertain input parameters for this model, which particularize the quality of the diagnosis related to the technical condition of the working spaces in the engine with respect to quality and quantity.
    Źródło:
    Zeszyty Naukowe Akademii Marynarki Wojennej; 2004, R. 45 nr 2 (157), 2 (157); 97-107
    0860-889X
    Pojawia się w:
    Zeszyty Naukowe Akademii Marynarki Wojennej
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Validation of selected presented method measured of length fatigue gap on compressor blades forming during resonant tests
    Autorzy:
    Kuźniar, M.
    Bednarz, A.
    Lichoń, D.
    Witek, L.
    Powiązania:
    https://bibliotekanauki.pl/articles/243027.pdf
    Data publikacji:
    2017
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    crack propagation
    gap
    thermovision
    turbine engine
    blades
    Opis:
    In this work, the validation of selected presented method measured of length fatigue gap was shown. The article describes three methods of determining fatigue gaps. The object of the study was the first stage compressor blade from aircraft engine. Blades have defects on the leading edge. This defect on the blade (as a result of the resonance vibration) was the origin point of the fatigue gap. Two of the methods, fluorescent and thermovision, were optical. The fluorescent method was a direct measurement, whereas direct-indirect thermography. The last of the presented methods was an analytical method, showing an algorithm based on amplitude-frequency characteristics. The advantages and disadvantages of these methods were compared. As a result of the analysis performed by the algorithm, there were specified patterns defining the dependence of change in crack length depending on the asymmetry of AF characteristics. The accuracy of the following methods and the results obtained for chord length were determined. Thanks to such use, these results have a utilitarian meaning. Such a compilation allowed us to evaluate the usefulness of particular measurement methods. Proposed methods of measuring the length of fatigue crack are used in experimental studies. It is also possible to implement them for research conducted during the operation of an aircraft engine.
    Źródło:
    Journal of KONES; 2017, 24, 3; 151-158
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Design and Strength Analysis of Curved-Root Concept for Compressor Rotor Blade in Gas Turbine
    Autorzy:
    Wdowiński, W.
    Szymczyk, E.
    Jachimowicz, J.
    Moneta, G.
    Powiązania:
    https://bibliotekanauki.pl/articles/97975.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    finite element method
    turbine engine
    rotor disk
    rotor blades
    blade-disc connection
    shape optimization
    Opis:
    The motivation of the article is fatigue and fretting issue of the compressor rotor blades and disks. These phenomena can be caused by high contact pressures leading to fretting occurring on contact faces in the lock (blade-disk connection, attachment of the blade to the disk). Additionally, geometrical notches and high cyclic loading can initiate cracks and lead to engine failures. The paper presents finite element static and modal analyses of the axial compressor 3rd for the original trapezoidal/dovetail lock geometry and its two modifications (new lock concepts) to optimize the stress state of the disk-blade assembly. The cyclic symmetry formulation was used to reduce modelling and computational effort.
    Źródło:
    Fatigue of Aircraft Structures; 2017, 9; 137-155
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-7 z 7

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