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Wyszukujesz frazę "fatigue stress" wg kryterium: Wszystkie pola

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    Tytuł:
    The Effect of a Complex Stress State on Fatigue Crack Propagation and the Orientation of the Cracking Plane in VT3-1 Aeronautical Titanium Alloy
    Autorzy:
    Kocańda, D.
    Mierzyński, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/97799.pdf
    Data publikacji:
    2009
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Opis:
    The subject of the paper is the investigations of fatigue crack imitation and propagation in notched specimens made of the VT3-1 aeronautical russian titanium alloy under combined bending - torsion loading. The presence of short cracks was revealed at various ratios of bending to torsion. Experimental courses of short and long crack growth rates have been proved by the SEM and TEM micrographs which illustrated the changes in the mechanism of cracking in the examined specimens. The attempt was undertaken in order to explain partly brittle fracture that was observed in the range of fatigue short crack growth in the VT3-1 titanium alloy specimens. The results of the study of atmospheric hydrogen absorption capability and its ability for penetration inside the faces of nucleated and propagated microcracks in the surface layer allowed for suggestion that the cleavage mechanism of fracture found in the regime of short crack growth in the VT3-1 titanium alloy specimens was induced by hydrogen.
    Źródło:
    Fatigue of Aircraft Structures; 2009, 1; 116-130
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests
    Autorzy:
    Brzęczek, J.
    Gruszecki, H.
    Pieróg, L.
    Deszcz, F.
    Pietruszka, J.
    Powiązania:
    https://bibliotekanauki.pl/articles/97849.pdf
    Data publikacji:
    2014
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    metallic airframe structure
    full scale fatigue tests
    Opis:
    The PZL M28’s service life is determined based on the fatigue tests of the wing and wing loadscarry-through structure. During the fatigue test, the first occurrence of significance was the appearance of a in the area of the wing where loads are applied from the strut. It was demonstrated during further activities that repairs of the wing and other basic assemblies enabled, when performed at an appropriate time, the airplane’s service life to be significantly increase. In the case of each design change implemented in the airframe subject to the fatigue testing, a stress analysis of the airframe was required in order to check if local changes, i.e. local repairs, did not affect the stress level in other tested areas. This helped to avoid significant stress redistribution in the airframe after the repair, so the fatigue test was still valid for all areas of interest.
    Źródło:
    Fatigue of Aircraft Structures; 2014, 6; 107-112
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Prediction of Fatigue Cracks Using Gamma Function
    Autorzy:
    Moussouni, Abdelfetah
    Benachour, Mustapha
    Benachour, Nadjia
    Powiązania:
    https://bibliotekanauki.pl/articles/24201171.pdf
    Data publikacji:
    2022
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    fatigue crack growth
    stress ratio
    fatigue
    2024 T351 Al-alloy
    Gamma function
    Opis:
    In the present study it has been endeavored to estimate the fatigue crack propagation in V-notch Charpy specimens of 2024 T351 Al-alloy. For this purpose, a new application of fatigue crack growth (FCG) is developed based on the “Gamma function.” Experimental fatigue tests are conducted for stress ratios from 0.1 to 0.5 under constant amplitude loading. The empiric model depends principally on physical parameters and materials’ properties in non-dimensional form. Deviation percentage, prediction ratio, and band error are used for validation of the performance of the fatigue life. The results determined from Gamma application are in good agreement with experimental FCG rates and those obtained from using Paris law.
    Źródło:
    Fatigue of Aircraft Structures; 2022, 14; 29--46
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Stress Intensity Factor Analysis and Fatigue Behavior of A Crack in The Residual Stress Field of Welding
    Autorzy:
    Terada, H.
    Powiązania:
    https://bibliotekanauki.pl/articles/97909.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    stress intensity factor analysis
    crack
    residual stress field
    butt weld
    stress redistribution
    fatigue crack
    crack propagation
    Opis:
    This paper deals with the behavior of a crack in the residual stress field induced by the butt weld in a wide plate. It is known that the distribution form of residual stress has similarities regardless of the welding process, although the size and the magnitude of the residual stress depend largely on the welding process. Stress intensity factor and stress redistribution induced by the crack extension were calculated for a crack with arbitrary length and location. The stress redistributions caused by crack extension obtained by the present analysis showed good agreement with the experimental data. Fatigue crack propagation behavior in the residual stress field reported by Glinka was also examined from ΔK point of view. The effect of residual stress on the fatigue crack propagation rate is considered to be the effect of varying mean stress. It was shown that fatigue crack propagation rate is estimated by the following equation with reasonable accuracy.
    da/dn=CΔFα(1+ σ0/Δσ Fres)
    In the above equation, material constants C and α of Paris’s law are experimentally obtained by using specimens without the weld joint.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 5-15
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Determination of Stress Values in the Surface Layer of Inconel 718 Samples Dedicated to Fatigue Tests
    Autorzy:
    Gadalińska, Elżbieta
    Michałowski, Andrzej
    Czarnewicz, Sławomir
    Powiązania:
    https://bibliotekanauki.pl/articles/97839.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    turning
    grinding
    X-ray diffraction
    stress analysis
    Inconel 718
    Opis:
    This work deals with the problem of X-ray stress determination on the samples dedicated to fatigue tests. A number of research studies point out the fact that the processing of hard, difficult to machine materials like nickel superalloys, reveals more than one trend of residual stress versus working parameters of behaviour (Lavella and Berruti, 2010). Many papers have shown that the residual stresses are dependent on a combination of a number of factors. When the above is taken into account simultaneously with the requirements of the internal General Electric specification for the fatigue tests samples preparation (Metallic test specimen preparation, low stress, 2017) the problem of turning and grinding parameters gathers significance. It is well known that the quality of the surface layer, produced during machining, is of vital importance for the fatigue life specially for the components of aircraft produced form nickel superalloys e.g. Inconel 718 (Kortabarri et al., 2011). That is why the surface layer’s properties are described in detail by the standards. The aim of the work is to determine one of the most influential features from the point of view of fatigue life, i.e. the stress state on the surface layer with one non-destructive method - the diffraction analysis.
    Źródło:
    Fatigue of Aircraft Structures; 2019, 11; 78-86
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The Elaboration of the Method of Fatigue Testing of the Rotor of the Mosups Plane Propulsion System
    Autorzy:
    Głowacki, D.
    Rodzewicz, M.
    Powiązania:
    https://bibliotekanauki.pl/articles/97933.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    UAV
    propulsion system
    stress analysis
    fatigue tests
    Opis:
    This paper concerns fatigue testing of the rotor of the propulsion system for the MOSUPS – an unmanned aircraft designed in a joint wing configuration, and equipped with a ducted propeller. The work presents the analysis of the stresses and deformations of the rotor structure as well as the form of the loading cycle. The aim of the paper is to introduce the concept of a simplified method of fatigue testing of multi-blade rotors. With the sophisticated geometry of the rotor in mind – the authors applied the FEM tools and implemented the ANSYS and nCode programs. The prototype of the fatigue stand built by the authors is also presented in the paper.
    Źródło:
    Fatigue of Aircraft Structures; 2016, 8; 97-103
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Local Phenomena During Riveting Process
    Autorzy:
    Kaniowski, J.
    Wronicz, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/97899.pdf
    Data publikacji:
    2013
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    riveting
    fatigue
    strain gauge
    FE model
    residual stress
    airframes
    Opis:
    The paper presents experimental and numerical study of the local phenomena during the riveting process. It is commonly accepted that technological factors of the riveting process has a strong influence on the fatigue life of riveted joints. The authors analysed the papers concerned the experimental researches of the riveting force influence on fatigue life. The magnitude of the life increase caused by the riveting force increase suggests the authors that this is not only the result of beneficial stress system but the change of the joint formation mechanism has taken place. This was an inspiration to undertake more detailed researches of the riveting process. The strain progress during the riveting process has been experimentally investigated for four types of aluminium rivets used in airframes. Measurements confirm very high strains near the driven head. For some types of rivets the reversal strain signal has been recorded. Several FE model has been use to investigate the riveting process. The axisymmetric and solid models were used. The agreement of experimental and numerical results in some cases were good, in other cases the numerical models demand further development. In any calculations, the reversal strain effect has not been obtained, This suggest that it is result of the phenomenon which has not been taken into account in numerical modelling. The working hypothesis has been assumed that during the riveting process adhesive joints (called cold welding) were formed and destroyed during the process, what was the reason of the observed reversal strain signal. The authors are going to continue this investigation.
    Źródło:
    Fatigue of Aircraft Structures; 2013, 5; 66-78
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Comparison of Residual Stress State on Sheets Faying Surface after Standard and NACA Riveting-Numerical Approach
    Autorzy:
    Wronicz, W.
    Powiązania:
    https://bibliotekanauki.pl/articles/97853.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    NACA riveting
    fatigue
    FE
    joints
    Opis:
    One crucial characteristic of the aircraft structure are fatigue properties and rivets are usually critical areas in metal airframes due to fatigue cracks nucleation. According to literature, the NACA riveting method offers a huge increase in fatigue life of riveted lap joints. This paper presents FE simulations of quasi-static riveting on a press for standard countersunk rivets and the NACA riveting in two configurations: with a normal brazier rivet and a brazier rivet with a compensator. The analyzed configurations have been compared based on the stress courses on the sheets faying surfaces after riveting process. Due to a lack of data, the rivet length and the squeezing force value were assumed for NACA riveting based on FE simulations. The results indicated beneficial influence of the NACA riveting in the outer sheet (with a countersunk) and disadvantageous influence in the inner sheet. This effect was stronger in the case of the rivet with a compensator.
    Źródło:
    Fatigue of Aircraft Structures; 2016, 8; 116-126
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Preparation of Samples used in Fatigue Testing of Aircraft Materials
    Autorzy:
    Manaj, W.
    Wronicz, W.
    Michałowski, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/98020.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    mechanical processing
    stress measurement
    X-ray diffraction
    Opis:
    The application of a new type of alloy requires the evaluation of its properties, which is typically achieved with destructive methods. For this purpose, among others, static and fatigue mechanical tests are performed. Tests are performed on standardized samples in a way which reflects the level of stress occurring in real elements. These tests should limit random errors associated with sample preparation. For this reason the proper preparation of samples is crucial, not only in terms of their geometric dimensions but also in terms of the residual stress level. A sample preparation process was developed, involving checking samples’ surface for cracks, scratches, roughness, and the state of stress. The measurements are performed with nondestructive methods so as not to affect the proceeding research. In this study, the residual stress and features of a mechanically prepared surface were characterized. The specimens were subjected to various surface finishes mainly, lathe turning and grinding surface conditions. The effects of residual surface stress (measured by XRD) were studied after machining and polishing.
    Źródło:
    Fatigue of Aircraft Structures; 2015, 7; 66-68
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Impact of Manufacturing Tolerances on Stress in a Turbine Blade Fir-Tree Root
    Autorzy:
    Moneta, Grzegorz
    Jachimowicz, Jerzy
    Powiązania:
    https://bibliotekanauki.pl/articles/2105140.pdf
    Data publikacji:
    2020
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    fir-tree root
    turbine
    lock
    blade
    disk
    manufacturing tolerances
    Monte-Carlo simulations
    Six Sigma
    Low Cycle Fatigue
    Design of Experiment
    Opis:
    Low Cycle Fatigue (LCF) is one of most common mechanisms behind turbine blade failures. The reason is high stress concentration in notch areas, like fir-tree root groves, which can cause cyclic stress beyond the safe threshold. The stress levels strictly depend on the manufacturing accuracy of the fir-tree lock (for both fitted together: blade root and disk groove). The probabilistic study aimed at determination of stress was performed using Finite Element Method (FEM) simulation on a population of 1000 turbine models (disk + blades +friction dampers), where fir-tree lock dimensions were sampled according to the normal distribution, within limits specified in the documentation. The studies were performed for different manufacturing quality levels: 3-Sigma, 6-Sigma and 3-Sigma with tolerance ranges reduced twice. Based on the results, the probabilistic distributions, probabilities and expected ranges of values could be determined for: material plastification, stress, strain, LCF lifetime, etc. The study has shown how each tooth of the root is loaded and how wide a stress range should be expected in each groove. That gives information on how the definition of tolerances should be modified to make the construction more optimal, more robust, with lower likelihood of damage, taking into account the cost-quality balance. It also shows how the Six Sigma philosophy can improve the safety of the construction, its repeatability and predictability. Additionally, the presented numerical study is a few orders of magnitude more cost- and time-effective than experiment.
    Źródło:
    Fatigue of Aircraft Structures; 2020, 12; 92--101
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-10 z 10

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