Wszystkie pola: engine-compressor - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: The study on algorithm for identification the fatigue crack length of compressor blade based on amplitude-frequency resonant characteristics
Autorzy:: Lichoń, D.
Bednarz, A.
Powiązania:: https://bibliotekanauki.pl/articles/243684.pdf
Data publikacji:: 2017
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: fatigue failure
crack length
compressor blade
aircraft engine
failure identification algorithm
Opis:: The article is focused on building the algorithm for identification the fatigue crack length in the first stage of compressor blade of the helicopter PZL-10W turbo-shaft engine. The fatigue wear of compressor blade is a process in which the fatigue crack begins at the structural notch of the working part. For compressor blade, the crack starts at the leading edge and progress along the blade chord. Due to working conditions, the compressor blades are referred to as critical components. The helicopter rotor downwash can easily lift particles form the ground that may cause damages in the compressor section. Aircraft engines are designed so that the rotational speed of impeller remains below the resonant frequency. However, the pulsation of working medium or mechanical vibrations may cause temporary increase of vibration frequency. The appearance of structural notch combined with temporary increase of vibrations may initiate the fatigue failure. The works undertaken at the Department of Aircraft and Aircraft Engines, Rzeszow University of Technology provided a wide spectrum of research data of amplitude-frequency (A-F) characteristics of 1st stage of compressor blade. For different crack lengths, the fatigue tests of resonant frequency and asymmetry of A-F characteristics were acquired. The crack lengths were measured by fluorescent or infrared mapping method. The aim of the article is to develop the numerical method for identification of crack length of compressor blade basing on A-F characteristics. The studies on A-F characteristics in order to find correlations between crack length, resonant frequency and characteristics asymmetry were performed. The next step was to build the algorithm for identification the crack length when only A-F characteristic is known. The article contains the description of researches background, A-F characteristics unique features, algorithm detailed methods of work and sample use of algorithm in identification the crack length.
Źródło:: Journal of KONES; 2017, 24, 4; 157-164
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

Artykuł

Zmień widok

na półce

Skocz do pozycji: 2.

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

Zmień widok

na półce

Skocz do pozycji: 3.

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

Zmień widok

na półce

Skocz do pozycji: 4.

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

Zmień widok

na półce

Informacja

Wyszukujesz frazę "engine-compressor" wg kryterium: Wszystkie pola

Źródło danych

Dostawca treści

Kolekcja

Rok wydania

Wydawca

Temat

Autor

Typ dokumentu

Język