Informacja

Drogi użytkowniku, aplikacja do prawidłowego działania wymaga obsługi JavaScript. Proszę włącz obsługę JavaScript w Twojej przeglądarce.

English (EN)·Polski (PL)·Yкраїнський (UK)
Przejdź do strony domowej biblioteki Centralna Biblioteka Wojskowa Link otwiera się w nowym oknie Logo biblioteki Prolib Integro - strona głównaCentralna Biblioteka Wojskowa

Wyszukujesz frazę "Zasada, A.A." wg kryterium: Autor

  Lista filtrów
Wyrównaj
    Wyświetlanie 1-5 z 5
    Tytuł:
    Degradation of the gas turbine blade coating and its influence on the microstructure state of the superalloy
    Autorzy:
    Błachnio, J.
    Kułaszka, A.
    Zasada, D.
    Powiązania:
    https://bibliotekanauki.pl/articles/244112.pdf
    Data publikacji:
    2015
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    turbine
    blade
    heat-resistant coating
    technical condition
    Opis:
    The technical condition of the blades has a critical influence on the reliability and life span of a gas turbine and an engine into which it is built in. The main causes of blade damage are overheating, creeping, thermal fatigue, high temperature corrosion, etc. It is often caused by adverse operational conditions or manufacturing defect, e.g. using insufficiently durable types of heat-resistant protective coatings or applied in an improper manner on the blade material. Reaction of coatings and blade material to mechanical and thermal loads depends mainly on the operating temperature of the turbine. Selection of a protective coating and material to manufacture a blade with an assumed strength must take into account its mechanical and thermal properties at maximum aerofoil temperature. The article presents characteristic forms of operational damages to the gas turbine blades of a turbojet aero engine. Distinguished were operational factors and their influence on the technical condition of coatings during the engine operation period. An influence of excess exhaust gas temperature on the condition of the heat-resistant blade layer was shown. Shown were also results of morphology tests of coating degradation types. Results of micro-structure tests of the blade superalloy after damage to the heat-resistant coating were also presented.
    Źródło:
    Journal of KONES; 2015, 22, 2; 17-24
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Badania nad zastosowaniem zgrzewania wybuchowego do uzyskania bimetalicznych blach z udziałem staliwa Hadfielda
    Research into the application of explosive welding of metal sheets with Hadfield’s steel (Mangalloy)
    Autorzy:
    Kosturek, R.
    Maranda, A.
    Senderowski, C.
    Zasada, D.
    Powiązania:
    https://bibliotekanauki.pl/articles/92713.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    zgrzewanie wybuchowe
    prędkość detonacji
    staliwo Hadfielda
    explosive welding
    detonation velocity
    Hadfield cast-steel
    Opis:
    Celem pracy było otrzymanie zgrzewanych wybuchowo blach stalowych 22G2A i 15HM z odpornym na ścieranie staliwem Hadfielda za pomocą amonowo-saletrzanych materiałów wybuchowych. Analizowano właściwości strukturalne oraz stopień umocnienia utworzonego złącza, określając jednocześnie odporność na zużycie erozyjne staliwa Hadfielda w stanie po zgrzaniu wybuchowym, w porównaniu do stali 65G stosowanej na elementy koła bijakowego w kotłach pyłowych.
    The purpose of this work was to weld steel sheets with sheets made of Hadfield steel (mangalloy) using industrial explosives. The degree of strengthening of the Hadfield steel layer and the structure of the bond between the welded steels, was examined. The results of erosive wear testing between steel 65G (used in hammer mills) and welded Hadfield steel has been compared.
    Źródło:
    Materiały Wysokoenergetyczne; 2016, T. 8; 91-102
    2083-0165
    Pojawia się w:
    Materiały Wysokoenergetyczne
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    The assessment of changes in the microstructure of a gas turbine blade with a non - destructive thermographic method
    Autorzy:
    Kułaszka, A.
    Błachnio, J.
    Zasada, D.
    Jóźwik, P.
    Powiązania:
    https://bibliotekanauki.pl/articles/246861.pdf
    Data publikacji:
    2012
    Wydawca:
    Instytut Techniczny Wojsk Lotniczych
    Tematy:
    gas turbine
    blade
    pulsed thermography diagnosing
    health/maintenance status
    Opis:
    Diagnostic methods applied nowadays to examine condition of a gas turbine blade have been discussed in the Introduction section. What follows in the body of the paper is presentation of findings on the assessment of changes in the microstructure of a gas turbine blade with a non-destructive thermographic method. A laboratory experiment performed on new turbine rotor blades made of the EI 867WD alloy has been described. The experiment consisted in holding the blades at different temperatures in the exhaust-gas environment produced by an aircraft engine supplied with jet fuel. The pulsed thermography method has been used to determine and analyse the temperature distribution upon the examined area while cooling-down after the earlier uniform warming it up with a heat pulse. Diffusion and effusion of heat in the alloy have been examined. Both phenomena are determined with thermal properties and other physical properties such as size, shape, weight, structure, chemical composition, thickness of the protective coating of the blade. Examination of the microstructure of the blade material has shown the increased thickness of the coating, grain size, and in particular disadvantageous modification in the strengthening gamma' phase against temperature. Finding the relationship between parameters of thermal responses of blade materials to heat pulse against the average size of precipitates of the gamma' phase and thickness of the aluminium protective coating enables inferences on changes in the blade material's condition. With this relationship as the basis and knowing permissible changes to the microstructure one can determine the 'fit-for-use' and 'unfit-for-use' (i.e. serviceable and unserviceable) conditions of the blades. Assuming the material criterion, i.e. some disadvantageous change in the morphology of precipitates of the gamma' phase in the EI 867WD alloy under examination, the 'fit-for-use' (serviceability) thresholds for blades affected with different temperatures have been defined.
    Źródło:
    Journal of KONES; 2012, 19, 2; 271-281
    1231-4005
    2354-0133
    Pojawia się w:
    Journal of KONES
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    ZL-130TCII Fracture Markers Solution for Full-Scale Fatigue Test
    Autorzy:
    Kłysz, S.
    Lisiecki, J.
    Zasada, D.
    Gmurczyk, G.
    Leski, A.
    Powiązania:
    https://bibliotekanauki.pl/articles/97988.pdf
    Data publikacji:
    2011
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    full scale fatigue test
    fracture surface marking
    quantitative fractography
    Opis:
    In the context of PZL-130TC-II full-scale fatigue test, several strategies of fatigue loadings that create fracture surface markings were considered. One block of spectrum is made of 200 flights. By reordering those flights, a block which should create a fracture marker, was developed. It was very important that reordering the load spectrum or adding overloads or underloads did not change spectrum severity. Pilot tests of aluminium alloys specimens were carried out to finalise appropriate marker intervals before commencing full-scale tests. The experiment was conducted with the MTS machine with 810.23 system. The results and conclusions are presented within this paper.
    Źródło:
    Fatigue of Aircraft Structures; 2011, 3; 22-27
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Introduction of Fatigue Markers in Full Scale Fatigue Test of an Aircraft Structure
    Autorzy:
    Leski, A.
    Kłysz, S.
    Lisiecki, J.
    Gmurczyk, G.
    Reymer, P.
    Bochenek, D.
    Zasada, D.
    Powiązania:
    https://bibliotekanauki.pl/articles/97777.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
    Tematy:
    full scale fatigue test
    fatigue markers
    load block rearrangement
    Opis:
    Air Force Institute of Technology participates in the service life assessment programme SEWST. The aim of this programme, funded by the Polish Ministry of Defense, is to modify the operation system of PZL-130 "Orlik" TC-II turbo propelled trainer aircraft. The structural part of the programme is focused on the Full Scale Fatigue Test of the whole airframe to be conducted at the VZLU in the Czech Republic. The load spectrum for the test was developed by the AFIT based on the flight test results. The basic load block represents 200 simulated flight hours and consists of 194 flights showing different levels of severity. At the end of the Full Scale Fatigue Test a teardown inspection is planned during which it would be most beneficial to be able to determine crack propagation rate by means of a crack surface inspection. Markers are usually visible on most fatigue crack surfaces, however they occur randomly therefore it is almost impossible to conclude anything about the crack history. Since the preliminary load block consisted of separate flights (flight loads together with landing and taxing loads) showing significantly different levels of severity, the easiest way to modify the load block was to change the order of flights within the block. Hence a pilot programme was started at the AFIT which was focused on the determination of the influence of flight sequence on crack appearance. Several load blocks were determined using various techniques of rearranging the order of flights within the preliminary load spectrum. This approach ensured the preservation of the initial severity of the load block and simultaneously enabled a significant increase in the probability of the markers occurrence introducing neither artificial underloads nor overloads that would most probably affect the crack propagation rate. Fatigue crack surfaces were inspected using Scanning Electron Microscope. As a result of the investigations a series of images were obtained showing the specimen microstructure with visible markers arranged in the desired sequences. Based on the obtained pictures the most promising load block arrangements were chosen for the Full Scale Fatigue Test.
    Źródło:
    Fatigue of Aircraft Structures; 2012, 4; 29-37
    2081-7738
    2300-7591
    Pojawia się w:
    Fatigue of Aircraft Structures
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-5 z 5

      Ta witryna wykorzystuje pliki cookies do przechowywania informacji na Twoim komputerze. Pliki cookies stosujemy w celu świadczenia usług na najwyższym poziomie, w tym w sposób dostosowany do indywidualnych potrzeb. Korzystanie z witryny bez zmiany ustawień dotyczących cookies oznacza, że będą one zamieszczane w Twoim komputerze. W każdym momencie możesz dokonać zmiany ustawień dotyczących cookies