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Wyszukujesz frazę "health/maintenance status" wg kryterium: Temat


Wyświetlanie 1-2 z 2
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:
Non-uniformity of the combustor exit flow temperature in front of the gas turbine
Autorzy:
Błachnio, J.
Pawlak, W.
Powiązania:
https://bibliotekanauki.pl/articles/386460.pdf
Data publikacji:
2014
Wydawca:
Politechnika Białostocka. Oficyna Wydawnicza Politechniki Białostockiej
Tematy:
gas turbine
blade
simulation model
working agent temperature field
health/maintenance status
turbina gazowa
łopatka turbiny
model symulacyjny
warunki techniczne
Opis:
Various types of damages to gas-turbine components, in particular to turbine blades, may occur in the course of gas turbine operation. The paper has been intended to discuss different forms of damages to the blades due to non-uniformity of the exit flow temperature. It has been shown that the overheating of blade material and thermal fatigue are the most common reasons for these damages. The paper presents results from numerical experiments with use of the computer model of the aero jet engine designed for simulations. The model has been purposefully modified to take account of the assumed non-homogeneity of the temperature field within the working agent at the turbine intake. It turned out that such non-homogeneity substantially affects dynamic and static properties of the engine considered as an object of control since it leads to a lag of the acceleration time and to increase in fuel consumption. The summarized simulation results demonstrate that the foregoing properties of a jet engine are subject to considerable deterioration in pace with gradual increase of the assumed non-homogeneity of the temperature field. The simulations made it possible to find out that variations of the temperature field nonhomogeneity within the working agent at the turbine intake lead to huge fluctuation of the turbine rpm for the idle run.
Źródło:
Acta Mechanica et Automatica; 2014, 8, 4; 209-213
1898-4088
2300-5319
Pojawia się w:
Acta Mechanica et Automatica
Dostawca treści:
Biblioteka Nauki
Artykuł
    Wyświetlanie 1-2 z 2

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