Temat: fatigue fracture - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Numerical Simulation of Fatigue Fracture of the Turbine Disc
Autorzy:: Witek, L.
Powiązania:: https://bibliotekanauki.pl/articles/97889.pdf
Data publikacji:: 2012
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: aircraft engine
crack propagation analysis
finite element method
fatigue fracture
Opis:: This paper presents the results of the crack propagation analysis of an aircraft engine turbine disc. In the first part of the work the finite element method was used for calculation of the stress state and the stress intensity factor (SIF, K_I, K-factor) in the turbine disc with an embedded quarter-elliptical corner crack, subjected to low-cycle thermo-mechanical fatigue. To refine the K-factor calculation, specially degenerated finite elements were used. These elements provide stress singularity suitable for the linear-elastic material of the disc. The performed calculations yielded the stress intensity factor K_I for different crack sizes. Subsequently, ΔK parameter was determined as a difference of the K_I values calculated for the turbine’s speeds equal to 6373 and 14200 RPM. Based on the Paris-Erdogan equation and the obtained ΔK values, the fatigue crack growth plot for the turbine disc subjected to complex thermo-mechanical loads was determined.
Źródło:: Fatigue of Aircraft Structures; 2012, 4; 114-122
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

Artykuł

Skocz do pozycji: 2.

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

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