Influence of the cyclic hardening model on the results of the numerical analysis of fatigue life on example of the compressor blade

• Autorzy: Bednarz Arkadiusz

Identyfikatory

DOI

10.2478/kones-2019-0026

• Języki publikacji: EN

Abstrakty

EN

The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.

Słowa kluczowe

EN

fatigue life; compressor blade; aircraft engine; cyclic hardening; numerical analysis

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2019
• Tom: Vol. 26, No. 2
• Strony: 7--14
• Opis fizyczny: Bibliogr. 18 poz., rys.

Twórcy

autor

Bednarz Arkadiusz

• Rzeszow University of Technology, Department of Aircraft and Aircraft Engines Powstancow Warszawy 12, 35-959 Rzeszow, Poland tel. [phone]
• Lehigh University, Department of Mechanical Engineering and Mechanics 27 Memorial Dr W, Bethlehem, PA 18015, United States

Bibliografia

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Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).