Impact of the vibration amplitude on the fatigue life of compressor blades with mechanical defects

• Autorzy: Witek L. , Bednarz A.

Identyfikatory

DOI

10.5604/12314005.1216501

• Języki publikacji: EN

Abstrakty

EN

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.

Słowa kluczowe

EN

turbine engine; compressor blade; v-notch; resonant vibrations; fatigue life

• 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: 2016
• Tom: Vol. 23, No. 3
• Strony: 571--576
• Opis fizyczny: Bibliogr. 13 poz., rys.

Twórcy

autor

Witek L.

• Rzeszow University of Technology, Department of Aircraft and Aircraft Engines Powstancow Warszawy 8, 35-959 Rzeszow, Poland tel.: [phone]

autor

Bednarz A.

• Rzeszow University of Technology, Department of Aircraft and Aircraft Engines Powstancow Warszawy 8, 35-959 Rzeszow, Poland tel.: [phone]

Bibliografia

• [1] Carter, T. J., Common failures in gas turbine blades, Engineering Failure Analysis, 12, pp. 237-247, 2005.
• [2] Chen, X., Foreign Object Damage on the leading Edge of a Thin Blade, Mechanics of Material, 37, pp. 447-457, 2005.
• [3] Cowles, B. A., High cycle fatigue in aircraft gas turbines – an industry perspective, International Journal of Fracture, 80, pp. 147-163, 1996.
• [4] Jahangiri, M. R., Fallah, A. A., Ghiasipour, A., Cement kiln dust induced corrosion fatigue damage of gas turbine compressor blades – A failure analysis, Materials and Design, 62, pp. 288-295, 2014.
• [5] Kermanpur, A., Sepehri, A. H., Ziaei-Rad, S., et al., Failure analysis of Ti6Al4V gas turbine compressor blades, Engineering Failure Analysis, 15, pp. 1052-1064, 2008.
• [6] Lourenço, N. J., Graça, M. L. A., Franco, L. A. L., Silva, O. M. M, Fatigue failure of a compressor blade, Engineering Failure Analysis, 15, pp. 1150-1154, 2008.
• [7] Pages, H. J., Wicks, B. J., Antoniou, R. A., An investigation of fatigue failures of turbine blades in a gas turbine engine by mechanical analysis, Engineering Failure Analysis, 9, pp. 201-211, 2002.
• [8] Poursaeidi, E., Salavatian, M., Failure analysis of generator rotor fan blades, Engineering Failure Analisys, 14, pp. 851-860, 2007.
• [9] Szczepanik, R., Analysis of 1st stage compressor rotor blade stress and vibration amplitudes in one-pass jet engine, Journal of KONES, No. 20, pp. 441-450, 2013.
• [10] Szczepanik, R., Investigation of the dynamic properties of engine fan titanium rotor blades in a high manoeuvrability aircraft in FOD aspect, Journal of KONES, No. 20, pp. 371-376, 2013.
• [11] Witek, L., Simulation of crack growth in the compressor blade subjected to resonant vibration using hybrid method, Engineering Failure Analysis, 49, pp. 57-66, 2015.
• [12] Witek, L., Crack propagation analysis of mechanically damaged compressor blades subjected to high cycle fatigue, Engineering Failure Analysis, 18, pp. 1223-1232, 2011.
• [13] Witek, L., Bednarz, A., Stachowicz, F., Fatigue analysis of compressor blade with simulated foreign object damage, Engineering Failure Analysis, 58, pp. 229-237, 2015.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.