Influence of Manufacturing Tolerances on Vibration Frequencies of Turbine Blade

• Autorzy: Moneta G. , Jachimowicz J. , Osiński J.
• Języki publikacji: EN

Abstrakty

EN

High Cycle Fatigue is one of most common mechanism of turbine blade failures. The reason are vibrations, which cause cyclic displacements and though that also variable stresses and strains. The most dangerous are excitation frequencies around resonances - that can cause failure in a very short time. About 70 years of jet engine development and more than one century of steam turbine history, was not enough to fully eliminate that problem. This paper shows an influence of manufacturing tolerances and accuracy of manufacturing technology on blade frequencies. Additionally, few methods for avoiding resonances have been presented and its implementation effort have been compared.

Słowa kluczowe

EN

vibrations; manufacturing tolerances; optimization; Monte Carlo simulation; Six Sigma; reverse engineering; 3D scanning

• Wydawca: Oficyna Wydawnicza Politechniki Warszawskiej
• Czasopismo: Machine Dynamics Research
• Rocznik: 2014
• Tom: Vol. 38, No. 1
• Strony: 105--118
• Opis fizyczny: Bibliogr. 9 poz., il., rys., tab., wykr.

Twórcy

autor

Moneta G.

• Alstom Power

autor

Jachimowicz J.

• Military University of Technology, Warsaw

autor

Osiński J.

• Institute of Machine Design Fundamentals, Warsaw University of Technology

Bibliografia

• [1] Jachimowicz J., Karliński W., Szachnowski W., 2000: Blade and Disc In-Lock Co-Operation - Selected Problems. Machine Dynamics Problems No. 4, Vol. 24, 2000. (s.71-86).
• [2] Peter, J., 1999: The History of Aircraft Gas Turbine Engine Development in the United States... A Tradition of Excellence, ASME IGTI publication, 1999.
• [3] Jachimowicz J. at al., 2010: Fretting phenomenon in Aircraft Structures - Original title in Polish Zjawisko frettingu w konstrukcjach lotniczych, Transactions o f the Institute of Aviation (Prace Instytutu Lotnictwa) Nr 206, 2010, pp. 36 - 58.
• [4] Rolls-Royce plc, 1996: The jet engine, Derby, England, 1996.
• [5] Hemberger D. et. al., 2012: Investigations on maximum amplitude amplification factor of real mistuned bladed structures, ASME Turbo Expo GT2012-68084.
• [6] Beck J.A. et al., 2012: Probabilistic mistuning assessment using nominal and geometry based mistuning methods, ASME Turbo Expo GT2012-68533.
• [7] Hall B. D., Gray L., 2011: Probabilistic high-cycle fatigue risk assessment of an integrally bladed rotor, ASME Turbo Expo GT2011-45151.
• [8] Arkhipov A. N., Krasnovskiy Y. E., Putchkov I. V., 2011: Probabilistic life assessment of turbine vanes, ASME Turbo Expo GT2011-45841.
• [9] Shuai W., Jianyao Y., 2010: Mistuning identification for integrally bladed disks based on the SNM technique, ASME Turbo Expo GT2010-22105.