Insight Into Vibration Sources in Turbines

• Autorzy: Moneta Grzegorz , Jachimowicz Jerzy , Pietrzakowski Marek , Doligalski Adam , Szwedowicz Jarosław

Identyfikatory

DOI

10.2478/fas-2021-0005

• Języki publikacji: EN

Abstrakty

EN

Despite of nearly 100 years of turbine engine development and design, blade vibrations remain a great engineering challenge. The rotating turbine blades’ vibrations lead to cyclic oscillations, which result in alternating stress and strain in harsh environments of high temperature and pressure. In modern aeroengines, high hot flow velocities might generate erosion and corrosion pitting on the metal surfaces, that leverage remarkably mean stresses. The combination of both mean and alternating stresses can lead to unexpected engine failures, especially under resonance conditions. Then, alternating stress amplitudes can exceed the safety endurance limit, what accelerates the high cyclic fatigue leading quickly to catastrophic failure of the blade. Concerning the existing state-of-the-art and new market demands, this paper revises forced vibrations with respect to excitation mechanisms related to three design levels: (i) a component like the blade design, (ii) turbine stage design consisting of vanes and blades and (iii) a system design of a combustor and turbine. This work reviews the best practices for preventing the crotating turbine and compressor blades from High Cyclic Fatigue in the design process. Finally, an engine commissioning is briefly weighed up all the pros and cons to the experimental validations and needed measuring equipment.

Słowa kluczowe

EN

vibrations; blade; gas turbine; turbine engine; strain gauge; tip timing; Additive Manufacturing

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2021
• Tom: Iss. 13
• Strony: 40--53
• Opis fizyczny: Bibliogr. 18 poz., rys., tab., wykr.

Twórcy

autor

Moneta Grzegorz

• Łukasiewicz Research Network - Institute of Aviation, Al. Krakowska 110/114, 02-256 Warsaw

• https://orcid.org/0000-0003-3899-1957

autor

Jachimowicz Jerzy

• Military University of Technology, gen. Sylwestra Kaliskiego 2, 00-908 Warsaw

• https://orcid.org/0000-0002-0486-6448

autor

Pietrzakowski Marek

• Warsaw University of Technology, plac Politechniki 1, 00-661 Warsaw

• https://orcid.org/0000-0001-6192-4272

autor

Doligalski Adam

• Łukasiewicz Research Network - Institute of Aviation, Al. Krakowska 110/114, 02-256 Warsaw

• https://orcid.org/0000-0002-4066-0850

autor

Szwedowicz Jarosław

• Zurich University of Applied Sciences, Technikumstrasse 9, 8400 Winterthur

• https://orcid.org/0000-0003-0908-4346

Bibliografia

• [1] Beretta-Müller, A. & Szwedowicz, J. (2015). Blade Resonant Forced Response Excited by Combustor Acoustic Eigenmodes. In: Proceedings of ASME Turbo Expo: Turbine Technical Conference and Exposition, June 15 - 19, 2015, Montreal, Quebec, Canada.
• [2] Corral, R. (2012). Bladed Disks: Flutter, Structural Design of Aircraft Engines, RTO-AVT-207-06, 25 January, Belgium.
• [3] Dodds, J., and Vahdati, M. (May 1, 2015). Rotating Stall Observations in a High Speed Compressor-Part II: Numerical Study. ASME. J. Turbomach. May 2015, Vol. 137, No. 5, 051003. DOI: 10.1115/1.4028558.
• [4] El-Aini, Y., et al. (1997). High Cycle Fatigue of Turbomachinery Components-Industry Perspective, In: 33 rd Joint Propulsion Conference. DOI: 10.2514/6.1997-3365.
• [5] Han, Y., Xiao, B. & Mignolet, M. P. (2007). Expedient Estimation of the Maximum Amplification Factor in Damped Mistuned Bladed Disks, ASME Paper No. GT2007-27353, In: Proceedings of ASME Turbo Expo, May 14-15, 2007, Montreal, Canada.
• [6] Hulme, J. C., Fiebiger, W., S. & Szwedowicz, J. (2015). Axial Compressor Blade Failure Design Mitigation and Its Validation, ASME Paper No. GT2015-43312, ISBN: 978-0-7918-5679-6, Proceedings of ASME Turbo Expo, June 15-19, 2015, Montreal, Canada.
• [7] Kenyon, J.A, & Griffin, J.H. (2001). Forced Response of Turbine Engine Bladed Disks and Sensitivity to Harmonic Mistuning. In: Proceedings of the ASME Turbo Expo: Power for Land, Sea, and Air. Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award. New Orleans, Louisiana, USA. June 4-7, 2001. V004T03A037. ASME. DOI: 10.1115/2001-GT-0274.
• [8] Kurnik, W. (1997). Bifurkacje dywergentne i oscylacyjne, WNT, Warszawa, ISBN 83-204-2221-3.
• [9] Moneta, G. (2019). Damping Optimization of Turbine Blade Vibration, Ph.D. Dissertation, Warsaw University of Technology.
• [10] Moneta, G. & Jachimowicz, J. (2020). Impact of Manufacturing Tolerances on Stress in a Turbine Blade Fir-Tree Root, Fatigue of Aircraft Structures, Vol. 2020, No. 12, 92-101, DOI: 10.2478/fas-2020-0009.
• [11] Moneta, G., Jachimowicz, J. & Osiński, J. (2014). Influence of Manufacturing Tolerances on Vibration Frequencies of Turbine Blade, Machine Dynamics Research, Vol. 38, No 1, 105-118.
• [12] Peter, J. (1999). The History of Aircraft Gas Turbine Engine Development in the United States: A Tradition of Excellence, ASME IGTI publication.
• [13] Schneider C.M., et. al. (2013). On the Unsteady Formation of Secondary Flow Inside a Rotating Turbine Blade Passage. ASME. J. Turbomach., Vol. 136, No. 6, 061004-061004-10. DOI:10.1115/1.4025582.
• [14] Srinivasan, A.V. (1997). Flutter and Resonant Vibration Characteristics of Engine Blades. In: Proceedings of the ASME International Gas Turbine and Aeroengine Congress and Exhibition. Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award. Orlando, Florida, USA. June 2-5, 1997. V004T17A001. ASME. DOI: 10.1115/97-GT-533.
• [15] Szwedowicz, J. (2008). High Cyclic Fatigue, Structural Design of Aircraft Engines: Key Objectives & Techniques. Lecture Series Monographs of von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Genèse, Belgium, ISSN: 0377-8312, ISBN: 978-2-930389-8-2-6, pp. 49.
• [16] Szwedowicz, J. (2010, April). 30-year anniversary of friction damper technology in turbine blades. Mechanical Engineering-CIME, Vol. 132, No. 4, 54+. https://link.gale.com/apps/doc/A223657423/AONE?u=googlescholar&sid=bookmark-AONE&xid=d990d10d.
• [17] Szwedowicz, J., et al. (April 3, 2008). Scaling Concept for Axial Turbine Stages With Loosely Assembled Friction Bolts: The Linear Dynamic Assessment. ASME. J. Eng. Gas Turbines Power. May 2008; Vol. 130, No. 3, 032504. DOI: 10.1115/1.2838995.
• [18] Whitehead, D. S. (1988). The Maximum Factor by Which Forced Vibration of Blades Can Increase Due to Mistuning, ASME J. Eng. Gas Turbines Power, Vol. 120, No. 1, 115-119.

Uwagi

Opracowanie rekordu ze środków MEiN, umowa nr SONP/SP/546092/2022 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2022-2023).