Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Investigating dynamics in the system consisting of a rotor and a casing of an aviation gas-turbine engine in the case of a fan blade-out

Published: 03.09.2018

Authors: Blinnik B.S., Myasnikov V.Yu., Ivanov I.I.

Published in issue: #8(80)/2018

DOI: 10.18698/2308-6033-2018-8-1797

Category: Mechanics | Chapter: Dynamics, Strength of Machines, Instruments, and Equipment

While the probability of a fan blade-out in a gas-turbine aviation engine is extremely low, it is not zero. A blade-out may lead to a catastrophe. Expensive testing is required to prove that there will be no dangerous consequences if the blade fails. This means that it is important to use suitable computational techniques to develop design steps to decrease the loads affecting force diagram nodes in the engine in the case of a blade-out. The paper presents an approach to solving the dynamic force problem in the system consisting of a rotor and a casing when a fan blade-out causes instantaneous unbalance. We state and solve this non-linear, non-steady-state problem, accounting for blade contact and compliance in the fan blade row, as well as for variations in the rotor angular frequency. We analyse the effect that certain engine component parameters have on the forces transmitted from the rotor to the casing system

[1] Examination of a failed Rolls-Royce RB211-524 turbofan engine. Boeing Commercial Aircraft Group, 747–436, G-BNLD. Technical Analysis Rep, 2002, no. 20/02. Available at: (accessed April 24, 2018).
[2] Aviatsionnye pravila [Aviation regulations]. Part 33. Normy letnoy godnosti dvigateley vozdushnykh sudov [Airworthiness standards for aircraft engines]. Moscow, Aviaizdat JSC Publ., 2012, 46 p.
[3] Regulations F.A.A. Part 33. Airworthiness Standards. Aircraft Engines. Washington, DC, Federal Aviation Administration, 1992, vol. 3.
[4] Certification Specification and Acceptable Means of Compliance for Engines (CS-E). Amendment 4. European Aviation Safety Agency. Available at: (accessed April 24, 2018).
[5] Shmotin Y., Gabov D., Ryabov A., Kukanov S., Rechkin V. Numerical analysis of aircraft engine fan blade-out. 42nd AIAA / ASME / SAE / ASEE Joint Propulsion Conference & Exhibit, 2006, p. 4620.
[6] Carney K.S., Lawrence C., Carney D.V. Aircraft engine blade-out dynamics. Seventh international LS-DYNA users conference. Livermore, CA, USA, Livermore Software Technology Corporation, 2002, pp. 14–17.
[7] Husband J.B. Developing an efficient FEM structural simulation of a fan blade off test in a turbofan jet engine. PhD thesis, University of Saskatchewan, Saskatoon, Saskatcheven, Canada, 2007.
[8] Sinha S.K., Dorbala S. Dynamic loads in the fan containment structure of a turbofan engine. Journal of Aerospace Engineering, 2009, vol. 22 (3), pp. 260–269.
[9] Muszynska A. Rotordynamics. Boca Raton, Fh., CRC press, 2005, 1128 p.
[10] Chelomey V.N., ed. Vibratsii v tekhnike [Vibrations in engineering]. In 6 vols. Vol. 3. Moscow, Mashinostroenie Publ., 1981, 544 p.
[11] Dimentberg F.M. Izgibnye kolebaniya vrashchayushchikhsya valov [Flexural vibrations in rotating shafts]. Moscow, Academy of Sciences of the USSR Publ., 1959, 248 p.
[12] Wang C., Zhang D., Ma Y., Liang Z., Hong J. Theoretical and experimental investigation on the sudden unbalance and rub-impact in rotor system caused by blade off. Mechanical Systems and Signal Processing, 2016, vol. 76, pp. 111–135.
[13] Ivanov I.I. Izvestiya vysshikh uchebnykh zavedeniy. Mashinostroenie — Proceedings of Higher Educational Institutions. Маchine Building, 2012, no. 10 (631), pp. 3–11.
[14] Bathe K.J. Finite element procedures. New Jersey, Prentice Hall, 2006, 1024 p.
[15] User reference manual for the MYSTRAN general purpose finite element structural analysis computer program. App. E. Derivation of the RBE3 element constraint equations. 2011, pp. 265–275. Available at: (accessed April 24, 2018).
[16] MSC Nastran. Quick reference guide. MSC Software, 2013, 3626 p.