Email this article Analysis of Geared Turbofan Engine Transmission on Operational and Breakdown Overloads
- Authors: Temis M.J1,2, Egorov A.M1
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Affiliations:
- Central Institute of Aviation Motors
- Bauman Moscow State Technical University
- Issue: Vol 9, No 3-4 (2015)
- Pages: 26-37
- Section: Articles
- URL: https://journals.rcsi.science/2074-0530/article/view/67095
- DOI: https://doi.org/10.17816/2074-0530-67095
- ID: 67095
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Abstract
Investigation of double-circuit geared turbofan engine (GTF) transmission dynamics for flight cycle loads was carried out. Flight cycle loads taking into account overloads at evolutions. Comparative analysis for response of engine models without load reduction device and with load reduction device fracture on fan blade fracture is performed. As basic GTF assembly the assembly presented in most of opensources is taken. For investigation the beam and solid models were developed. Both models contain of fan rotor, gear and low pressure rotor. Special finite element are used in beam model for simulation of stiffness characteristics of complex geometry rotor elements. Stiffness characteristics of beam model are verified with assistance of solid model.
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##article.viewOnOriginalSite##About the authors
M. J Temis
Central Institute of Aviation Motors; Bauman Moscow State Technical University
Email: mikhail.temis@gmail.com
PhD.; 8 (495) 361-64-82
A. M Egorov
Central Institute of Aviation Motors
Email: tejoum@ciam.ru
8 (495) 361-64-82
References
- Riegler C., Bichlmaier C. The geared turbofan technology opportunities, challenges, and readi- ness status // Proc. of 1st CEAS European Air and Space Conference, Berlin, Germany, September 2007.
- Gmelin T.C., Huttig G., Lehmann O. Zusammenfassende Darstellung der Effizienzpotenziale bei Flugzeugen unter besonderer Berucksichtigung der aktuellen Triebwerkstechnik sowie der absehbaren mittelfristigen Entwicklungen.
- Kurzke J. Fundamental differences between conventional and geared turbofans // Proc. of ASME Turbo Expo 2009: Power for Land, Sea and Air. June 8-12, 2009, Orlando, Florida, USA.
- Dewanji D., Arvind Rao G., van Buijtenen J. Feasibility study of some novel concepts for high bypass ratio turbofan engines // Proc. of ASME Turbo Expo 2009: Power for Land, Sea and Air. June 8-12, 2009, Orlando, Florida, USA.
- Kyprianidis K.G., Rolt A.M., Grönstedt T. Multi-disciplinary analysis of a geared fan intercooled core aeroengine // Proc. of ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. June 3-7, 2013, San Antonio, Texas, USA.
- United States Patent № 8,935,913 B2 «Geared turbofan gas turbine engine architecture». Jan. 20, 2015.
- United States Patent № 2012/0251306 A1 «Fan rotor support». Oct. 04, 2012.
- United States Patent № 7,694,505 B2 «Gas turbine engine assembly and method of assembling same». Apr. 13, 2010.
- United States Patent № 6,494,032 B2 «Ducted fan gas turbine engine with frangible connection». Dec. 17, 2002.
- United States Patent № 8,430,622 «Turbofan gas turbine engine». Apr. 30, 2013.
- United States Patent № 4,375,906 «System for supporting a rotor in conditions of accidental dynamic imbalance». Mar. 08, 1983.
- Подшипники качения. Расчет, проектирование и обслуживание опор / Под ред. Л.Я. Переля и А.А. Филатова. Справочник. М.: Машиностроение, 1992.
- United States Patent № 8,790,075 B2 «Gas turbine engine neared architecture axial retention arrangement». Jul. 29, 2014.
- Wilkes J.C., Dyck B.J. The numerical and experimental characteristics of multi-mode dryfriction whip and whirl // Proc. of ASME Turbo Expo 2009: Power for Land, Sea and Air. June 8-12, 2009, Orlando, Florida, USA.
