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Prediction of Engine Mounting Loads in Transient Dynamic Response Under Blade Shedding Unbalance

[+] Author Affiliations
Mathieu Herran, Hervé Chalons

Turbomeca, Safran Group, Bordes, France

Daniel Nélias

Université de Lyon, Villeurbanne, France

Roland Ortiz

Onera, Lille, France

Paper No. GT2009-59615, pp. 837-846; 10 pages
  • ASME Turbo Expo 2009: Power for Land, Sea, and Air
  • Volume 6: Structures and Dynamics, Parts A and B
  • Orlando, Florida, USA, June 8–12, 2009
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4887-6 | eISBN: 978-0-7918-3849-5
  • Copyright © 2009 by ASME


For the TURBOMECA new generation turboshaft engines, overspeed electronic protection of the free turbine is coupled with a mechanical protection called “Blade Shedding”. This mechanical protection is provided by the rupture of all the turbine blades and the retention of the generated debris by a dedicated containment shield. During Blade Shedding, significant transient loads are transmitted to the helicopter frame through the engine mountings. The prediction of the transient loads within the turbine engine itself and those transmitted through the engine mountings is of first importance in order to plan and reduce the number of development engine tests. These loads come on one hand from impacts on the blade housing, and on the other hand from the rotor unbalance. The effects of the rotor dynamics were first implemented in the finite element code Europlexus (a Computer Program for the Finite Element Simulation of Fluid-Structure Systems under Transient Dynamic Loading) to take into account gyroscopic effects. Then the analysis of an academical test case demonstrates the relevance of the method. Finally a blades-off sequence is simulated on an industrial whole engine model and the mounting loads due to unbalance are investigated. The various assumptions made in this simulation are then discussed and the results are compared to test results.

Copyright © 2009 by ASME



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