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Advanced Experimental and Analytical Investigations on Combined Cycle Fatigue (CCF) of Conventional Cast and Single-Crystal Gas Turbine Blades

[+] Author Affiliations
Swen Weser, Uwe Gampe, Mario Raddatz

Dresden University of Technology, Dresden, Germany

Roland Parchem

Rolls-Royce Deutschland Ltd. & Co. KG, Blankenfelde-Mahlow, Germany

Petr Lukas

Institute of Physics of Materials, Brno, Czech Republic

Paper No. GT2011-45171, pp. 19-28; 10 pages
  • ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition
  • Volume 6: Structures and Dynamics, Parts A and B
  • Vancouver, British Columbia, Canada, June 6–10, 2011
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5466-2
  • Copyright © 2011 by Rolls-Royce Deutschland Ltd. & Co. AG


Rotor blades are the highest thermal-mechanical loaded components of gas turbines. Their service life is limited by interaction of creep, low cycle fatigue (LCF), high cycle fatigue (HCF) and surface attack. Because assurance of adequate HCF strength of the rotor blade is an important issue of the blade design the European project PREMECCY has been started by the European aircraft engine manufacturers and research institutes to enhance the predictive methods for combined cycle fatigue (CCF), as a superposition of HCF and LCF. Although today’s predictive methods ensure safe blade design, there are certain shortcomings of assessing fatigue life with Haigh or “modified Goodman diagrams”, such as isolated HCF assessment as well as uni-axial and off-resonant testing. HCF and LCF are considered without taking into account their interaction. PREMECCY is aimed to deliver new and improved CCF prediction methods for exploitation in the industrial design process. Beside development of predictive methods the authors are involved in the design and testing of advanced specimens representing rotor blade features. In this connection the paper presents a novel test specimen type and a unique hot gas rig for CCF feature test at mechanical and ambient representative conditions.

Copyright © 2011 by Rolls-Royce Deutschland Ltd. & Co. AG



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