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Evaluation of Torsion Axis Positon on Turbine Blade Flutter by Direct Measurement Experiment: Rig Design and Numerical Simulation

[+] Author Affiliations
Naoki Tani, Mizuho Aotsuka

IHI Corporation, Nishitama, Japan

Junichi Kazawa

JAXA, Chofu, Japan

Paper No. GT2016-57108, pp. V07BT34A013; 10 pages
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 7B: Structures and Dynamics
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4984-2
  • Copyright © 2016 by ASME


Flutter has been a very important and severe problem for gas turbines, and its importance is increasing since a modern jet engine has very thin blades to reduce weight. There have been a lot of researches on its mechanism and evaluation technique[1][2][3], however, almost all of these researches are done by CFD, forced excitation and post evaluation of engine test. Among these activities, it became clear that torsion axis plays an important role to suppress flutter onset, however, there are few data on direct measurement during flutter on an influence of torsion axis. In the present study, two blade cascades which has different torsion axis were prepared and evaluate flutter can truly suppressed or not. Test rig was designed not to disturb circumferential disturbance which is generated by flutter at the test cascade, and pressure fluctuation transduces are introduced to measure pressure field during flutter vibration. The first test campaign will be held February 2016, and the experimental data will be compared with design and CFD results. The data will help clarifying the present design criteria can be truly applied to actual flutter onset and suppression. The present paper reports rig and blade design, and these evaluations by CFD simulations.

Copyright © 2016 by ASME



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