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Publications at Chair of Aero Engines

Aeroelastic Control on Compressor Blades With Virtual Control Surfaces: A Numerical Assessment
Citation key 2018_motta_75079-asme
Author Motta, V. and Malzacher, L. and Bicalho Civinelli de Almeida, V. and Peitsch, D.
Pages GT2018-75079
Year 2018
ISBN 978-0-7918-5115-9
DOI 10.1115/GT2018-75079
Location Oslo, Norway
Journal ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
Volume Volume 7C: Structures and Dynamics
Month 06
Note V07CT36A003,
Technische Universität Berlin:
V. Motta, L. Malzacher, V. Bicalho Civinelli de Almeida, D. Peitsch
Editor ASME
Series Turbo Expo: Power for Land, Sea, and Air
Abstract Plasma actuators are numerically implemented as virtual control surfaces to reduce turbomachinery blades vibration and enlarge flutter-free ranges. Actuators are located at the trailing edge of the blades, both on pressure and suction side, and are triggered either independently or alternately. Upstream blowing — i.e. plasma operating in a way that the induced flow is against the freestream — has been assessed by the authors in a previous work, and is now compared with downstream blowing — i.e. plasma-induced flow in the direction of the freestream. Steady state and traveling-wave mode calculations are performed. Transient results indicate that both upstream and downstream actuation increase remarkably the stability of the cascade. This improvement in the aeroelastic response is observed for the entire interblade phase angle range. Furthermore, the effects of locally actuating the flow on lift, drag and moment coefficients are typified. A wide range of angles of attack and blowing forces is simulated. The obtained results demonstrate that also downstream plasma actuation can be a powerful tool to deal with aeroelastic instabilities on turbomachinery, and make worthwhile to assess further in-depth the capabilities of the two actuation approaches.
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