The Institute of Aeroelasticity operates a test facility which enables aeroelastic investigations of plane cascades in low-speed flow. The test stand serves as a pilot facility to develop tools for analogous investigations in transonic flow. Eleven blades are elastically suspended in a windtunnel with a 1 × 0.2 m2 cross section. This paper describes the experimental method of determining the flutter boundary by extrapolation of the results measured in subcritical flow. A two-dimensional theoretical model of the 11 blades, including the windtunnel walls, permits the computation of unsteady pressures, forces, and moments in close relation to the experiment. The prediction of flutter is compared with experimental results. In the present investigation, the motion of the blades is constrained to pitch around mid-chord. The vibrating blades are mechanically uncoupled. Any interaction between the blades is effected by the air stream, leading to a sensitive dependence on the aerodynamic forces.
Skip Nav Destination
Article navigation
October 1998
Research Papers
Experimental Investigation and Theoretical Predication of Flutter Behavior of a Plane Cascade in Low Speed Flow
H. Hennings,
H. Hennings
Bunsenstrase 10, Goettingen, D-37073, Germany
Search for other works by this author on:
W. Send
W. Send
Bunsenstrase 10, Goettingen, D-37073, Germany
Search for other works by this author on:
H. Hennings
Bunsenstrase 10, Goettingen, D-37073, Germany
W. Send
Bunsenstrase 10, Goettingen, D-37073, Germany
J. Eng. Gas Turbines Power. Oct 1998, 120(4): 766-774 (9 pages)
Published Online: October 1, 1998
Article history
Received:
March 3, 1997
Online:
November 19, 2007
Citation
Hennings, H., and Send, W. (October 1, 1998). "Experimental Investigation and Theoretical Predication of Flutter Behavior of a Plane Cascade in Low Speed Flow." ASME. J. Eng. Gas Turbines Power. October 1998; 120(4): 766–774. https://doi.org/10.1115/1.2818465
Download citation file:
Get Email Alerts
Cited By
A Multi-Stage Nonlinear Method for Aeroengine Health Parameter Estimation Based on Adjacent Operating Points
J. Eng. Gas Turbines Power
A Combined Experimental and Turbulence-Resolved Modeling Approach for Aeroengine Turbine Rim Seals
J. Eng. Gas Turbines Power (August 2024)
Related Articles
A Numerical Method for Turbomachinery Aeroelasticity
J. Turbomach (April,2004)
Effects of Shock Waves on Aerodynamic Instability of Annular Cascade Oscillation in a Transonic Flow
J. Turbomach (July,1989)
Numerical Investigation of Nonlinear Fluid-Structure Interaction in Vibrating Compressor Blades
J. Turbomach (April,2001)
Unsteady Aerodynamic Damping Measurement of Annular Turbine Cascade With High Deflection in Transonic Flow
J. Turbomach (October,1990)
Related Proceedings Papers
Related Chapters
Aerodynamic Performance Analysis
Axial-Flow Compressors
Wind Turbine Aerodynamics Part B: Turbine Blade Flow Fields
Wind Turbine Technology: Fundamental Concepts in Wind Turbine Engineering, Second Edition
Scalability of Abinit on BlueGene/L for Identifying the Band Structure for Nanotechnology Materials
International Conference on Advanced Computer Theory and Engineering (ICACTE 2009)