Forming the first part of a two-part paper, the experimental approach to acquire resonant vibration data is presented here. Part II deals with the estimation of damping. During the design process of turbomachinery components, mechanical integrity has to be guaranteed with respect to high cycle fatigue of blades subject to forced response or flutter. This requires the determination of stress levels within the blade, which in turn depend on the forcing function and damping. The vast majority of experimental research in this field has been performed on axial configurations for both compressors and turbines. This experimental study aims to gain insight into forced response vibration at resonance for a radial compressor. For this purpose, a research impeller was instrumented with dynamic strain gauges and operated under resonant conditions. Modal properties were analyzed using finite element method and verified using an optical method termed electronic-speckle-pattern-correlation-interferometry. During the experiment, unsteady forces acting on the blades were generated by grid installations upstream of the impeller, which created a distorted inlet flow pattern. The associated flow properties were measured using an aerodynamic probe. The resultant pressure fluctuations on the blade surface and the corresponding frequency content were assessed using unsteady computational fluid dynamics. The response of the blades was measured for three resonant crossings, which could be distinguished by the excitation order and the natural frequency of the blades. Measurements were undertaken for a number of inlet pressure settings starting at near vacuum and then increasing. The overall results showed that the installed distortion screens generated harmonics in addition to the fundamental frequency. The resonant response of the first and the second blade mode showed that the underlying dynamics support a single-degree-of-freedom model.
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March 2009
Research Papers
Experimental Study on Impeller Blade Vibration During Resonance—Part I: Blade Vibration Due to Inlet Flow Distortion
Albert Kammerer,
Albert Kammerer
LEC, Laboratory for Energy Conversion, Department of Mechanical and Process Engineering,
ETH Zurich
, 8092 Zürich, Switzerland
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Reza S. Abhari
Reza S. Abhari
LEC, Laboratory for Energy Conversion, Department of Mechanical and Process Engineering,
ETH Zurich
, 8092 Zürich, Switzerland
Search for other works by this author on:
Albert Kammerer
LEC, Laboratory for Energy Conversion, Department of Mechanical and Process Engineering,
ETH Zurich
, 8092 Zürich, Switzerland
Reza S. Abhari
LEC, Laboratory for Energy Conversion, Department of Mechanical and Process Engineering,
ETH Zurich
, 8092 Zürich, SwitzerlandJ. Eng. Gas Turbines Power. Mar 2009, 131(2): 022508 (11 pages)
Published Online: December 29, 2008
Article history
Revised:
April 8, 2008
Received:
April 8, 2008
Published:
December 29, 2008
Connected Content
A companion article has been published:
Experimental Study on Impeller Blade Vibration During Resonance—Part II: Blade Damping
Citation
Kammerer, A., and Abhari, R. S. (December 29, 2008). "Experimental Study on Impeller Blade Vibration During Resonance—Part I: Blade Vibration Due to Inlet Flow Distortion." ASME. J. Eng. Gas Turbines Power. March 2009; 131(2): 022508. https://doi.org/10.1115/1.2968869
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