Affiliation:
1. Beijing University of Aeronautics and Astronautics
Abstract
A full-annulus unsteady quasi-3D simulation for a transonic compressor was conducted to investigate the low engine order excitation sources. A special inlet total pressure distortion was used in the simulation to account for the effect of non-axisymmetric tip clearance. The unsteady aerodynamic forces were obtained by integrating the static pressure along the blade surface. Furthermore, the effect of downstream rotor detached shock on upstream stator was analyzed. It was shown that the unsteady aerodynamic excitation of the rotor was subjected to the first two harmonic frequencies of the inlet distortion, and the adjacent stators’ basic frequency and lower harmonics. It was found that the detached shock had a significant impact on the surface static pressure distribution of the upstream stators.
Publisher
Trans Tech Publications, Ltd.
Reference10 articles.
1. L. He, Unsteady Flow and Aeroelasticity, Handbook of Turbomachinery. New York: Marcel Dekker, Inc, (2003).
2. Jay R. L. and Fleeter S., Unsteady Aerodynamic Mesaurements in Forced Vibration Research, AGARD Manual on Aeroelasticity in Axial Flow Turbomachines, AGARD-AG-298, ISBN92-835-0467-4, Max F. Platzer and Franklin O. Carta eds., (1988).
3. M. Jocker et al., Comparison of Models to Predict Low Engine Order Excitation in a High Pressure Turbine Stage, Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, 2006, pp.145-159.
4. A.J. Sanders, S. Fleeter, Multi-Blade Row Interaction in a Transonic Axial Compressor Part2: Rotor Wake Forcing Function and Stator Unsteady Aerodynamic Response, ASME Paper 2001-GT-0269, (2001).
5. F. Leroeuf and I. Trebinjac, Methodology and Results of Analysis for Unsteady Flows in Transonic Turbine and Compressor Stages, AIAA Paper 2003-3733, (2003).