Investigation into the Noise Characteristics Based on Rotating Instabilities Mechanism in a Multi-Stage Axial Compressor

Abstract:

Rotating instability can be observed in the tip flow region of axial compressor stage while stable operation. In order to investigate the noise characteristics in a multi-stage axial compressor, the noise inner compressor casing is measured simultaneously with the vibration of the rotor blades on a high pressure compressor component rig testing. An azimuthal mode analysis and theoretical formulation of the rotating source mechanism are applied to the unsteady pressure at the casing wall immediately upstream of the inlet plane of the rotor. It is shown that RIs might be described by a group of superimposed modes. This is the reason why RIs can be identified as an amplitude increase in a frequency band. The mode orders of RI are consecutively numbered riseing with frequency. The frequency in the source frame (ω^N) closed to the frequency in the rotating frame (ω^N) can be got well recovered. The results presented in this paper can be a reference for further understanding of the characteristics of unsteady flow field and the effects of the high intensity sound waves on the rotor blades.

• Periodical: Applied Mechanics and Materials (Volume 160)
• Pages: 366-372
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.160.366
• Online since: March 2012
• Authors: Yun Dong Sha, Xian Zhi Cui, Feng Tong Zhao, Xiao Chi Luan
• Keywords: Axial Compressor, Noise Characteristics, Rotating Instabilities (RIs), Vibration

References

[1] F. Kameier , W. Neise, Rotating Blade Flow Instability as a Source of Noise in Axial Turbomachines, Journal of Sound and Vibration. 203(5), 1997, pp.833-853.

DOI: 10.1006/jsvi.1997.0902

[2] F. Kameier and W. Neise in: Experimental Study of Tip Clearance Losses and Noise Generation in Axial Turbomachines and Their Reductio, edited by N.A. Cumpsty, ASME J. Turbomach., 119, 1997, p.460–471.

DOI: 10.1115/1.2841145

[3] J., L. Neuhaus, W. Neise., and X. Gui : Circumferential Structure of Rotating Instability under Variation of Flow Rate and Solidity, VDI-Tagung: Turbokompressoren im industriellen Einsatz, Oct. 6–7, 1998, Hannover, Germany.

[4] M. Baumgartner, F. Kameier, and J. Hourmouziadis : Non-Engine Order Blade Vibration in a High Pressure Compressor, 12th International Symposium on Airbreathing Engines, Sept. 10–15, 1995, Melbourne, Australia.

[5] J. M. Liu, F. Holste, and W. Neise : On the Azimuthal Mode Structure of Rotating Blade Flow Instabilities in Axial Turbomachines, Published by the American Institute of Aeronautics and Astronautics, 1996 , pp.96-1741.

DOI: 10.2514/6.1996-1741

[6] R. Mailach, I. Lehman, and K. Vogeler : Rotating Instabilities in a Axial Compressor Originating From the Blade Tip Vortex, ASME J. Turbomach , 123 , p.453 – 463 (2001).

DOI: 10.1115/1.1371008

[7] J. Marz, Chunill Hah and W. Neise : An Experimental and Numerical Investigation Into the Mechanism of Rotating Instability, ASME J. Turbomach, 124, pp.367-374 (2002).

DOI: 10.1115/1.1460917

[8] Huu Duc Vo* : Role of Tip Clearance Flow in the Generation of Non-Synchronous Vibrations Published by the American Institute of Aeronautics and Astronautics (2006).

[9] L. Neuhaus and W. Neise in: Active Control to Improve the Aerodynamic Performance and Reduce the Tip Clearance Noise of Axial Turbo machines with Steady Air Injection into the Tip Clearance Gap edited by R. King: Active Flow Control, NNFM 95, p.293–306, (2007).

DOI: 10.1007/978-3-540-71439-2_18

[10] J. Thomassin, H.D. Vo and N.W. Mureithi : Blade Tip Clearance Flow and Compressor Non-synchronous Vibrations: The Jet CoreFeedback Theory as the Coupling Mechanism published by Journal of Turbomachinery (2009).

DOI: 10.1115/1.2812979