0
Research Papers

Rotating Stall Observations in a High Speed Compressor—Part I: Experimental Study

[+] Author and Article Information
J. Dodds

Rolls-Royce,
Derby DE24 8BJ, UK
e-mail: john.dodds@rolls-royce.com

M. Vahdati

Imperial College,
London SW7 2AZ, UK
e-mail: m.vahdati@imperial.ac.uk

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 8, 2014; final manuscript received July 22, 2014; published online November 18, 2014. Editor: Ronald Bunker.

J. Turbomach 137(5), 051002 (May 01, 2015) (9 pages) Paper No: TURBO-14-1123; doi: 10.1115/1.4028557 History: Received July 08, 2014; Revised July 22, 2014; Online November 18, 2014

In this two-part paper, the phenomenon of part span rotating stall is studied. The objective is to improve understanding of the physics by which stable and persistent rotating stall occurs within high speed axial flow compressors. This phenomenon is studied both experimentally (Part I) and through the use of unsteady RANS simulations (Part II). In this paper, the behavior of an eight stage high speed compressor is studied during slow acceleration maneuvres along a fixed working line. Casing mounted pressure transducers and rotor mounted strain gages are used to examine the spectral content of any unsteadiness in the flow and its behavior across the operating range. By deliberate aerodynamic mismatching of the front stages through adjustment of three rows of variable stator vanes (VSVs), stable rotating stall is initiated. The observed behavior falls into two “families” of high and low frequency when tracked on the instrumentation. Further analysis based on the Doppler shift between the static and rotating measurements confirms that these respective phenomena are due to rotating stall of high and low cell count. Acoustic modes resulting from stall/rotor interaction are also identified. Strong correlation of the stall intensity with simple 1D meanline predicted loading parameters suggests that these families of behavior are independently linked to the stalling of different regions within the compressor.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.

References

Emmons, H. W., Pearson, C. E., and Grant, H. P., 1955, “Compressor Surge and Stall Propagation,” Trans. ASME, 77, pp. 455–469.
Moore, F. K., and Greitzer, E. M., 1986, “A Theory of Post-Stall Transients in Axial Compression Systems—Parts I and II,” ASME J. Eng. Gas Turbines Power, 108(1), pp. 68–76, 231–239. [CrossRef]
Day, I. J., 1993, “Stall Inception in Axial Flow Compressors,” ASME J. Turbomach., 155(1), pp. 1–9. [CrossRef]
Camp, T. R., and Day, I. J., 1998, “A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor,” ASME J. Turbomach., 120(3), pp. 393–401. [CrossRef]
Day, I. J., Breuer, T., Escuret, J., Cherrett, M., and Wilson, A., 1999, “Stall Inception and the Prospects for Active Control in Four High Speed Compressors,” ASME J. Turbomach., 121(1), pp. 18–27. [CrossRef]
Day, I. J., Greitzer, E. M., and Cumpsty, N. A., 1978, “Prediction of Compressor Performance in Rotating Stall,” ASME J. Eng. Gas Turbines Power, 100(1), pp.1–12. [CrossRef]
Greitzer, E. M., 1978, “Surge and Rotating Stall in Axial Flow Compressors—Parts I and II,” ASME J. Eng. Gas Turbines Power, 98(2), pp. 190–217. [CrossRef]
Longley, J. P., and Hynes, T. P., 1990, “Stability of Flow Through Multistage Compressors,” ASME J. Turbomach., 112(1), pp. 126–132. [CrossRef]
Young, A., Day, I., and Pullan, G., 2011, “Stall Warning by Blade Pressure Signature Analysis,” ASME J. Turbomach., 135(1), p. 01133. [CrossRef]
Pullan, G., Young, A., Day, I., Greitzer, E. M., and Spakovszky, Z. S., 2012, “Origins and Structure of Spike-Type Rotating Stall,” ASME Paper No. GT2012-68707. [CrossRef]
Inoue, M., Kuroumaru, M., Tanino, T., and Furukawa, M., 2000, “Propagation of Multiple Short-Length-Scale Stall Cells in an Axial Compressor Rotor,” ASME J. Turbomach.122(1), pp. 45–53. [CrossRef]
Cumpsty, N. A., 1989, Compressor Aerodynamics, Longman Scientific & Technical, London.
Baumgartner, M., Kameier, F., and Houmouziadis, J., 1995, “Non-Engine Order Blade Vibration in a High Pressure Compressor,” Twelfth International Symposium on Airbreathing Engines, Melbourne, Australia, Sept. 10–15, ISABE Paper No. 95-7094.
Lieblein, S., Schwenk, F. C., and Broderick, R. L., 1953, “Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial Flow Compressor Blade Elements,” National Advisory Committee for Aeronautics, Washington, DC, Paper No. NACA RM E53D01.
Tyler, J. M., and Sofrin, T. G., 1962, “Axial Flow Compressor Noise Studies,” SAE Technical Paper No. 620532. [CrossRef]
Kameier, F., and Neise, W., 1997, “Experimental Study of Tip Clearance Losses and Noise in Axial Turbomachines and their Reduction,” ASME J. Turbomach., 119(3), pp. 460–471. [CrossRef]

Figures

Grahic Jump Location
Fig. 2

Operating map for the test compressor

Grahic Jump Location
Fig. 3

Mean line diffusion factor for R1 and R2

Grahic Jump Location
Fig. 4

Spectral analysis of transducer at position P2 for configuration B, A, C, and D

Grahic Jump Location
Fig. 5

Correlation of peak unsteady pressure to diffusion factor for (a) rotor 1 and (b) rotor 2

Grahic Jump Location
Fig. 6

Spectra for case D

Grahic Jump Location
Fig. 7

Analysis of case D

Grahic Jump Location
Fig. 8

Case “C”—rotating stall on P2 transducer and S1 strain gage

Grahic Jump Location
Fig. 1

Schematic views of the test compressor

Grahic Jump Location
Fig. 9

Spectral analysis of transducer at position P1 for configuration E, A, F, and G

Grahic Jump Location
Fig. 10

R1 stall—correlation of to meanline model

Grahic Jump Location
Fig. 11

Spectra for of case G

Grahic Jump Location
Fig. 12

“Case G” rotating stall behavior across operating range

Grahic Jump Location
Fig. 13

Close up of spectrum in Fig. 11(a)

Grahic Jump Location
Fig. 14

Analogy between a nonuniform rotor assembly and a rotating stall pattern

Grahic Jump Location
Fig. 15

Spectral analysis of case F on both transducer and rotor strain gage

Grahic Jump Location
Fig. 16

Case F spectra, PX transducer

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In