Research Papers

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

[+] Author and Article Information
J. Dodds

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.

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Fig. 1

Schematic views of the test compressor

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Fig. 2

Operating map for the test compressor

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Fig. 3

Mean line diffusion factor for R1 and R2

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Fig. 4

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

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Fig. 5

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

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Fig. 6

Spectra for case D

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Fig. 13

Close up of spectrum in Fig. 11(a)

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Fig. 14

Analogy between a nonuniform rotor assembly and a rotating stall pattern

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Fig. 12

“Case G” rotating stall behavior across operating range

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Fig. 11

Spectra for of case G

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Fig. 10

R1 stall—correlation of to meanline model

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Fig. 9

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

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Fig. 8

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

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Fig. 7

Analysis of case D

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Fig. 15

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

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Fig. 16

Case F spectra, PX transducer




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