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Research Papers

Experimental Study of Surge Precursors in a High-Speed Multistage Compressor

[+] Author and Article Information
Nicolas Courtiade

e-mail: Nicolas.Courtiade@ec-lyon.fr

Xavier Ottavy

e-mail: Xavier.Ottavy@ec-lyon.fr
Laboratoire de Mécanique
des Fluides
et d'Acoustique,
Ecole Centrale de Lyon,
36, Avenue Guy de Collongue,
Ecully 69130, France

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 18, 2012; final manuscript received August 31, 2012; published online September 13, 2013. Editor: David Wisler.

J. Turbomach 135(6), 061018 (Sep 13, 2013) (9 pages) Paper No: TURBO-12-1152; doi: 10.1115/1.4023462 History: Received July 18, 2012; Revised August 31, 2012

Pressure measurements using high frequency response sensors have been carried out on the third rotor of the 3.5-stage high speed compressor CREATE (rotation speed: 11,543 RPM, Rotor 1 tip speed: 313 m/s) over the complete characteristic line and during the surge transient. Precursors to the instabilities occurring near surge are observable at stable operating points. Just before surge, these precursors characterized as rotating disturbances grow in amplitude and provoke the onset a stall cell after a variable duration, which finally triggers surge. This paper presents a detailed analysis of the phenomena of rotating instabilities and surge transient and shows that it is possible to develop an antisurge active control system based on the early detection of the precursors.

Copyright © 2013 by ASME
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References

Figures

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Fig. 1

Meridian view of the compressor CREATE

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Fig. 2

Pressure ratio and isentropic efficiency versus mass flow rate for the design shaft-speed of the compressor CREATE

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Fig. 3

Shroud removable bloc with 12 axial positions for the pressure sensors at the tip of the rotor 3 blades

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Fig. 4

Wall static pressure measurements a few revolutions before surge—section 27 A (downstream of rotor 2)

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Fig. 5

Wall static pressure spectra at different operating points—section 280

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Fig. 6

Wall static pressure spectrum at operating point e—section 280

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Fig. 7

Time evolution of the amplitude of FBPF, F17, and F18, a few seconds before surge inception—section 280

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Fig. 8

Wall static pressure measurements over one rotor revolution—section 280

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Fig. 9

Evolution along the machine axis of the amplitude of F18 near surge inception

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Fig. 10

Global view of the pressure field affected by rotating instabilities over one rotor revolution—rotor 3

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Fig. 11

Zoom of the pressure field over one instability—rotor 3

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Fig. 12

Global view of the pressure field during surge phase 1 over four rotor revolutions—rotor 3

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Fig. 13

Global view of the pressure field during surge phase 3 over three rotor revolutions—rotor 3

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Fig. 14

Wall static pressure at mid chord of rotor 3 during surge

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Fig. 15

Schematic diagram of the antisurge control system

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Fig. 16

Temporal evolution of the ratio for three surges—section 280

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Fig. 17

Temporal evolution of the ratio during a successful test of the system—section 280

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