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Research Papers

Analysis of the Rotordynamic Response of a Centrifugal Compressor Subject to Aerodynamic Loads Due to Rotating Stall

[+] Author and Article Information
Davide Biliotti

Department of Industrial Engineering,
University of Florence,
Via di Santa Marta 3,
Firenze 50139, Italy
e-mail: biliotti@vega.de.unifi.it

Alessandro Bianchini

Department of Industrial Engineering,
University of Florence,
Via di Santa Marta 3,
Firenze 50139, Italy
e-mail: bianchini@vega.de.unifi.it

Giuseppe Vannini

GE Oil&Gas,
Via Felice Matteucci 2,
Florence 50127, Italy
e-mail: giuseppe.vannini@ge.com

Elisabetta Belardini

GE Oil&Gas,
Via Felice Matteucci 2,
Florence 50127, Italy
e-mail: elisabetta.belardini@ge.com

Marco Giachi

GE Oil&Gas,
Via Felice Matteucci 2,
Florence 50127, Italy
e-mail: marco.giachi@ge.com

Libero Tapinassi

GE Oil&Gas,
Via Felice Matteucci 2,
Florence 50127, Italy
e-mail: libero.tapinassi@ge.com

Lorenzo Ferrari

CNR-ICCOM,
National Research Council of Italy,
Via Madonna del Piano 10,
Sesto Fiorentino 50019, Italy
e-mail: lorenzo.ferrari@iccom.cnr.it

Giovanni Ferrara

Department of Industrial Engineering,
University of Florence,
Via di Santa Marta 3,
Firenze 50139, Italy
e-mail: giovanni.ferrara@unifi.it

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 15, 2014; final manuscript received July 30, 2014; published online September 10, 2014. Editor: Ronald Bunker.

J. Turbomach 137(2), 021002 (Sep 10, 2014) (8 pages) Paper No: TURBO-14-1148; doi: 10.1115/1.4028246 History: Received July 15, 2014; Revised July 30, 2014

In the current industrial research on centrifugal compressors, manufacturers are showing increasing interest in the extension of the minimum stable flow limit in order to improve the operability of each unit. The aerodynamic performance of a compressor stage is indeed often limited before surge by the occurrence of diffuser rotating stall. This phenomenon generally causes an increase of the radial vibrations, which, however, is not always connected with a remarkable performance detriment. In case the operating curve has been limited by a mechanical criterion, i.e., based on the onset of induced vibrations, an investigation on the evolution of the aerodynamic phenomenon when the flow rate is further reduced can provide some useful information. In particular, the identification of the real thermodynamic limit of the system could allow one to verify if the new load condition could be tolerated by the rotordynamic system in terms of radial vibrations. Within this context, recent works showed that the aerodynamic loads due to a vaneless diffuser rotating stall can be estimated by means of test-rig experimental data of the most critical stage. Moreover, by including these data into a rotordynamic model of the whole machine, the expected vibration levels in real operating conditions can be satisfactorily predicted. To this purpose, a wide-range analysis was carried out on a large industrial database of impellers operating in presence of diffuser rotating stall; the analysis highlighted specific ranges for the resultant rotating force in terms of intensity and excitation frequency. Moving from these results, rotordynamic analyses have been performed on a specific case study to assess the final impact of these aerodynamic excitations.

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References

Figures

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Fig. 1

Dimensionless head coefficient versus dimensionless flow coefficient (i.e., φ*=φ/φdes) for a tested stage

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Fig. 2

Distribution of the dimensionless force coefficient in the analyzed test models

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Fig. 3

Analyzed stall patterns as a function of the dimensionless frequency and the force coefficient

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Fig. 4

Analyzed stall patterns as a function of the flow coefficient range and the force coefficient

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Fig. 5

Comparison between predicted vibrations and experiments

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Fig. 6

Rotordynamic model of the compressor

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Fig. 7

Predicted vibrations as a function of the stall force intensity and frequency for the two clearance limits of the bearings (no seals)

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Fig. 8

Predicted vibrations as a function of the stall force intensity and frequency with the laby seals effect

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Fig. 9

Maximum tolerated χ values as a function of the stall frequency (with respect to f1xREV) and the clearance of the bearings

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Fig. 10

Approach of the study

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