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Research Papers: Gas Turbines: Structures and Dynamics

New Steps to Improve Rotordynamic Stability Predictions of Centrifugal Compressors

[+] Author and Article Information
Manoj K. Gupta

 Dresser-Rand Company, 1200 W. Sam Houston Pkwy N., Houston, TX 77043manoj_k_gupta@dresser-rand.com

Thomas A. Soulas

 Dresser-Rand Company, 1200 W. Sam Houston Pkwy N., Houston, TX 77043TSoulas@dresser-rand.com

Dara W. Childs

Turbomachinery Laboratory, Turbo Expo 2006, Texas A&M University, College Station, TX 77843dchilds@mengr.tamu.edu

J. Eng. Gas Turbines Power 130(2), 022505 (Mar 03, 2008) (5 pages) doi:10.1115/1.2799531 History: Received May 02, 2007; Revised July 06, 2007; Published March 03, 2008

Improved rotordynamic stability is desired by end users, and centrifugal compressor manufacturers are expected to meet, if not exceed, this expectation. Compressor manufacturers are required to design and build machines that are rotordynamically stable on the test stand and in the field. Confidence has been established in predicting the excitation forces from seals and bearings, but impeller aerodynamic excitation forces continue to be a challenge. While much attention is paid to impellers from an aerodynamic performance point of view, more efforts are needed from a rotordynamic standpoint. A high-pressure, reinjection centrifugal compressor is analyzed in order to predict rotordynamic stability using the best available resources for seals and bearings. Impeller shroud forces are predicted using the bulk-flow model developed by Gupta and Childs (Gupta, M., and Childs, D., Proc. of ASME Turbo Expo 2000, Power for Land, Sea, and Air). Each impeller stage is analyzed and an attempt is made to improve the estimation of impeller aerodynamic excitation forces. Logarithmic decrement (log dec) predictions for the full rotor model consisting of all the stages and seals are compared to the full-load full-pressure test measured values using a magnetic bearing exciter. A good correlation is obtained between the measured test results and analytical predictions.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Sketch of high pressure, back-to-back compressor

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Figure 2

Schematic of the rotor model

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Figure 3

Solid model of the magnetic bearing exciter

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Figure 4

Magnetic bearing used for the excitation

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Figure 5

Bulk-flow impeller code predicted cross-coupled stiffness versus discharge pressure

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Figure 6

Test and predicted rotor log dec versus discharge pressure

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