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Research Papers

Performance Evaluation of Nonuniformly Fouled Axial Compressor Stages by Means of Computational Fluid Dynamics Analyses

[+] Author and Article Information
Nicola Aldi

Terra&AcquaTech,
Università degli Studi di Ferrara,
Ferrara, Italy

Mirko Morini

MechLav,
Università degli Studi di Ferrara,
Ferrara, Italy

Mauro Venturini

Dipartimento di Ingegneria,
Università degli Studi di Ferrara,
Ferrara, Italy

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 12, 2013; final manuscript received July 22, 2013; published online October 10, 2013. Editor: Ronald Bunker.

J. Turbomach 136(2), 021016 (Oct 10, 2013) (11 pages) Paper No: TURBO-13-1152; doi: 10.1115/1.4025227 History: Received July 12, 2013; Revised July 22, 2013

In this paper, three-dimensional numerical simulations are carried out to evaluate the effect of fouling on an axial compressor stage. A numerical model of the NASA Stage 37, validated in previous papers of the same authors against experimental data available from literature, is used as a case study. The occurrence of fouling is simulated by imposing different spanwise distributions of surface roughness, in order to analyze its effect on compressor performance. To this aim, both the stage performance maps of the fouled compressor and the spanwise distribution of work and losses are analyzed and discussed. Moreover, the definition of an averaged roughness parameter is suggested, to characterize the different roughness distributions.The results show that the drop of overall performance can actually be predicted by means of the numerical model. Moreover, detailed information about fluid-dynamic phenomena can be analyzed on the basis of the actual distribution of surface roughness on rotor blades.

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Figures

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Fig. 1

Modeled geometry and numerical grid for NASA Stage 37

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Fig. 3

Fouled compressor stage performance maps

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Fig. 4

Spanwise variation of the pressure ratio β at rotor outlet section

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Fig. 5

Spanwise variation of stage total pressure

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Fig. 6

Spanwise variation of the ratio φ at rotor outlet section

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Fig. 7

Spanwise variation of the ratio γ at rotor outlet section

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Fig. 8

Blade loading versus the streamwise coordinate, at 10%, 50%, or 90% of the span height

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Fig. 9

Averaged roughness parameter for the considered NURDs

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Fig. 10

Blade loading versus the streamwise coordinate, at 90% of the span height: comparison of URD 2 to NURD 2 and TCS

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Fig. 11

Blade loading versus the streamwise coordinate, at 90% of the span height: comparison of URD 5 to NURD 5 and TCS

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Fig. 12

Spanwise variation of the pressure ratio β: comparison of URD 2 to NURD 2 and TCS

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