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Research Papers

Centrifugal Compressor Design for Near-Critical Point Applications

[+] Author and Article Information
Alireza Ameli

Mem. ASME
Laboratory of Fluid Dynamics,
School of Energy Systems,
Lappeenranta University of Technology,
Lappeenranta 53850, Finland
e-mail: alireza.ameli@lut.fi

Ali Afzalifar

Laboratory of Fluid Dynamics,
School of Energy Systems,
Lappeenranta University of Technology,
Lappeenranta 53850, Finland
e-mail: ali.afzalifar@fmi.fi

Teemu Turunen-Saaresti

Laboratory of Fluid Dynamics,
School of Energy Systems,
Lappeenranta University of Technology,
Lappeenranta 53850, Finland
e-mail: teemu.turunen-saaresti@lut.fi

Jari Backman

Laboratory of Fluid Dynamics,
School of Energy Systems,
Lappeenranta University of Technology,
Lappeenranta 53850, Finland
e-mail: jari.backman@lut.fi

1Corresponding author.

2Present Address Senior researcher at Finnish Meteorological Institute, Finland

Manuscript received June 25, 2018; final manuscript received June 26, 2018; published online October 5, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(3), 031016 (Oct 05, 2018) (8 pages) Paper No: GTP-18-1336; doi: 10.1115/1.4040691 History: Received June 25, 2018; Revised June 26, 2018

The supercritical CO2 (sCO2) Brayton cycle has been attracting much attention to produce the electricity power, chiefly due to its higher thermal efficiency with the relatively lower temperature at the turbine inlet compared to other common energy conversion cycles. Centrifugal compressor operating conditions in the supercritical Brayton cycle are commonly set in vicinity of the critical point, owing to smaller compressibility factor and eventually lower compressor work. This paper investigates and compares different centrifugal compressor design methodologies in close proximity to the critical point and suggests the most accurate design procedure based on the findings. An in-house mean-line design code, which is based on the individual enthalpy loss models, is compared to stage efficiency correlation design methods. Moreover, modifications are introduced to the skin friction loss calculation to establish an accurate one-dimensional design methodology. Moreover, compressor performance is compared to the experimental measurements.

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Figures

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Fig. 1

Specific heat in constant pressure variation near the critical point. The dot shows the critical point location.

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Fig. 2

Velocity triangle schematics at the leading (left) and trailing (right) edges of the blade

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Fig. 3

Geometry and mesh of the studied centrifugal compressor

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Fig. 4

Share of the individual loss (design point)

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Fig. 5

Locations along the stream-wise direction from the main blade leading edge (MB-L) to the blade trailing edge (B-T)

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Fig. 6

Wall shear stress distribution at 90% of the blade passage (peak efficiency point)

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Fig. 7

Normalized relative velocity distribution at 90% of the blade passage in blade-to-blade direction (peak efficiency point). Circles locate Un−1=0.995Un.

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Fig. 8

Skin friction coefficient distribution along the meridional length

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Fig. 9

Compressor map comparison (at 50,000 rpm)

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Fig. 10

Internal loss comparison

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Fig. 11

Comparison between the accuracy of different design methodologies (design point)

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