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Research Papers

Aerodynamic Optimization of a Transonic Centrifugal Compressor by Using Arbitrary Blade Surfaces

[+] Author and Article Information
Alexander Hehn

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany
e-mail: hehn@ist.rwth-aachen.de

Moritz Mosdzien

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany
e-mail: mosdzien@ist.rwth-aachen.de

Daniel Grates

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany
e-mail: grates@ist.rwth-aachen.de

Peter Jeschke

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany
e-mail: jeschke@ist.rwth-aachen.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 18, 2017; final manuscript received December 20, 2017; published online April 6, 2018. Editor: Kenneth Hall.

J. Turbomach 140(5), 051011 (Apr 06, 2018) (10 pages) Paper No: TURBO-17-1216; doi: 10.1115/1.4038908 History: Received November 18, 2017; Revised December 20, 2017

A transonic centrifugal compressor was aerodynamically optimized by means of a numerical optimization process. The objectives were to increase the isentropic efficiency and to reduce the acoustic signature by decreasing the amplitude of pre-shock pressure waves at the inlet of the compressor. The optimization was performed at three operating points on the 100% speed line in order to maintain choke mass flow and surge margin. At the design point, the specific work input was kept equal. The baseline impeller was designed by using ruled surfaces due to requirements for flank milling. To investigate the benefits of arbitrary blade surfaces, the restrictions of ruled surfaces were abolished and fully three-dimensional (3D) blade profiles allowed. In total, therefore, 45 parameters were varied during the optimization. The combined geometric and aerodynamic analysis reveals that a forward swept leading edge (LE) and a concave suction side at the tip of the LE are effective design features for reducing the shock strength. Beyond that, the blade shape of the optimized compressor creates a favorable impeller outlet flow, which is the main reason why the performance of the vaneless diffuser improves. In total, a gain of 1.4% points in isentropic total-to-static efficiency, evaluated by computational fluid dynamics (CFD) at the exit plane of the vaneless diffuser, is achieved.

Copyright © 2018 by ASME
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Figures

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Fig. 1

Baseline impeller SRV4R

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Fig. 2

Baseline compressor stage SRV4R

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Fig. 3

Optimization process

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Fig. 4

Global optimization results

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Fig. 5

3D rendering of design 603

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Fig. 6

Static pressure at shroud in OP1: (a) SRV4R and (b) design 603

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Fig. 7

Wall pressure along the evaluation line, which is 10% of the axial MB length in front of the LE. Operating point close to OP1.

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Fig. 8

Performance comparison: (a) TPR at the diffuser outlet, (b) efficiency at the impeller outlet, and (c) efficiency at the diffuser outlet. The 92% speed line was left out in (b) and (c) for reasons of clarity.

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Fig. 10

Schematic velocity triangles at the impeller exit

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Fig. 11

Diffuser performance in OP1

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Fig. 12

Absolute flow angle distribution in the diffuser inlet in OP1: (a) SRV4R and (b) design 603

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Fig. 13

Averaged entropy, blockage, and relative Mach number along the impeller in OP1

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Fig. 14

Meridional velocity distribution at the impeller exit in OP1: (a) SRV4R and (b) design 603

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Fig. 15:

Comparison of the blade and the flow angle in OP1: (a) SRV4R and (b) design 603

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Fig. 16

Blade loading in OP1: (a) 50% span and (b) 90% span

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