Research Papers

Numerical Analysis of the Vaned Diffuser of a Transonic Centrifugal Compressor

[+] Author and Article Information
Michele Marconcini

“Sergio Stecco” Department of Energy Engineering, University of Florence, via di Santa Marta 3, 50139 Firenze, Italymichele.marconcini@arnone.de.unifi.it

Filippo Rubechini, Andrea Arnone

“Sergio Stecco” Department of Energy Engineering, University of Florence, via di Santa Marta 3, 50139 Firenze, Italy

Seiichi Ibaraki

Nagasaki R&D Center, Mitsubishi Heavy Industries, Ltd., 5-717-1 Fukahori-machi, Nagasaki 851-0392, Japan

J. Turbomach 132(4), 041012 (May 05, 2010) (8 pages) doi:10.1115/1.2988481 History: Received September 19, 2007; Revised December 03, 2007; Published May 05, 2010; Online May 05, 2010

A three-dimensional Navier–Stokes solver is used to investigate the flow field of a high pressure ratio centrifugal compressor for turbocharger applications. Such a compressor consists of a double-splitter impeller followed by a vaned diffuser. Particular attention is focused on the analysis of the vaned diffuser, designed for high subsonic inlet conditions. The diffuser is characterized by a complex three-dimensional flow field and influenced by the unsteady interaction with the impeller. Detailed particle image velocimetry flow measurements within the diffuser are available for comparison purposes.

Copyright © 2010 by American Society of Mechanical Engineers
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Figure 1

Cross section of the compressor stage

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Figure 2

PIV measurement locations

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Figure 3

Three-dimensional view of the impeller and diffuser computational mesh

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Figure 4

Compressor stage characteristic (full scale geometry)

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Figure 5

Measured and computed (steady state) circumferential averaged flow angle (a) and meridional velocity (b)

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Figure 6

Comparison between the measured (17) and computed flow angle contours and velocity vectors (near peak): (a) Sec. C—23% span (PIV), (b) Sec. B—50% span (PIV), (c) Sec. A—67% span (PIV), (d) Sec. C—23% span, (e) Sec. B—50% span, (f) Sec. A—67% span

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Figure 7

Evolution of the lift coefficient (a) and the lift coefficient amplitude harmonics (b) on the impeller (c) and on the diffuser blades (near peak)

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Figure 8

Measured and computed circumferential averaged flow angle at r=1.12⋅r2 (near peak)

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Figure 9

Cp distributions (a) and level of unsteadiness (b) on the diffuser vane (near peak)

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Figure 10

Time evolution of the flow angle in the vaned diffuser (near peak): (a) point a, (b) point b, (c) point c

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Figure 11

Instantaneous entropy contours at midspan (near peak)

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Figure 12

Instantaneous entropy contours at midspan and the streamline on the hub and pressure surface during an impeller full blade passing period (near peak): (a) t∕T=0.0, (b) t∕T=0.1, (c) t∕T=0.2, (d) t∕T=0.3, (e) t∕T=0.4, (f) t∕T=0.5, (g) t∕T=0.6, (h) t∕T=0.7, (i) t∕T=0.8, (j) t∕T=0.9, and (k) wake reference at t∕T=0.0



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