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Research Papers

Particle Image Velocity Investigation of a High Speed Centrifugal Compressor Diffuser: Spanwise and Loading Variations

[+] Author and Article Information
Beni Cukurel, Patrick B. Lawless, Sanford Fleeter

 Purdue University, West Lafayette, IN 47907-2040

J. Turbomach 132(2), 021010 (Jan 12, 2010) (9 pages) doi:10.1115/1.3104616 History: Received October 01, 2008; Revised November 25, 2008; Published January 12, 2010; Online January 12, 2010

An efficient diffuser is essential to a modern compressor stage due to its significance in stage performance, durability, and operability. To address the need for data that describe the complex, unsteady flow field in a vaned diffuser, particle image velocity is utilized to characterize the spanwise and circumferential variations in the flow features in the vaned diffuser passage of a transonic centrifugal compressor. The spanwise variation in the diffuser flow field is further investigated by the comparison of three different operating conditions representative of low, nominal, and high loading. These data demonstrate that not only the diffuser flow field is highly dependent on the operation conditions, e.g., hub-to-shroud variation increases with loading, but also the circumferential periodicity, created by the highly three dimensional impeller discharge flow, generates a larger unsteadiness toward the hub region of the vaned diffuser.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Diffuser access window

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Figure 2

Impeller flow interaction with the diffuser, Mach number distribution, and typical delay

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Figure 3

Nominal loading, hub plane, Mach number

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Figure 4

Nominal loading, hub plane, flow angle α°

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Figure 5

Nominal loading, midplane, Mach number

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Figure 6

Nominal loading, midplane, flow angle α°

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Figure 7

Nominal loading, shroud plane, Mach number

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Figure 8

Nominal loading, shroud plane, flow angle α°

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Figure 9

Choke loading, mean Mach number

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Figure 10

Choke loading, mean flow angle α°

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Figure 11

Nominal loading, midplane, typical delay, throat shock structures, Mach number (top), and flow angle α° (bottom)

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Figure 12

Choke loading, midplane, typical delay, throat shock structures, Mach number (top), and flow angle α° (bottom)

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Figure 13

Prestall loading, mean Mach number

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Figure 14

Prestall loading, mean flow angle α°

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Figure 15

Nominal loading, sum of variances (m2/s2)

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Figure 16

Prestall loading, sum of variances (m2/s2)

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