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Research Papers

Effect of Recirculation Device With Counter Swirl Vane on Performance of High Pressure Ratio Centrifugal Compressor

[+] Author and Article Information
Hideaki Tamaki

 Turbo Machinery and Engine Technology Department, IHI Corporation, 1, Shin-Nakahara-Cho, Isogo-Ku, Yokohama, 235-8501hideaki_tamaki@ihi.co.jp

J. Turbomach 134(5), 051036 (Jun 05, 2012) (12 pages) doi:10.1115/1.4004820 History: Received July 10, 2011; Revised July 28, 2011; Published June 05, 2012; Online June 05, 2012

Centrifugal compressors used for turbochargers need to achieve a wide operating range. The author has developed a high pressure ratio centrifugal compressor with pressure ratio 5.7 for a marine use turbocharger. In order to enhance operating range, two different types of recirculation devices were applied. One is a conventional recirculation device. The other is a new one. The conventional recirculation device consists of an upstream slot, bleed slot and the annular cavity which connects both slots. The new recirculation device has vanes installed in the cavity. These vanes were designed to provide recirculation flow with negative preswirl at the impeller inlet, a swirl counterwise to the impeller rotational direction. The benefits of the application of both of the recirculation devices were ensured. The new device in particular, shifted surge line to a lower flow rate compared to the conventional device.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 21

Circumferentially averaged streamlines near shroud

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Figure 22

Relative Mach number contours at Mu = 1.40.(a) RC m/md  = 0.68 and (b) CS m/md  = 0.68

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Figure 23

Relative Mach number and entropy contours at m/md  = 0.89 and Mu = 1.62. (a) relative Mach number (left: RC, right: CS) and (b) entropy distribution (left: RC, right: CS).

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Figure 8

Work coefficient based on measured data

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Figure 9

Work coefficient based on CFD results

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Figure 10

One-dimensional model of the recirculation device

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Figure 11

Inlet work coefficient based on 1-D model

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Figure 12

Inlet work coefficient based on CFD results

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Figure 13

Recirculation ratio

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Figure 14

Circumferentially averaged circumferential velocity distribution of leading edge at Mu=1.40

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Figure 15

Total temperature, relative flow angle and relative Mach number at Mu = 1.40 (m/md  = 0.81). (a) total temperature distribution near impeller inlet, (b) circumferentially averaged relative flow angle at leading edge, and (c) relative Mach number on full blade at 90% span.

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Figure 16

Total temperature, relative flow angle and relative Mach number at Mu = 1.40 (m/md  = 0.68, 0.55). (a) total temperature distribution near impeller inlet,(b) Circumferentially averaged relative flow angle at leading edge, and (c) Relative Mach number on full blade at 90% span.

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Figure 17

Circumferentially averaged streamlines near shroud:SW (m/md  = 0.81, Mu = 1.40) RC (m/md  = 0.68, Mu = 1.40) and CS (m/md  = 0.55 at Mu = 1.40)

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Figure 18

Circumferentially averaged circumferential velocity distribution of leading edge at Mu=1.62

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Figure 19

Relative Mach number and total temperature at Mu = 1.62 (m/md  = 0.89). (a) relative Mach number on full blade at 90% span and (b) total temperature distribution near impeller inlet.

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Figure 20

Relative flow angle at onset of instability

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Figure 1

Schematic view of conventional recirculation device

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Figure 2

Illustration of new recirculation device

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Figure 3

Picture of investigated compressor

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Figure 4

Investigated recirculation device

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Figure 5

Measured compressor performance

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Figure 6

Calculated compressor performance

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Figure 7

Measured and calculated static pressure at 1.14R2

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Figure 26

Axial velocity at 98% span and axial vorticity at 97% span (m/md  = 0.89 and Mu = 1.62). (a) Axial velocity (RC), (b) axial vorticity (RC), (c) Axial velocity (CS), and (d) axial vorticity (CS).

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Figure 27

Axial velocity at 98% span and axial vorticity at 97% span (m/md  = 0.75 and Mu = 1.62). (a) Axial velocity (CS) and (b) axial vorticity (CS).

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Figure 28

Relative Mach number at m/md  = 0.75 and Mu = 1.62

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Figure 29

Relative Mach number at m/md  = 0.55 and Mu = 1.40

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Figure 30

Limiting streamline of CS m/md  = 0.55 at Mu = 1.40 m/md  = 0.75 at Mu=1.62

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Figure 24

Axial component of vorticity at 0.86H

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Figure 25

Axial velocity at 98% span and axial vorticity at 97% span (m/md  = 0.97 and Mu = 1.62). (a) Axial velocity (SW), (b) axial vorticity (SW), (c) Axial velocity (RC), and (d) axial vorticity (RC).

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