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Research Papers

The Effects of Radially Distorted Incident Flow on Performance of Axial-Flow Fans With Forward-Skewed Blades

[+] Author and Article Information
B. Yang

e-mail: byang0626@sjtu.edu.cn

Ch. G. Gu

e-mail: cggu2006@126.com
School of Mechanical Engineering,
Shanghai Jiaotong University,
Shanghai, China

Contributed by International Gas Turbine Institute (IGTI) of ASME for publication in JOURNAL OF TURBOMACHINERY. Manuscript received August 1, 2011; final manuscript received August 31, 2011; published online October 31, 2012. Editor: David Wisler.

J. Turbomach 135(1), 011039 (Oct 31, 2012) (12 pages) Paper No: TURBO-11-1172; doi: 10.1115/1.4006535 History: Received August 01, 2011; Revised August 31, 2011

In this study, experiments and numerical simulations were carried out to evaluate the effects of radially distorted incident flow on the performance of axial-flow fans, which were equipped with three kinds of forward-skewed blades. Loss coefficient and velocity components at exit section as well as overall performance are discussed, both at the design point and the lower mass flow rate point. Furthermore, rotating stall was also observed by use of three dynamic pressure sensors. All results reveal that there are beneficial effects of forward-skewed blades on the fan performance, but the fan performance and its unsteady aerodynamic characteristics are quite affected by the radially distorted incident flow.

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References

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Figures

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Fig. 1

Scheme of definition of forward-skewed angle (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 2

Three blades with different forward-skewed angles

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Fig. 3

Seven-hole probe: (1) screen carrier, (2) impeller, (3) motor, (4) test tube, (5) straightening screen, (6) conical throttle. A, seven-hole probe at inlet of impeller; B, seven-hole probe at outlet of the impeller; C, dynamic pressure sensors; D, pitot probe.

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Fig. 4

Scheme of experimental rig

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Fig. 5

Instruments arrangement (a) efficiency (b) total pressure coefficient

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Fig. 6

Fan performance under uniform inlet condition

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Fig. 7

Distribution of loss coefficient spanwise at design point under uniform inlet condition

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Fig. 8

Distribution of tangential velocity coefficient spanwise at design point under uniform inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 9

Contours of axial velocity at design point under uniform inlet condition

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Fig. 10

Distribution of loss coefficient spanwise at lower mass flow rate point under uniform inlet condition

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Fig. 11

Distribution of tangential velocity coefficient spanwise at lower mass flow rate point under uniform inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 12

Contours of axial velocity at lower mass flow rate point under uniform inlet condition (a) efficiency (b) total pressure coefficient

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Fig. 13

Fan performance under hub-covered inlet condition

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Fig. 14

Distribution of loss coefficient spanwise at design point under hub-covered inlet condition

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Fig. 15

Distribution of tangential velocity coefficient spanwise at design point under hub-covered inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 16

Contours of axial velocity at design point under hub-covered inlet condition

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Fig. 17

Distribution of loss coefficient spanwise at lower mass flow rate point under hub-covered inlet condition

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Fig. 18

Distribution of tangential velocity coefficient spanwise at lower mass flow rate point under hub-covered inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 19

Contours of axial velocity at lower mass flow rate point under hub-covered inlet condition (a) efficiency (b) total pressure coefficient

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Fig. 20

Fan performance under tip-covered inlet condition

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Fig. 21

Distribution of loss coefficient spanwise at design point under tip-covered inlet condition

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Fig. 22

Distribution of tangential velocity coefficient spanwise at design point under tip-covered inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 23

Contours of axial velocity at design point under tip-covered inlet condition

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Fig. 24

Distribution of loss coefficient spanwise at lower mass flow rate point under tip-covered inlet condition

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Fig. 25

Distribution of tangential velocity coefficient spanwise at lower mass flow rate point under tip-covered inlet condition (a) 3 deg (b) 6 deg (c) 12 deg

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Fig. 26

Contours of axial velocity at lower mass flow rate point under tip-covered inlet condition (a) uniform inlet condition (b) hub-covered inlet condition (c) tip-covered inlet condition

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Fig. 27

Static pressure trace

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