Influence of form of tip gap on aerodynamic performance of centrifugal compressor using mixture of helium and xenon

被引：0

作者：

Wang G. ^{[1
]}

Liu X. ^{[1
]}

Gao J. ^{[1
]}

Zheng Q. ^{[1
]}

机构：

[1] College of Power and Energy Engineering, Harbin Engineering University, Harbin

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2020年 / 35卷 / 06期

关键词：

Aerodynamic performance; Centrifugal compressor; Flow characteristics; Mixture of helium and xenon; Tip gap;

D O I：

10.13224/j.cnki.jasp.2020.06.021

中图分类号：

学科分类号：

摘要：

The tip leakage flow directly affects the performance of the centrifugal compressor. The influence of the independent change of the radial and axial tip gaps and the influence of the distribution of the tip gap on the centrifugal compressor internal flow field and performance were studied by numerical simulation. The influence law of different height and shape of the centrifugal compressor tip gap on its performance was summarized. Result showed that increasing the centrifugal compressor gap would reduce the efficiency at near surge condition and design condition; increasing the radial gap solely, from 0.1mm to 0.4mm, could broaden the choke mass flow range by 3.88% and improve the performance of the centrifugal compressor near blockage condition; increasing the axial gap solely had no effect on the performance at near choke condition. The shrinking distribution of tip gap increased the efficiency of the centrifugal compressor by 0.23%. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1304 / 1314

页数：10

共 19 条

[1]

TIAN Zhitao, ZHENG Qun, JIANG Bin, Design and analysis of helium and xenon binary mixture gas centrifugal compressor, Chinese Journal of Turbomachinery, 60, 3, pp. 14-19, (2018)

[2]

SKOCH G., Experimental investigation of centrifugal compressor stabilization techniques, Journal of Turbomachinery, 125, 4, pp. 765-776, (2003)

[3]

HAH C, KRAIN H., Secondary flows and vortex motion in a high-efficiency backswept impeller at design and off-design conditions, Journal of Turbomachinery, 112, 1, pp. 7-13, (1990)

[4]

MOORE J, MOORE J G., Secondary flow, separation and losses in the NACA 48-inch centrifugal impeller at design and off-design conditions, (1988)

[5]

SENOO Y., Mechanics on the tip clearance loss of impeller blades, Journal of Turbomachinery, 113, 4, pp. 680-685, (1991)

[6]

SENOO Y, ISHIDA M., Deterioration of compressor performance due to tip clearance of centrifugal impellers, Transactions of the Japan Society of Mechanical Engineers, 109, 1, pp. 55-61, (1987)

[7]

ISHIDA M, UEKI H, SENOO Y., Effect of blade tip configuration on tip clearance loss of a centrifugal impeller, Transactions of the Japan Society of Mechanical Engineers, 112, 1, pp. 14-18, (1990)

[8]

SCHLEER M, SONG S J, ABHARI A R S., Clearance effects on the onset of instability in a centrifugal compressor, Journal of Turbomachinery, 130, 3, pp. 993-1003, (2006)

[9]

SCHLEER M, ABHAEI R S., Clearance effects on the evolution of the flow in the vaneless diffuser of a centrifugal compressor at part load condition, Journal of Turbomachinery, 130, 3, (2008)

[10]

YAMADA K, TAMAGAWA Y, FUKUSHHIMA H, Et al., Comparative study on tip clearance flow fields in two types of transonic centrifugal compressor impeller with splitter blades, (2010)

← 1 2 →