Effects of Blade Leading Edge Lean and Sweep on the Aerodynamic Performance of Centrifugal Impellers

doi:10.7652/xjtuxb201511001

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Effects of Blade Leading Edge Lean and Sweep on the Aerodynamic Performance of Centrifugal Impellers

更新时间：2025-07-09

- Effects of Blade Leading Edge Lean and Sweep on the Aerodynamic Performance of Centrifugal Impellers
- Vol. 49, Issue 11, Pages: 1-7(2015)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201511001
  CLC： TK269
- Online First：10 November 2015，
  
  Published：2015
- 稿件说明：
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Effects of Blade Leading Edge Lean and Sweep on the Aerodynamic Performance of Centrifugal Impellers[J]. 2015, 49(11): 1-7.
DOI：

Effects of Blade Leading Edge Lean and Sweep on the Aerodynamic Performance of Centrifugal Impellers[J]. 2015, 49(11): 1-7. DOI： 10.7652/xjtuxb201511001.

摘要

为了研究叶片前缘倾掠对离心叶轮气动性能及稳定工况范围的影响

在叶片前缘处沿子午面弦长方向进行叶尖前掠、叶尖后掠、叶根前掠、叶根后掠

实现了4种不同的叶片前缘倾掠。研究结果表明

对跨声速离心叶轮

叶尖前掠和叶根前掠可提高叶轮最高等熵效率和压比; 叶尖后掠对叶轮等熵效率影响很小

但可降低叶轮压比; 叶根后掠使叶轮等熵效率和压比均有所降低。同时

叶尖前掠和叶根后掠可提高其失速裕度

叶尖后掠和叶根前掠则可减小其失速裕度。为了便于比较

还研究了一个亚声速叶轮。研究发现

与跨声速叶轮相比

叶片前缘倾掠对亚声速叶轮的等熵效率和压比影响更小

但对失速裕度的影响和跨声速叶轮相似。对跨声速叶轮

叶尖前掠是提高其等熵效率、压比和失速裕度的一种有效方法。

Abstract

To study the effects of blade leading edge lean and sweep on the aerodynamic performance and stable operating range of centrifugal impellers

this paper presents four different blade leading edge lean and sweep by sweeping blade tip forward and backward

and sweeping blade root forward and backward along the meridional chord line. Firstly

the effects of blade leading edge sweep on the overall performance and flow field of a transonic centrifugal impeller are studied

and the results show that the blade tip forward sweep or blade root forward sweep can improve the highest isentropic efficiency and total pressure ratio of the centrifugal impeller; the blade tip backward sweep almost has no effect on the isentropic efficiency

but can decrease the total pressure ratio; the blade root backward sweep decreases both the isentropic efficiency and total pressure ratio. Additionally

the stall margin is increased by the blade tip forward sweep or blade root backward sweep

and reduced by the blade tip backward sweep or blade root forward sweep. Finally

the effect of blade leading edge sweep on a subsonic centrifugal impeller is investigated

and it indicates that

compared with transonic centrifugal impeller

the blade leading edge sweep has less effect on the isentropic efficiency and total pressure ratio in a subsonic centrifugal impeller. However

the effects on stall margin are almost the same for both transonic and subsonic centrifugal impellers. For an unshrouded transonic impeller

blade tip forward sweep is an effective way to increase its isentropic efficiency

pressure ratio and stall margin.

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references

王宏亮, 席光. 离心叶轮几何形变对气动性能的影响 [J]. 西安交通大学学报, 2009, 43(5): 46-50.

WANG Hongliang, XI Guang. Effect of geometrical deformation of the centrifugal impeller on the aerody-namic performance [J]. Journal of Xi'an Jiaotong University, 2009, 43(5): 46-50.

李学臣, 席光. 离心叶轮出口流动分离区影响因素的数值研究 [J]. 西安交通大学学报, 2013, 47(9): 16-22.

LI Xuechen, XI Guang. Numerical research on influence factors of flow separation near centrifugal impeller outlet [J]. Journal of Xi'an Jiaotong University, 2013, 47(9): 16-22.

HAH C, PUTERBAUGH S L, WAIDIA A R. Control of shock structure and secondary slow field inside transonic compressor rotors through aerodynamic sweep [C]∥International Gas Turbine and Aeroengine Congress and Exhibition. New York, USA: ASME, 1998: 98-GT-561.

WADIA A R, SZUCS P N, CRALL W W. Inner workings of aerodynamic sweep [C]∥International Gas Turbine and Aeroengine Congress and Exhibition. New York, USA: ASME, 1997: 97-GT-401.

JANG C M, SAMAD A, KIM K Y. Optimal design of swept, leaned and skewed blades in a transonic axial compressor [C]∥Proceedings of ASME Turbo Expo 2006: Power for Land, Sea, and Air. New York, USA: ASME, 2006: 1279-1288.

KRAIN H, HOFFMANN B. Flow study of a redesigned high pressure ratio centrifugal compressor [J]. Journal of Propulsion and Power, 2008, 24(5): 1117-1123.

GANESH S, NAGPURWAL Q H, BHASKAR D C S. Effect of leading edge sweep on the performance of a centrifugal compressor impeller [J]. Technical Journal of M. S. Ramaiah School of Advance Studies, 2010, 9(2): 55-62.

XU C, AMANO R S. Aerodynamic and structure considerations in centrifugal compressor design: blade lean effects [C]∥Turbine Technical Conference and Exposition. New York, USA: ASME, 2012: 2012-GT-68207.

RAINS D A. Tip clearance flow in axial flow compressor and pumps [D]. Los Angeles, California, USA: Califomia Institute of Technology, 1954.

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