Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets

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Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets

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- Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets
- Vol. 43, Issue 6, Pages: 123-128(2009)
- 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：
  CLC： TH452
- Online First：10 June 2009，
  
  Published：2009
- 稿件说明：
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Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets[J]. 2009, 43(6): 123-128.
DOI：

Numerical Investigation to Performance of Centrifugal Impeller with Vortex Generator Jets[J]. 2009, 43(6): 123-128. DOI：

摘要

采用数值计算方法

对带有漩涡发生器的离心叶轮内流动进行了研究

从宏观和微观角度说明了流体的可压缩性直接影响着流动分离的发生.将二倍转速下的离心叶轮作为研究对象

详细分析了漩涡发生器不同前缘距离(射流管距叶片前缘的距离)、射流管径、倾斜角度(前向倾斜角和侧向倾斜角)及射流流量等对流动控制性能设计的影响.结果表明

前缘距离和前向倾斜角对叶轮性能的影响不如射流管径、射流流量以及侧向倾斜角的影响大

最优参数组合时的效率和压比较原机分别提高了3.06%和4.09%.进一步研究发现

合理布置漩涡发生器能明显改善离心叶轮小流量工况时的性能

且有效扩大了其变工况范围.

Abstract

The flow performance of centrifugal impeller with vortex generator jets is investigated numerically

and the obvious effects of the fluid compressibility on flow separation is verified respectively from both macro and micro viewpoints. The effects of different forward distance(distance between the jet and the impeller vane)

different jet diameter

different inclined angles(including the injection angle and the yaw angle)and different injection flux on the flow separation control are evaluated. The numerical results show that the jet diameter

the yaw angle and the injection flux exert greater influence than the other two parameters. The efficiency and the pressure ratio of the impeller are increased by 3.06% and 4.09% via optimal design of vortex generator jets. And the performance of the centrifugal impeller at lower flow rate is improved and the working range is widened by the reasonable distributions of vortex generator jets.

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Keywords

references

WALLIS R A. The use of air jets for boundary layer control, Aerodynamics Note 110(N-34736)[R]. London,UK:Aeronautical Research Laboratories, 1952.

DAY I J. Active suppression of rotating stall and surge in axial compressors [J]. Journal of Turbomachinery, 1993, 115(1):40-47.

SKOCH G J. Experimental investigation of centrifugal compressor stabilization techniques [J]. Journal of Turbomachinery, 2003, 125(4):704-713.

SKOCH G J. Experimental investigation of diffuser hub injection to improve centrifugal compressor stability [J]. Journal of Turbomachinery, 2005, 127(1):107-117.

STEIN A. Computational analysis of stall and separation control in centrifugal compressors [D]. Atlanta, USA: School of Aerospace Engineering,Georgia Institute of Technology, 2000.

HATHAWAY M. Laser anemometer measurements of the three-dimensional rotor flow field in the NASA low-speed centrifugal compressor, TP-2527[R]. Washington,USA:NASA, 1995.

CHRISS R M, HATHAWAY M D, WOOD J R. Experimental and computational results from the NASA Lewis low speed centrifugal impeller at design and part-flow conditions [J]. Journal of Turbomachinery,1996, 118(1):55-65.

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