三元叶片型面造型对离心压缩机叶轮气动性能影响的数值研究

孙晔晨 1; 田玉宝 1; 2; 席光 1; 王志恒 1; 赵会晶 1; 樊宏周 1

doi:10.7652/xjtuxb201511022

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三元叶片型面造型对离心压缩机叶轮气动性能影响的数值研究

更新时间：2025-07-09

- 三元叶片型面造型对离心压缩机叶轮气动性能影响的数值研究
- Numerical Research on Effect of 3-D Blade Surface Profiles on Aerodynamic Performance of Centrifugal Compressor Impellers
- 西安交通大学学报 2015年49卷第11期页码：135-141
- 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：
  
  : 2015-01-06。作者简介: 孙晔晨(1991-),男,硕士生;席光(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金资助项目(51236006)
- DOI：10.7652/xjtuxb201511022
  中图分类号： O354.1
- 网络首发：2015-11-10，
  
  纸质出版：2015
- 稿件说明：
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孙晔晨 1, 田玉宝 1, 2, 等. 三元叶片型面造型对离心压缩机叶轮气动性能影响的数值研究[J]. 西安交通大学学报, 2015,49(11):135-141.

Numerical Research on Effect of 3-D Blade Surface Profiles on Aerodynamic Performance of Centrifugal Compressor Impellers[J]. 2015, 49(11): 135-141.
孙晔晨 1, 田玉宝 1, 2, 等. 三元叶片型面造型对离心压缩机叶轮气动性能影响的数值研究[J]. 西安交通大学学报, 2015,49(11):135-141. DOI： 10.7652/xjtuxb201511022.

Numerical Research on Effect of 3-D Blade Surface Profiles on Aerodynamic Performance of Centrifugal Compressor Impellers[J]. 2015, 49(11): 135-141. DOI： 10.7652/xjtuxb201511022.

摘要

以某一离心压缩机中的任意曲面叶轮为研究对象

将其“直纹面化”以降低制造成本

同时研究发现

直纹面化处理后任意空间曲面三元叶轮的气动性能下降。为了提升直纹面叶轮的气动性能

通过设计8+1套改型设计方案、调整叶片型线控制点、改变叶片前缘及尾缘坐标

并借助流体计算软件Numeca进行了数值模拟

由此求得了性能曲线及内部流场。结果显示:当直纹面叶轮叶片进口安装角扩大时

气动性能明显下降

反之亦然; 当直纹面叶轮叶片出口安装角扩大时

压比的提升较为明显

叶片出口安装角缩小时

效率的改善更为显著; 综合改进叶片前缘与尾缘的型线

可使直纹面叶轮的气动性能显著提高。研究表明

直纹面叶轮气动性能对叶片型线变化非常敏感

通过适当地改进型线可以有效提升直纹面叶轮的气动性能

使之不低于原任意曲面叶轮的气动性能。

Abstract

A centrifugal compressor impeller with arbitrary curved surface is analyzed. The surface is transformed into ruled surface for the purpose of reducing manufacture costs

however the transformation leads to a worse aerodynamic performance. To improve the performance of impeller with ruled surface

8+1 sets of schemes are designed by changing control points of shape lines of leading edge and/or trailing edge

and the internal flow field and performance curves are evaluated by commercial CFD software Numeca. The aerodynamic performance worsens when the inlet blade angle increases and vice versa. The pressure ratio rises more considerably as the outlet blade angle increases

while the efficiency is improved more obviously as the outlet blade angle decreases. The integrated method combines the results from the changing of both leading and trailing edges to effectively enhance the aerodynamic performance. This approach indicates that the impeller with ruled surface is very sensitive to the modification of shape lines

and the aerodynamic performance of the appropriately modified impeller with ruled surface can be comparable with that of impeller with arbitrary curved surface.

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Keywords

references

HU Chuangguo, ZHENG Junjun, ZUO Pingying, et al. A study on integrated milling process of shrouded impeller [C]∥Proceedings of ASME Turbo Expo. New York, USA: ASME, 2014: 22A008.

WILLIAM T, LEI Yu, JACQUELYNN G, et al. Test and simulation of the effects of surface roughness on a shrouded centrifugal impeller [C]∥Proceedings of ASME Turbo Expo. New York, USA: ASME, 2014: 42A012.

BI Qingzhen, CHEN Hua, ZOU Xueqi, et al. Five-axis flank milling for design and manufacture of turbocharger compressor impeller [C]∥Proceedings of ASME Turbo Expo. New York, USA: ASME, 2014: 24A001.

陈力. 自由曲面直纹化方法以及在五轴侧铣加工中的应用 [D]. 上海: 上海交通大学, 2013.

WU C Y. Arbitrary surface flank milling and flank sam and manufacturing of jet engine and compressor airfoils [C]∥Proceedings of ASME Turbo Expo. New York, USA: ASME, 2012: 21-30.

LIANG Quan, WANG Yongzhang, FU Hongya, et al. Cutting path planning for ruled surface impellers [J]. Chinese Journal of Aeronautics, 2008, 21(5): 462-471.

ZHOU Y, SCHULZE J, SCHAFFLER S. Blade geometry design with kinematic ruled surface approximation [C]∥Proceedings of the 2010 ACM Symposium on Applied Computing. New York, USA: ACM, 2010: 1266-1267.

高丽敏, 刘波, 王欢. 无叶扩压器对离心压缩机流场及性能影响的数值研究 [J]. 中国机械工程, 2008, 19(17): 2098-2102.

GAO Limin, LIU Bo, WANG Huan. Numerical investigation of the influence of vaneless diffusers on the flow and performance of a centrifugal compressor [J]. China Mechanical Engineering, 2008, 19(17): 2098-2102.

王晓峰. 基于三维粘性流场分析的离心压缩机叶轮近似模型优化设计 [D]. 西安: 西安交通大学, 2005.

PEKKA R, AKI G, AHTI J, et al. Effects of different blade angle distributions on centrifugal compressor performance [J/OL]. International Journal of Rotating Machinery, 2009: 1-9. [2014-12-10]. doi: 10.1155/2009/537802

BONAIUTI D, ARNONE A, ERMINI M, et al. Analysis and optimization of transonic centrifugal compressor impellers using the design of experiments technique [J]. ASME Journal of Turbomachinery, 2002, 6: 1089-1098.

初雷哲, 杜建一, 黄典贵, 等. 离心压气机叶片前缘几何形状对性能的影响 [J]. 工程热物理学报, 2008, 29(5): 767-769.

CHU Leizhe, DU Jianyi, HUANG Diangui, et al. Effect of the blade leading edge on the performance of a centrifugal compressor [J]. Journal of Engineering Thermophysics, 2008, 29(5): 767-769.

姜华, 宫武旗, 张炜, 等. 带分流叶片离心叶轮非定常流场的实验研究 [J]. 西安交通大学学报, 2009, 43(9): 14-18.

JIANG Hua, GONG Wuqi, ZHANG Wei, et al. Ex-perimental investigation of the unsteady discharge flow in a centrifugal impeller with splitter blades [J]. Journal of Xi'an Jiaotong University, 2009, 43(9): 14-18.

HILDEBRANDT A, GENRUP M. Numerical investigation of the effect of different back sweep angle and exducer width on the impeller outlet flow pattern of a centrifugal compressor with vaneless diffuser [J]. ASME Journal of Turbomachinery, 2007, 129(2): 421-433.

卢佳玲. 跨音风扇级轴向倾斜槽机匣扩稳效果的数值研究 [J]. 西北工业大学学报, 2009, 27(6): 846-853.

LU Jialing. Numerically simulating effect of location of slot of axial-and-skewed slot casing treatment on extending the stage stable operating range [J]. Journal of Northwestern Polytechnical University, 2009, 27(6): 846-853.

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