Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors

TIAN Xiao-pei; SHAN Peng

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Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors

叶轮机械 | 更新时间：2026-07-07

- Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors
- Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors
- 航空动力学报 2013年28卷第7期
- 作者机构：
  
  School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics,Beijing,China,100191
- 作者简介：
- 基金信息：
  
  ProgrammeofIntroducingTalentsofDisciplinetoUniversities(B08009)ProgrammeofIntroducingTalentsofDisciplinetoUniversities(B08009)
- DOI：
  中图分类号：
- 纸质出版：2013
- 稿件说明：
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TIAN Xiao-pei, SHAN Peng. Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors[J]. 航空动力学报, 2013,28(7).

TIAN Xiao-pei, SHAN Peng. Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors[J]. 2013, 28(7).
TIAN Xiao-pei, SHAN Peng. Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors[J]. 航空动力学报, 2013,28(7). DOI：

TIAN Xiao-pei, SHAN Peng. Two 3-D multi-cascade co-design inverse methods based on streamline curvature approach and Clebsch formulation for single-stage centrifugal compressors[J]. 2013, 28(7). DOI：

摘要

Two strategies extended the single-cascade methods from a compressible three-dimensional inverse method for radial and mixed flow turbomachines to two three-dimensional multi-cascade co-design methods for single-stage centrifugal compressors.These two three-dimensional methods and a typical quasi-three-dimensional streamline curvature through-flow inverse method were employed to design the same subsonic high-speed single-stage centrifugal compressors.The compressor performances were simulated by a commercial Reynolds averaged Navier-Stokes (RANS) equations solver.The studies show that two three-dimensional co-design methods are reasonable and feasible.It was found that:firstly the blade camber angle designed by the three-dimensional methods was larger than that designed by the quasi-three-dimensional method;and secondly with regard to two three-dimensional methods with different boundary conditions

the co-design result differences between the diffusers were small

but those between the deswirlers were relatively large.

Abstract

the co-design result differences between the diffusers were small

but those between the deswirlers were relatively large.

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