Numerical Prediction of Multi-Stage Axial Flow Compressor off-Design Performances

LIU Qian-zhi

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Numerical Prediction of Multi-Stage Axial Flow Compressor off-Design Performances

更新时间：2026-07-07

- Numerical Prediction of Multi-Stage Axial Flow Compressor off-Design Performances
- Vol. 19, Issue 1, (2004)
- 作者机构：
  
  西北工业大学动力与能源学院,陕西,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2004
- 稿件说明：
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LIU Qian-zhi. Numerical Prediction of Multi-Stage Axial Flow Compressor off-Design Performances[J]. 2004, 19(1).
DOI：

LIU Qian-zhi. Numerical Prediction of Multi-Stage Axial Flow Compressor off-Design Performances[J]. 2004, 19(1). DOI：

摘要

采用LU-SGS隐式解法以及叶排间掺混面模型数值模拟压气机三维粘性流动

研究了多级轴流压气机的设计与非设计状态性能的预估问题。对一台五级高压压气机进行了详细的流场数值计算

包括了设计转速的100%

90%及80%等多个转速及各种工作状态。结果表明

本文所建立的数值方法与计算机程序对多级轴流压气机各种非设计状态的计算都具有收敛容易和快速的优点

计算得到的压气机总性能和各分级性能与设计参数进行了对比

证明该方法和程序的预估结果是比较准确的。根据设计转速下的计算结果

预估了压气机设计点的喘振裕度。此外

还对不同状态下叶片进口气流角的变化进行了分析。

Abstract

The paper presents numerical predictions of design and off-design performance for multistage axial compressors.A time marching

implicit

finite-difference scheme was used to solve three-dimensional Reynolds-averaged Navier-Stokes equations.The shocks in transonic flow field are captured with a high resolution procedure.The turbulent viscosity is calculated using the two-layer Baldwin-Lomax algebraic turbulence model.Detailed computations were carried out for a five stage high-pressure compressor configuration for design and off-design conditions at 100%

90% and 80% corrected speeds.The mass flow rate convergences were obtained (smaller than 1%) at all these computations.The predicted results of stage and multistage performances at design operating point show a good agreement with the design.The surge margin at design operating point was estimated by the numerical results.The Maximum difference of stator blade inlet flow angles between design and off-design operating points is larger than 15 degrees at design speed.

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