Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion

SHI Ya-feng; WU Hu; HUANG Jian; YANG Jin-guang

Chinese

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Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion

更新时间：2026-07-07

- Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion
- Vol. 27, Issue 3, (2012)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
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SHI Ya-feng, WU Hu, HUANG Jian, et al. Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion[J]. 2012, 27(3).
DOI：

SHI Ya-feng, WU Hu, HUANG Jian, et al. Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion[J]. 2012, 27(3). DOI：

摘要

以跨声速压气机NASA转子11为原型进行前掠改进

对得到的前掠转子与原型转子内流场进行了定常数值模拟

结果表明:在设计转速下前掠转子的性能有所提高

尤其是近失速流量有明显的降低.在周向总压畸变进气条件下

对转子11和前掠转子进行了非定常数值模拟

两者的性能较均匀进气条件下都出现了不同程度的下降

但前掠转子的近失速流量仍明显低于转子11

这是因为转子11叶尖区域处气流较前掠转子更易堵塞.

Abstract

A forward swept rotor was produced on the basis of transonic compressor NASA rotor 11 original geometry.The steady flow fields of this forward swept rotor and rotor 11 have been numerically simulated under design rotation speed

which shows that the performance of forward swept rotor especially the stall margin has been improved.The unsteady simulation of the flow fields of forward swept rotor and rotor 11 indicates that the inlet circumferential total pressure distortion has caused the deterioration of performance.However the forward swept rotor has lower mass flow near stall point compared with the original rotor 11 under the inlet circumferential pressure distortion

because the flow field near the blade tip region benefits from the forward swept rotor.

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