Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip

SHAO Wei-wei; JI Lu-cheng; HUANG Wei-guang

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Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip

更新时间：2026-07-07

- Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip
- Vol. 23, Issue 2, (2008)
- 作者机构：
  
  1. 中国科学院工程热物理研究所,北京,100080
  2. 中国科学院研究生院,北京,100080
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2008
- 稿件说明：
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SHAO Wei-wei, JI Lu-cheng, HUANG Wei-guang. Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip[J]. 2008, 23(2).
DOI：

SHAO Wei-wei, JI Lu-cheng, HUANG Wei-guang. Analysis of overall aerodynamic performance of axial-flow compressor with attenuated blade tip[J]. 2008, 23(2). DOI：

摘要

以ROTOR3转子为例

采用数值模拟方法对叶尖压力面片削深度(沿叶片切向)及高度(沿叶片展高方向)进行参数化研究.计算得到60%

80%

90%及100%设计转速工况下的全工况特性曲线

并对100%设计转速工况作了详细的内部流场分析.包括原型在内10种模型计算结果表明:在0～50%片削深度和82%～100%展高内片削使ROTOR3转子堵塞流量、总压比、绝热效率略有提高

失速裕度略有下降

但影响并不十分显著.

Abstract

Parameter studies for different attenuation thickness(in the tangential direction of blade) and relative height(in the spanwise direction of blade) of pressure surface at tip region are developed

which take ROTOR37 as an example and adopt numerical simulation to obtain the results.Aerodynamic performance curves are obtained at 60%

80%

90% and 100% of design rotate speed working conditions

moreover

detailed analysis of internal flow field is presented for design condition.Results of ten models including the model with unchanged blade element indicate that blade tip attenuation within certain range can advance choke mass flow

total pressure ratio and adiabatic efficiency

and decrease stall margin of the rotor

however

the influence is not so patent.

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Related Author

SHAO Wan-ren

BIAN Lei

YAN Ze-Xiang

ZOU Zheng-ping

ZHU Fang

CHEN Yun-yong

WEI Fei-fei

JIN Dong-hai

Related Institution

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China

National Key Laboratory of of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics

Department of System Engineering, China Aerospace Science and Technology Corporation

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics

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