不同顶部间隙对跨声风扇转子的影响分析

刘建勇; 袁巍; 周盛; 陆亚钧

不同顶部间隙对跨声风扇转子的影响分析

北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室, 北京 100083

基金项目: 国家自然科学基金(50476003)

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出版历程
- 收稿日期: 2006-11-15
- 修回日期: 2007-01-23
- 刊出日期: 2007-11-28

Analysis for influence of different tip clearance on transonic fan rotor

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 为研究跨声压气机叶尖间隙流动对性能影响的特征,数值计算了某高负荷跨声风扇转子在种等高间隙和两种阶梯间隙结构下的性能.通过对总体性能参数和叶尖区静压、周向速度、熵等细节参数的分析,认为叶尖前段间隙流比后段间隙流对压气机性能的影响更大.其中,涡波干涉对于前段间隙流带来的危害尤为重要.比较阶梯间隙的计算结果,验证了这一推断.
- 航空、航天推进系统 /
- 跨声压气机 /
- 叶尖间隙 /
- 涡波干涉
Abstract: In order to study the influence of tip clearance flow on the performance of a transonic compressor,a high-load transonic fan's rotor with five constant width clearances and two step-clearances were numerically simulated.After analysis of the overall performance parameters and the detailed flow parameters including the static pressure,circumferential velocity and entropy,it is concluded that the front part clearance flow has greater influence on the compressor than the back part clearance flow.In particular,the vortex-shock interference may worsen the front part clearance flow,as demonstrated by comparing the simulation of two step-clearances.
- aerospace propulsion system /
- transonic compressor /
- tip clearance /
- vortex-shock interference

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参考文献(8)

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