多级环境下径向总压畸变影响效应的试验评价

向宏辉; 侯敏杰; 葛宁; 吴森林; 杨荣菲

多级环境下径向总压畸变影响效应的试验评价

1.
中国航空工业集团公司中国燃气涡轮研究院,四川江油 621703
2.
南京航空航天大学能源与动力学院,南京 210016

基金项目: 国家APTD计划(APTD-0801); 航空科学基金(2008ZD24012)

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出版历程
- 收稿日期: 2011-07-07
- 刊出日期: 2012-06-28

Experimental evaluation of steady-state effect of inlet radial total pressure distortion under multistage environment

1.
China Gas Turbine Establishment, Aviation Industry Corporation of China,Jiangyou Sichuan 621703,China
2.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

摘要

摘要: 为量化评价径向总压畸变对多级轴流压气机气动性能的综合影响效应,将标准畸变模拟网与叶型探针技术相结合,开展了径向总压畸变对压气机性能与稳定性影响的试验研究.试验结果表明:径向总压畸变会轻度恶化压气机总体性能与稳定裕度,轮毂畸变与轮缘畸变对压气机性能的影响程度较为接近,而稳定裕度受轮缘畸变的影响要大于轮毂畸变,最大偏差达2%.两种径向总压畸变在压气机流道内均会迅速径向掺混,气流在强烈掺混过程中也将产生相应的压力损失.径向总压畸变会改变压气机原有级间负荷的分配,使某级的性能得到改善,该物理现象与转子攻角的变化范围相关联.
- 多级轴流压气机 /
- 径向总压畸变 /
- 气动性能 /
- 稳定裕度 /
- 级间匹配 /
- 试验研究
Abstract: In order to evaluate quantificationally the steady-state effect of inlet radial total pressure distortion on a highly loaded multistage axial compressor,the experimental investigation of two types of radial total pressure distortions including hub distortion and shroud distortion effects on the overall and stage performances of the compressor was performed using the pressure distortion mesh and the airfoil-probe technique.The experimental results indicate that both the radial total pressure distortions deteriorate slightly the overall performance and the stability margin of the compressor.The effect of shroud distortion on the overall performance parameters agrees well with hub distortion,while the stability margin loss caused by shroud distortion is larger than that caused by hub distortion(the maximum deviation is equal to 2%).The inlet radial non-uniform airflow mixes quickly in the flowpath of the compressor and produce the corresponding total pressure loss in the mixing process.In addition,both the inlet radial total pressure distortions affect the distribution of stage loading,which results in the improvement of one stage characteristic in comparison to that in the inlet uniform condition.The above physical phenomenon is relevant to the variation range of the attack angles of the rotor blade rows.
- multistage axial compressor /
- radial total pressure distortion /
- aerodynamic performance /
- stability margin /
- stage matching /
- experimental investigation

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参考文献(12)

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