多级轴流压气机进气畸变模型研究

推进技术 ›› 2016, Vol. 37 ›› Issue (12): 2278-2287.

多级轴流压气机进气畸变模型研究

尹超,胡骏,严伟,郭晋

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:尹超，男，博士生，研究领域为叶轮机械气动热力学。
基金资助:
南京航空航天大学青年科技创新基金(NS2014021)。

Investigation of Multistage Axial Compressor Distortion Analysis Model

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究进气畸变对多级轴流压气机性能以及稳定性的影响，基于彻体力模型理论建立了一个模拟多级轴流压气机进气畸变的三维分析模型CSAC，并采用实验与CFD相结合的方法进行了验证。利用CSAC模型模拟了周向总压畸变对四级低速轴流压气机性能的影响。结果表明:均匀进气下CSAC与CFD计算特性最大误差不超过1.5%；进口总压畸变传递到第三级时畸变度衰减为0；在低压区的转子出口存在一个高总温畸变区，其强度在向下游传递中逐渐增强，到达第四级时总温最大升高0.4%；高总温影响区域在向下游发展中沿叶片转动方向逐渐扩张，造成压气机性能损失加大，最大总压比下降0.7%。所有结果均显示出CSAC模型是当前分析畸变对压气机性能影响的有力工具。

关键词: 多级轴流压气机；彻体力模型；进气畸变；畸变传递

Abstract: In order to analysis the effects of inlet-distortion on multistage axial compressors performance and stability，a three-dimensional analysis model called CSAC for multistage axial compressor was developed based on body-force model theory. CSAC model was validated by both measurements and CFD methods. The effects of inlet circumferential total pressure distortion on the four-stage compressor were analyzed using this model. The results show that the maximum error of both CSAC and CFD results under clean inlet is less than 1.5%. The inlet circumferential total pressure distortion decays rapidly to zero when it propagates to the third stage. A high total temperature distortion area appears at the exit of rotor，and the temperature increases by 0.4% when it spreads to the fourth stage. The affected region extends circumferentially along rotation direction，which causes more serious loss with 0.7% in total pressure ratio decrease. All results show that the CSAC model is a powerful distortion analysis tool for compressors in current time.

Key words: Multistage axial compressor；Body-force model；Inlet distortion；Distortion transfer

尹超,胡骏,严伟,郭晋. 多级轴流压气机进气畸变模型研究[J]. 推进技术, 2016, 37(12): 2278-2287.

YIN Chao,HU Jun,YAN Wei,GUO Jin. Investigation of Multistage Axial Compressor Distortion Analysis Model[J]. Journal of Propulsion Technology, 2016, 37(12): 2278-2287.

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