应用改进的平行压气机模型预测旋流畸变对压气机性能的影响

推进技术 ›› 2016, Vol. 37 ›› Issue (8): 1485-1489.

应用改进的平行压气机模型预测旋流畸变对压气机性能的影响

胡伟波,程邦勤,陈志敏,王浩,李军

空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038,空军工程大学航空航天工程学院，陕西西安 710038

发布日期:2021-08-15
作者简介:胡伟波，男，硕士生，研究领域为推进系统气动热力理论与工程。

Prognostication for Effects of Swirl Distortion on Compressor Performance with Modified Parallel Compressor Model

Aeronautics and Astronautics Engineering College，Air Force Engineering University，Xi’an 710038，China,Aeronautics and Astronautics Engineering College，Air Force Engineering University，Xi’an 710038，China,Aeronautics and Astronautics Engineering College，Air Force Engineering University，Xi’an 710038，China,Aeronautics and Astronautics Engineering College，Air Force Engineering University，Xi’an 710038，China and Aeronautics and Astronautics Engineering College，Air Force Engineering University，Xi’an 710038，China

Published:2021-08-15

摘要/Abstract

摘要： 为预测旋流畸变对压气机性能的影响，采用改进的平行压气机模型探究了常见的整体涡和对称涡旋流畸变下压气机性能参数的变化。改进的平行压气机模型利用平均线模型获得输入进口条件下压气机各级的特性，将得到的级压比和温比等参数传递给平行压气机模型进行求解，进而得到完整的压气机特性。结果表明:同向整体涡作用下，压气机工作点压比降低，稳定裕度增大；反向整体涡使得压气机压比增加，稳定裕度减小；对称涡使得压气机压比降低，稳定裕度减小。以10°旋流为例，同向整体涡下压比的最大降幅达到15.2%，反向整体涡下压比的最大增幅为13.3%，对称涡下压比的最大降幅仅为4.6%。

关键词: 旋流畸变；平均线模型；平行压气机模型；整体涡；对称涡；压气机性能

Abstract: In order to predict performance of compressor with vortex distortion，an investigation of variation of compressor operating parameters under bulk vortex and twin vortex has been conducted applying modified parallel compressor model. Firstly，meanline model was used to obtain stage characteristics according to input inlet conditions，and then the stage pressure ratio and temperature ratio were passed to parallel compressor model. Finally，overall compressor performance map can be acquired by modified parallel compressor model. The results show that the compressor has lower pressure ratio and higher surge margin with co-rotating bulk vortex. However，the pressure ratio increases and surge margin decreases with counter-rotating bulk vortex. For twin vortex，the pressure ratio and surge margin decrease. Taking 10° vortex for example，the calculated maximum decrease in pressure ratio is 15.2% and 4.6% with co-rotating bulk vortex and twin vortex，respectively，and maximum increase in pressure ratio is 13.3% with counter-rotating bulk vortex.

Key words: Swirl distortion；Mealine model；Parallel compressor model；Bulk vortex；Paired vortex；Compressor performance

胡伟波,程邦勤,陈志敏,王浩,李军. 应用改进的平行压气机模型预测旋流畸变对压气机性能的影响[J]. 推进技术, 2016, 37(8): 1485-1489.

HU Wei-bo,CHENG Bang-qin,CHEN Zhi-min,WANG Hao,LI Jun. Prognostication for Effects of Swirl Distortion on Compressor Performance with Modified Parallel Compressor Model[J]. Journal of Propulsion Technology, 2016, 37(8): 1485-1489.

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