压气机角区失速预测模型的改进与实验验证

doi:10.13675/j.cnki.tjjs.190106

推进技术 ›› 2020, Vol. 41 ›› Issue (3): 527-536.DOI: 10.13675/j.cnki.tjjs.190106

压气机角区失速预测模型的改进与实验验证

刘宝杰^1,2,3,邱迎¹,于贤君^1,2,3,安广丰^1,2,3

1.北京航空航天大学能源与动力工程学院，北京100191;2.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国家级重点实验室，北京100191;3.先进航空发动机协同创新中心，北京100191

发布日期:2021-08-15
作者简介:刘宝杰，博士，教授，研究领域为叶轮机气动热力学。E-mail:liubj@buaa.edu.cn
基金资助:
国家自然科学基金（51790511；51476004）。

Improvement of Criterion for Prediction of Axial CompressorCorner Stall and Its Experimental Verification

1.School of Energy and Power Engineering,Beihang University,Beijing100191,China;2.National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing100191,China;3.Collaborative Innovation Center of Advanced Aero-Engine,Beijing100191,China

Published:2021-08-15

摘要/Abstract

摘要： 角区分离普遍存在于压气机中，随着负荷的提升，角区分离可能发展为角区失速，导致流动的堵塞与损失显著增大。前人基于二维叶栅，提出了预测叶片角区失速的模型，但这些模型并没有考虑到真实压气机环境中流动的强三维性。本文在现有模型基础上，一方面对其进行改进，以考虑压气机中流动具有强三维性的影响；另一方面，利用低速压气机实验台上获得的大量实验数据对现有模型和改进后的模型进行校验。结果表明：在真实压气机中，现有的准则不再可行；而基于改进后的模型，存在一个临界参数，能够准确判断静子根部角区分离和角区失速；另外，改进后的参数与静子根部端区流动影响范围内的堵塞和损失存在很强的关联。

关键词: 角区分离;角区失速;角区失速预测模型;轴流压气机

Abstract: Endwall corner separation is a typical secondary flow in axial compressor. With the increase of blade loading, the corner separation flow could develop into corner stall flow, which could cause serious flow blockage and loss in compressor blade passage and should be avoided during the compressor design procedure. In order to predict the corner stall flow in compressors, some criterions has been developed， which are mainly based on two-dimensional airfoil data. The endwall flow is strong three-dimensional in real compressor environment. A new criterion is developed accordingly in the present paper. The newly developed criterion was verified by experimental data obtained from low-speed compressor tests. The results showed that the existed criterions do not work well in real compressor environment and the newly developed criterion could accurately predict the stator hub corner stall in compressors with a critical value of. In addition, the newly developedD parameter shows related correlation to the flow loss and blockage in compressor stators.

刘宝杰,邱迎,于贤君,安广丰. 压气机角区失速预测模型的改进与实验验证[J]. 推进技术, 2020, 41(3): 527-536.

LIU Bao-jie^1,2,3,QIU Ying¹,YU Xian-jun^1,2,3,AN Guang-feng^1,2,3. Improvement of Criterion for Prediction of Axial CompressorCorner Stall and Its Experimental Verification[J]. Journal of Propulsion Technology, 2020, 41(3): 527-536.

参考文献

[1] Cumpsty N A.Compressor Aerodynamics[M].Harlow:Longman Scientific & Technical,1989.
[2] Gbadebo S A，Cumpsty N A，Hynes T P.Three-Dimensional Separations in Axial Compressors[J].Journal of Turbomachinery，2005，127(2):331-339.
[3] Lei V M，Spakovszky Z S，Greitzer E M.A Criterion for Axial Compressor Hub-Corner Stall[J].Journal of Turbomachinery，2008，130(3).
[4] Taylor J V，Miller R J.Competing Three-Dimensional Mechanisms in Compressor Flows[J].Journal of Turbomachinery，2016，138(2).
[5] Joslyn H D，Dring R P.Axial Compressor Stator Aerodynamics[J].Journal of Engineering for Gas Turbines & Power，1984，106(2).
[6] Schulz H D，Gallus H D.Experimental Investigation of the Three-Dimensional Flow in an Annular Compressor Cascade[J].Journal of Turbomachinery，1988，110(4):467-478.
[7] Dong Y，Gallimore S J，Hodson H P.Three-Dimensional Flows and Loss Reduction in Axial Compressors[J].Journal of Turbomachinery，1987，109(3):354-361.
[8] Gbadebo S A，Cumpsty N A，Hynes T P.Interaction of Tip Clearance Flow and Three-Dimensional Separations in Axial Compressors[J].Journal of Turbomachinery，2006，128(4):71-78.
[9] Breugelmans F A H，Carels Y，Demuth M.Influence of Dihedral on the Secondary Flow in a Two-Dimensional Compressor Cascade[J].Journal of Engineering for Gas Turbines & Power，1984，106(3):578-584.
[10] Weingold H D，Neubert R J，Behlke R F，et al.Reduction of Compressor Stator Endwall Losses Through the Use of Bowed Stators[R].ASME 95-GT-380.
[11] Peacock R E.Boundary Layer Suction to Eliminate Corner Separation[R].NACA-RM-3663，2017.
[12] Gbadebo S A，Cumpsty N A，Hynes T P.Control of Three-Dimensional Separations in Axial Compressors by Tailored Boundary Layer Suction[J].Journal of Turbomachinery，2008，130(1):125-128.
[13] Nerger D，Saathoff H，Radespiel R，et al.Experimental Investigation of Endwall and Suction Side Blowing in a Highly Loaded Compressor Stator Cascade[J].Journal of Turbomachinery，2010，132(2):255-267.
[14] Lieblein S，Schwenk F C，Broderick R L.Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial-Flow-Compressor Blade Elements[R].NACA-RM-E53D01，1953.
[15] Dean R C.Secondary Flow in Axial Compressors[R].Massachusetts:Massachusetts Institute of Technology，1954.
[16] Yu X，Liu B.A Prediction Model for Corner Separation/Stall in Axial Compressors[R].ASME GT-2010-22453.
[17] Liu B，An G，Yu X，et al.Experimental Investigation of the Effect of Rotor Tip Gaps on 3D Separating Flows inside the Stator of a Highly Loaded Compressor Stage[J].Experimental Thermal and Fluid Science，2016，75（2）:96-107.
[18] Du Hui，Yu Xianjun，Zhang Zhibo，et al.Relationship Between the Flow Blockage of Tip Leakage Vortex and Its Evolutionary Procedures Inside the Rotor Passage of a Subsonic Axial Compressor[J].Journal of Thermal Science，2013，22(6):522-531.
[19] 刘宝杰，张帅，于贤君，等.单级低速模拟轴流压气机实验台改进设计[J].航空动力学报，2018，33(7):1665-1675.
[20] Liu B，An G，Yu X.Assessment of Curvature Correction and Reattachment Modification into the Shear Stress Transport Model Within the Subsonic Axial Compressor Simulations[J].Proceedings of the Institution of Mechanical Engineers，Part A: Journal of Power and Energy，2015，229(8):910-927.
[21] Yu X，Liu B，Jiang H.Characteristics of the Tip Leakage Vortex in a Low-Speed Axial Compressor[J].AIAA Journal，2007，45(4):870-878.

压气机角区失速预测模型的改进与实验验证

Improvement of Criterion for Prediction of Axial CompressorCorner Stall and Its Experimental Verification

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价