一种槽道式处理机匣的准定常流动模型Ⅰ: 建模方法及验证

宁方飞; 樊琳

一种槽道式处理机匣的准定常流动模型Ⅰ: 建模方法及验证

宁方飞,
樊琳

北京航空航天大学能源与动力工程学院,北京 100191

基金项目: 国家自然科学基金(50506001)

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出版历程
- 收稿日期: 2012-02-16
- 刊出日期: 2012-06-28

Quasi-steady flow model of slot-type casing treatments Ⅰ: modeling method and validation

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 为降低对槽道式处理机匣流动进行模拟的计算量,特别地,为了提供一种可用于处理机匣工程设计的快速评估手段,基于对带有槽道式处理机匣的压气机非定常流动物理的理解,提出了一种处理机匣的准定常流动模型,并利用带有处理机匣的跨声压气机转子实验测量结果,以及非定常数值模拟结果对所提出的模型进行了验证.结果表明:处理机匣流动模型很好地预测了由于采用处理机匣所取得的转子失速裕度的提高,并且与非定常模拟结果比较,流动模型对转子主流以及处理机匣内部流动模拟的准确性也能得到保证.采用处理机匣流动模型所需的计算量仅约为非定常模拟的1%,这保证了提出的模型可用于快速评估槽道式处理机匣的气动特性,从而为其工程优化设计提供了有效的手段.
- 航空发动机 /
- 轴流压气机 /
- 处理机匣 /
- 数值模拟 /
- 流动模型
Abstract: In order to predict more efficiently the compressor flow with slot-type casing treatment as well as to provide a computationally efficient tool for the design optimization of casing treatment,a quasi-steady flow model of the slot-type casing treatment flows was developed based on the understanding of the unsteady flow physics of the rotor-casing treatment combination.The new model has been coded up and validated against a slot-type casing treatment which was examined by experiment and unsteady RANS(Reynolds-averaged Navier-Stokes) calculations.Results show that the developed model predicts the extension of the rotor stall margin due to the application of the casing treatment quite well.Moreover,as compared to the unsteady simulation results,the model well reproduces the flow field in both the rotor passage and the casing treatment.The computational expenses using the flow model is just about 1% of that using unsteady simulations.This ensures that the model can be used to give fast prediction of the aerodynamic characteristics of a compressor with slot-type casing treatment,and the design and optimization of casing treatment are thus readily applicable.
- aero-engine /
- axial compressor /
- casing treatment /
- numerical simulation /
- flow model

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参考文献(20)

[1]	Prince D C,Jr.,Wisler D C,Hilvers D E.A study of casing treatment stall margin improvement phenomena .NASA-CR-134552,1974.
[2]	Takata H,Tsukuda Y.Stall margin improvement by casing treatment:its mechanism and effectiveness[J].Journal of Engineering for Power,1977,99(1):121-133.
[3]	Fujita H,Takata H.A study of configurations of casing treatment for axial flow compressors[J].Bulletin of the JSME,1984,27(230):1675-1681.
[4]	Smith G D J,Cumpsty N A.Flow phenomena in compressor casing treatment[J].ASME Journal of Engineering for as Turbines and Power,1984,106(3):532-541.
[5]	Cheng P,Prell M E,Greitzer E M,et al.Effects of compressor hub treatment on stator stall margin and performance[J].Journal of Aircraft,1984,21(7):469-475.
[6]	庄平,陆亚钧.机匣处理对压气机性能和气流结构影响的试验研究[J].航空学报,1986,7(4):363-370. ZHUANG Ping,LU Yajun.The effect of casing treatment on the performance and flowfield in axial compressors[J].Acta Aeronautica et Astronautica Sinica,1986,7(4):363-370.(in Chinese)
[7]	Lee N K W,Greitzer E M,Effects of endwall suction and blowing on compressor stability enhancement[J].Journal of Turbomachinery,1990,112(1):133-144.
[8]	Hall E J,Heidegger N J,Delaney R A.Performance prediction of endwall treated fan rotors with inflow distortion .AIAA-1996-244,1996.
[9]	Yang H,Nuernberger D,Nicke E,et al.Numerical investigation of casing treatment mechanisms with a conservative mixed-cell approach .ASME Paper GT-2003-38483,2003.
[10]	Wilke I,Kau H P.A numerical investigation of the flow mechanisms in a high pressure compressor front stage with axial slots[J].Journal of Turbomachinery,2004,126(3):339-349.
[11]	Crook A J.Numerical investigation of endwall casing treatment flow phenomena .GTL Report No.200,1989.
[12]	Hall E J,Crook A J,Delaney R A.Aerodynamic analysis of compressor casing treatment with a 3-D Navier-Stokes solver .AIAA Paper 94-2796,1994.
[13]	Wilke I,Kau H P.A numerical investigation of the influence of casing treatments on the tip leakage flow in a hpc front stage .ASME Paper GT-2002-30642,2002.
[14]	NING Fangfei,XU Liping.Aerodynamics of compressor casing treatment PartⅡ:a quasi-steady model for casing treatment flows .ASME Paper GT2008-51542,2008.
[15]	Denton J D.Loss mechanisms in turbomachines[J].Journal of Turbomachinery,1993,115(4):621-656.
[16]	宁方飞.考虑真实几何复杂性的跨声压气机内部流动的数值模拟 .北京: 北京航空航天大学,2002. NING Fangfei.Numerical simulation of the transonic compressor inner flow considering real geometrical complexity .Beijing:Beijing University of Astronautics and Aeronautics,2002.(in Chinese)
[17]	Edwards J R.A low-diffusion flux-splitting scheme for navier-stokes calculations[J].Computer & Fluids,1997,26(6):635-659.
[18]	NING Fangfei,XU Liping.Numerical investigation of transonic compressor rotor flow using an implicit 3d flow solver with one-equation Spalart-Allmaras turbulence model .ASME Paper 2001-GT-0359,2001.
[19]	Jameson A.Time dependent calculation using multigrid with applications to unsteady flows past airfoils and wings .AIAA Paper 91-1596,1991.
[20]	NING Fangfei,XU Liping.A solver using newton's method for unsteady viscous flows[J].Acta Mechanica Sinica,2003,19(3):220-227.