某压气机静叶基元叶型优化设计及实验

李晓东; 钟兢军

doi:10.13224/j.cnki.jasp.2020.03.007

某压气机静叶基元叶型优化设计及实验

doi: 10.13224/j.cnki.jasp.2020.03.007

李晓东¹,
钟兢军²

基金项目: 国家自然科学基金重点项目（51436002）；中央高校基本科研业务费专项资金（3122019172）

计量
- 文章访问数: 434
- HTML浏览量: 4
- PDF量: 544
- 被引次数: 0
出版历程
- 收稿日期: 2019-09-04
- 刊出日期: 2020-03-28

Optimum design and experiment of stator blade profile of a compressor

LI Xiaodong¹,
ZHONG Jingjun²

1.
School of Airworthiness,Civil Aviation University of China,Tianjin 300300,China
2.
Merchant Marine College,Shanghai Maritime University,Shanghai 201306,China

摘要

摘要: 为了得到更加适合压气机静叶的叶型以降低气动损失,提取了静叶中径处的叶型,通过平面叶栅实验获得了原叶型的损失特性,发现原叶型气动损失较高,需要通过合理匹配设计参数来降低损失。为此,搭建数值优化平台在约束空间内搜寻气动损失更低的叶型,目标函数的构建综合考虑了多个冲角下的总压损失系数以提升叶片的变工况性能。优化结果显示：目标函数值降低了约9%,进一步实验研究发现,在实验涉及的整个马赫数和冲角范围内优化叶型比原叶型具有更低的总压损失系数,设计工况总压损失系数较原型叶型下降了31.3%,提升了叶型在正冲角边界附近的抗失速能力,设计进口马赫数正4°冲角下气流折转角增加1°。通过对实验结果的深入分析,解释了叶型性能提升的机理,对工作在相似环境的叶型设计及多目标优化方向给出了建议。
- 多目标优化 /
- 静叶 /
- 叶型 /
- 平面叶栅实验 /
- 总压损失系数 /
- 压气机
Abstract: In order to obtain a more suitable blade profile for compressor stator to reduce aerodynamic loss, the blade profile at mid-span of stator was extracted. The loss characteristics of the original blade profile were obtained through linear cascade experiment, finding that the aerodynamic loss of original blade profile was relatively high, making it necessary to match the design parameters properly to reduce the loss. For this reason, a numerical optimization platform was built to search for blade profile with lower aerodynamic loss in constrained design space. The objective function was constructed by taking the total pressure loss coefficient at multiple incidence angles into account to improve the design and off-design performance. The optimization results showed that, the value of objective function was reduced by about 9%. Further experimental studies showed that the optimized blade profile had lower total pressure loss coefficient than the original one in the whole Mach numbers and incidence angles involved in the experiment. The total pressure loss coefficient in the design condition was reduced by 31.3% compared with the original one, and the stall resistance capacity of the blade profile near positive incidence angle boundary was improved, the airflow inflection angle increased by 1° at the design inlet Mach number with an incidence angle of 4°. The mechanism of blade profile performance improvement was explained through in-depth analysis of experimental results, and suggestions for the design and multi-objective optimization of blade profiles working in similar environment were given.
- multi-objective optimization /
- stator /
- blade profile /
- linear cascade experiment /
- total pressure loss coefficient /
- compressor

HTML

参考文献(20)

[1]	KOCH C,SMITH L.Loss sources and magnitudes in compressors［J］.Journal of Engineering for Power,1976,98(2):411-416.
[2]	DENTON J.Loss mechanisms in turbomachines［J］.Journal of Turbomachinery,1993,115(4):621-656.
[3]	ERWIN J R,SAVAGE M,EMERY J C.Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading［R］.NACA-TN-3817,1956.
[4]	CARTER A D S,HOUNSELL A F.General performance data for aerofoils having c1,c2 or c4 base profiles on circular arc camber lines［R］.British NGTE-M62,1949.
[5]	HOBBS D E,WEINGOLD H D.Development of controlled diffusion airfoils for multistage compressor application［J］.Journal of Engineering for Gas Turbines and Power,1984,106(2):271-278.
[6]	RECHTER H,STEINERT W,LEHMANN K.Comparison of controlled diffusion airfoils with conventional NACA 65 airfoils developed for stator blade application in a multistage axial compressor［J］.Journal of Engineering for Gas Turbines and Power,1985,107(2):494-498.
[7]	魏巍,刘波,杜炜，等.可控扩散叶型与双圆弧叶型实验对比研究［J］.推进技术,2017,38(1):61-68. WEI Wei,LIU Bo,DU Wei,et al.Experimental comparison of controlled diffusion airfoils with double circle airfoils［J］.Journal of Propulsion Technology,2017,38(1):61-68.(in Chinese)
[8]	SIEVERDING F,RIBI B,CASEY M,et al.Design of industrial axial compressor blade sections for optimal range and performance［J］.Journal of Turbomachinery,2004,126(2):323-331.
[9]	SANGER N L.The use of optimization techniques to design-controlled diffusion compressor blading［J］.Journal of Engineering for Power,1983,105(4):256-264.
[10]	SONODA T,YAMAGUCHI Y,ARIMA T,et al.Advanced high turning compressor airfoils for low reynolds number condition:Part Ⅰ design and optimization［J］.Journal of Turbomachinery,2004,126(3):350-359.
[11]	SCHREIBER H,STEINERT W,SONODA T,et al.Advanced high turning compressor airfoils for low Reynolds number condition:Part Ⅱ experimental and numerical analysis［J］.Journal of Turbomachinery,2004,126(4):482-492.
[12]	KOLLER U,MONIG R,KUSTERS B,et al.Development of advanced compressor airfoils for heavy-duty gas turbines:Part Ⅰ design and optimization［R］.ASME Paper GT-1999-95,1999.
[13]	JIANG Bin,ZHENG Qun,ZHANG Hai,et al.Advanced axial compressor airfoils design and optimization［R］.ASME Paper GT2015-43846,2015.
[14]	BRIASCO G,BRUNA D,CRAVERO C,et al.A NURBS-based optimization tool for axial compressor cascades at design and off-design conditions［R］.ASME Paper GT2008-50622,2008.
[15]	SAFARI A,YOUNIS A,WANG G.Development of a metamodel assisted sampling approach to aerodynamic shape optimization problems［J］.Journal of Mechanical Science and Technology,2015,29(5):2013-2024.
[16]	周正贵,邱名,徐夏,等.压气机/风扇二维叶型自动优化设计［J］.航空学报,2011,32(11):1987-1997. ZHOU Zhenggui,QIU Ming,XU Xia,et al.Automatic optimization design of compressor/fan 2D blade profiles［J］.Acta Aeronautica et Astronautica Sinica,2011,32(11):1987-1997.(in Chinese)
[17]	徐全勇,阙晓斌,吴锋.可控扩散叶型的扩稳优化［J］.航空动力学报,2017,32(7):1762-1768. XU Quanyong,QUE Xiaobin,WU Feng.Aerodynamic stability optimization of controlled diffusion airfoil［J］.Journal of Aerospace Power,2017,32(7):1762-1768.(in Chinese)
[18]	成金鑫,向航,陈江.基元叶栅攻角特性多目标优化［J］.航空动力学报,2017,32(12):3064-3072. CHENG Jinxin,XIANG Hang,CHEN Jiang.Multi-objective optimization of incidence features for cascade［J］.Journal of Aerospace Power,2017,32(12):3064-3072.(in Chinese)
[19]	李晓东,钟兢军,高宇.高负荷压气机静叶根部叶型气动性能试验研究［J］.推进技术,2017,38(3):581-587. LI Xiaodong,ZHONG Jingjun,GAO Yu.Experimental investigation on performance of a profile at cascade hub in a high load compressor stator［J］.Journal of Propulsion Technology,2017,38(3):581-587.(in Chinese)
[20]	钟兢军,李晓东,高宇.跨声速级不同转速下静叶的损失特性［J］.航空动力学报,2017,32(9):2243-2252.