跨声串列转子及前后排叶片匹配特性分析

doi:CNKI:11-1929/V.20100330.1304.001

流体力学与飞行力学

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跨声串列转子及前后排叶片匹配特性分析

赵斌, 刘宝杰

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防科技重点实验室, 北京 100191

收稿日期:2010-06-09 修回日期:2010-11-22 出版日期:2011-06-25 发布日期:2011-06-24
通讯作者: Tel.: 010-82316419 E-mail: liubj@buaa.edu.cn E-mail:liubj@buaa.edu.cn
作者简介:赵斌(1983- ) 男,博士研究生。主要研究方向:高负荷风扇气动设计方法。 Tel: 010-82338139-812 E-mail: IHPTET@163.com 刘宝杰(1971- ) 男,博士,教授,博士生导师。主要研究方向:压气机设计及其内部复杂流场。 Tel: 010-82316419 E-mail: liubj@buaa.edu.cn

Analysis of Transonic Tandem Rotor and Matching Characteristic of Forward and Aft Blades

ZHAO Bin, LIU Baojie

National Key Laboratory of Science and Technology on Aero-thermoengines, School of Jet Propulsion, Beihang University, Beijing 100191, China

Received:2010-06-09 Revised:2010-11-22 Online:2011-06-25 Published:2011-06-24

摘要/Abstract

摘要： 在叶尖折合切线速度为381 m/s的条件下,利用跨声串列转子技术实现了总压比为2.25、负荷系数高达0.55的风扇转子设计。基于数值模拟结果,分析了串列转子前后排叶片独特的匹配特性,及其与常规压气机匹配特性不同的原因;并进一步推导验证了前后排叶片气动参数之间的解析关系,为利用常规压气机设计体系进行跨声串列转子设计提供数学物理模型。研究结果表明:在跨声串列转子工况从堵点向近失速点移动的过程中,前排叶片的工作特性与常规转子一样,而后排叶片的总温升、总压比则不断下降,该变化规律存在解析关系,并可以利用数学物理模型进行准确预测后排叶片的整体性能。

关键词: 跨声串列转子, 前后排叶片, 匹配特性, 气动设计, 高负荷风扇

Abstract: With transonic tandem rotor technology, fan stage design is accomplished to produce total pressure ratio of 2.25 and responding loading coefficient of 0.55 at corrected tip speed of 381m/s. Based on the simulation results, the distinctive matching characteristic between forward blades (FB) and aft blades (AB) is analyzed, as well as the reason for its difference from conventional multistage compressor. Analytic correlation of aerodynamic parameter between the FB and AB is deduced and testified further, which provides a mathematic and physical model to elementary design for tandem rotor in conventional compressor design system. The result indicates that while the operating point is moving from choking to near stall condition, the characteristic of FB is identical with conventional rotor, whereas the total temperature rise and total pressure ratio of AB are declining in certain analytic rules. The model in this paper is competent to predict the characteristic of AB.

Key words: transonic tandem rotor, forward and aft blades, matching characteristic, aerodynamic design, highly loaded fan

中图分类号:

V231.3

赵斌, 刘宝杰. 跨声串列转子及前后排叶片匹配特性分析[J]. 航空学报, 2011, 32(6): 978-987.

ZHAO Bin, LIU Baojie. Analysis of Transonic Tandem Rotor and Matching Characteristic of Forward and Aft Blades[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(6): 978-987.

参考文献

[1] Burger G D, Keenan M J. Single-stage evaluation of highly-loaded high-Mach-number compressor stages.3—Data and performance tandem rotor. NASA-CR-72772, 1971.

[2] Brent J A, Clemmons D R. Single-stage experimental evaluation of tandem-airfoil rotor and stator blading for compressors, part 8: final report. NASA-CR-134713, 1974.

[3] Bammert K, Staude R. Optimization for rotor blades of tandem design for axial flow compressors. ASME Paper 79-GT-125, 1979.

[4] Bammert K, Beetle H. Investigation of an axial flow compressor with tandem cascade. ASME Paper 80-GT-83, 1980.

[5] Bammert K, Staude R. New features in the design of axial-flow compressors with tandem blades. ASME Paper 81-GT-113, 1981.

[6] Wu G, Zhang B, Guo B. Experimental investigation of tandem blade cascade with double circular arc profile. ASME Paper 85_IGT-94, 1985.

[7] Sachmann J, Fother L. Highly loaded tandem compressor cascade with variable camber and stagger. ASME Paper 93-GT-225, 1993.

[8] Roy B, Saha U. K. Experimental analysis of controlled diffusion compressor cascades with single and tandem airfoils. ASME Paper 95-CTP-41, 1995.

[9] Roy B, Saha U K. On the application of variable camber blading axial flow fans and compressors. ASME Paper 96-TA-58, 1996.

[10] Hasegawa H, Matsuoka A. Development of highly loaded fan with tandem cascade. AIAA-2003-1065, 2003.

[11] McGlumphy J, Ng W F, Wellborn S R, et al. Numerical investigation of tandem airfoils subsonic axial-flow tandem compressor blades. ASME Paper GT-2007-43929, 2007

[12] McGlumphy J, Ng W F, Wellborn S R, et al. 3D numerical investigation of tandem airfoils for acore compressor rotor. ASME Paper GT-2008-50427, 2008.

[13] McGlumphy J. Numerical investigation of subsonic axial-flow tandem compressor blades. Virginia: Virginia Polytechnic Institute & State University, 2007.

[14] Car D, Puterbaugh S L. Analysis of a highly loaded, transonic, inlet compressor stage: isolated and multi-stage performance. AIAA-2000-3206, 2000.

[15] 李清亮. DENTON湍流模型改进研究. 北京:北京航空航天大学能源与动力工程学院,2008. Li Qingliang. Research of turbulence model modification for Denton code. Beijing: School of Jet Propulsion, Beihang University, 2008. (in Chinese)

E-mail：hkxb@buaa.edu.cn

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跨声串列转子及前后排叶片匹配特性分析

Analysis of Transonic Tandem Rotor and Matching Characteristic of Forward and Aft Blades

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