进口预旋对高负荷跨声风扇性能的影响分析

赵斌; 刘宝杰

进口预旋对高负荷跨声风扇性能的影响分析

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家级重点实验室,北京 100191

计量
- 文章访问数: 1825
- HTML浏览量: 69
- PDF量: 18
- 被引次数: 0
出版历程
- 收稿日期: 2010-01-22
- 修回日期: 2010-03-15
- 刊出日期: 2011-03-28

Analysis of inlet pre-swirl influence on aerodynamic performance in highly loaded transonic fan

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

摘要

摘要: 利用三维数值模拟手段,研究了全转速条件下高负荷风扇进口级转子的预旋设计形式和其对气动性能的影响,以及在优化的预旋分布规律下,转子的典型部分转速特性.该风扇转子叶尖切线速度为480m/s,设计总压比为2.55,负荷系数高达0.42.结果表明:使用常规转子仍能达到该负荷水平,但采用带进口导叶的设计形式十分必要;在转子叶尖采用正预旋、低反力度的设计形式能有效地提高气动性能,如果想利用常规手段来设计下游静子则必须在叶根处引入反预旋;采用上述预旋规律所设计的转子在典型部分转速下仍然具有良好的性能.
- 高负荷风扇 /
- 气动性能 /
- 进口预旋 /
- 常规转子 /
- 典型部分转速
Abstract: Numerical simulation was conducted to explore the inlet pre-swirl design methodology and its influence on aerodynamic performance for highly loaded inlet stage fan rotor at full speeds,as well as the typical part speeds characteristic with optimum inlet pre-swirl distribution.The fan rotor was designed to produce a total pressure ratio of 2.55 and loading coefficient of 0.42 at a tip speed of 480m/s.The result indicates that conventional rotor has capability of achieving this loading level,but inlet guide vane is necessary in design.The adoption of positive pre-swirl and low reaction degree increases the tip performance effectively,negative pre-swirl is required at hub for stator based on conventional design method;rotor with aforementioned pre-swirl design has favorable performance at typical part speeds.
- highly loaded fan /
- aerodynamic performance /
- inlet pre-swirl /

HTML

参考文献(13)

[1]	Law C H,Wadia A R.Low aspect ratio transonic rotors Part 1:baseline design and performance[J].ASME Journal of Turbomachinery,1993,115(2):218-225.
[2]	Wadia A R,Law C H.Low aspect ratio transonic rotors Part 2:influence of location of maximum thickness on transonic compressor performance[J].ASME Journal of Turbomachinery,1993,115(2):226-239.
[3]	Wadia A R,Copenhaver W W.An investigation of the effect of cascade area ratios on transonic compressor performance[J].ASME Journal of Turbomachinery,1996,118(4):760-770.
[4]	Wadia A R,Szucs P N,Crall D W.Inner workings of aerodynamics sweep[J].ASME Journal of Turbomachinery,1998,120(4):671-682.
[5]	陈葆实,胡国荣,魏玉冰,等.高马赫数、高负荷单级风扇设计和试验研究[J].航空发动机,2000(3):28-35. CHEN Baoshi,HU Guorong,WEI Yubing,et al.Design and test research of highly loaded single-stage fan[J].Aeroengine,2000(3):28-35.(in Chinese)
[6]	Yu Q,Li Q S,Li L.The experimental research on improving operating stability of a single-stage transonic fan .ASME Paper 2002-GT-30640,2002.
[7]	Xing X Q,Zhou S,Zhao X L.Probing into the connotation of sweep aerodynamics of transonic fans and compressors .ASME Paper 2001-GT-0352,2001.
[8]	Kerrebrock J L.The prospects for aspirated compressors .AIAA 2000-2472,2000.
[9]	Merchant A A,Kerrebrock J L,Adamczyk J J,et al.Experimental investigation of a high pressure ratio aspirated fan stage[J].ASME Journal of Turbomachinery,2005,127(1):43-51.
[10]	李清亮.Denton湍流模型改进研究 .北京:北京航空航天大学,2008. LI Qingliang.Research of turbulence model modification for Denton code .Beijing:Beijing University of Aeronautics and Astronautics,2008.(in Chinese)
[11]	Neubert R J,Hobbs D E,Weingold H D.Application of sweep to improve the efficiency of a transonic fan Part Ⅰ:design[J].Journal of Propulsion and Power,1995,11(1):49-54.
[12]	Wennerstrom A J.Highly loaded axial flow compressor:history and current developments[J].ASME Journal of Turbomachinery,1990,112(4):567-578.
[13]	Wennerstrom A J.Some experiments with a supersonic axial compressor stage[J].ASME Journal of Turbomachinery,1987,109(3):388-397.