两类对转风扇的设计与气动特征数值研究

杨小贺; 单鹏

两类对转风扇的设计与气动特征数值研究

杨小贺,
单鹏

北京航空航天大学能源与动力工程学院,北京 100191

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出版历程
- 收稿日期: 2010-11-18
- 修回日期: 2011-02-25
- 刊出日期: 2011-10-28

Aerodynamic design and investigation of two counter-rotating fans

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

摘要

摘要: 采用一维设计程序分析了前后转子设计转速比的影响,研究了平均半径处的增压比、绝热效率、扩散损失和激波损失随转速比的变化规律.用计算流体力学分析了设计点与非设计状态的两个对转级流场,研究了其详细物理现象.结果表明两个对转级的设计与非设计性能均良好.发现低速风扇的两个转子均为常规跨声速转子,而高速风扇的前转子常规,后转子则为前缘激波和通道激波均贯穿全叶展的全超声速转子.同时发现,均带有与常规风扇级相当的失速裕度,低速对转级是两个转子同时达到失速点并且激波被推出叶栅,而高速对转级则是后转子先达到失速点并激波推出,从而后转子决定着级失速裕度.
- 叶轮机设计 /
- 对转风扇 /
- 超大涵道比 /
- 高负荷 /
- 转速比
Abstract: The design rotating speed ratio of forward and afterward rotors was discussed based on one-dimensional analysis.The variations of pressure ratios,adiabatic efficiencies,diffusion losses and shock losses at the streamline of half-annulus-area radius against the varied design rotating speed ratios were studied.The flow fields of these two contra-stages were numerically simulated and the detailed flow physics was investigated at the design and off-design conditions.The simulations reveal that these two stages are quite well performed.For the civil engine contra-stage test fan,both rotors are conventional transonic rotors due to the low pressure ratio and low tip speed.For the military engine contra-stage fan different from the conventional transonic forward rotor,the afterward rotor is a full-span relative supersonic rotor in which both the leading edge shock and the passage shock extend from the casing to the hub.Furthermore,these two contra-stages exhibit stall margins competitive to conventional rotor-stator stages.For the civil test fan of low pressure ratio at the stall point,both the forward and afterward rotors are stall and the shocks are detached,correspondingly;for the military fan of high pressure ratio,only the afterward rotor is stall,determining the stage stall point.
- turbomachine design /
- counter-rotating fan (CRF) /
- ultra-high bypass ratio /
- high loading level /
- rotating speed ratio

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参考文献(24)

[1]	Wennerstrom A J,Frost G R.Design of a 1500 ft/sec,transonic,high-through-flow,single-stage axial-flow compressor with low hub/tip ratio .AFARL-TR-76-59,AD-B016386,1976.
[2]	Wennerstrom A J,Forst G R.Design of a rotor incorporating splitter vanes for a high pressure ratio supersonic axial compressor stage .ARL-TR-74-0110,1974.
[3]	Merchant A A.Design and analysis of axial aspirated compressor stages .Cambridge:Massachusetts Institute of Technology,1999.
[4]	Brent J A.Single-stage experimental evaluation of tandem-Airfoil rotor and stator blading for compressors Part Ⅷ:final report .NASA CR-72772,1974.
[5]	Yonug R H.Contra-rotating axial fans[J].J.Instn.Heat.Vent.Eng.,1951,18:187-192.
[6]	Johnsen L J,Fessler T E.Experimental investigation of performance of single-stage transonic compressor with guide vanes turning counter to direction of rotor whirl .NACA RM E57B04,1957.
[7]	Anonymous.Final report on compressor portion of turboaccelerator crcle evaluation and experimental verification program .Pratt & Whitney Aircraft,PWA-2833,1966.
[8]	Sabel E J,Sabatiuk A.Turbojet engine development:design of phase I compressor .Curtiss-Wright Corporation,C.W.R.Report NO.501,1957.
[9]	Sabel E J,SabatiuK A.Turbojet engine development:phase Ⅱ compressor test results .Curtiss-Wright Corporation,C.W.R.Report NO.502,1957.
[10]	Wennerstrom A J.Highly loaded axial flow compressors:history and current developments[J].ASME Journal of Turbomachinery,1990,112(4):567-578.
[11]	Law C H,Wennerstrom A J.Performance of two transonic compressor rotors incorporating inlet counterswil[J].ASME Journal of Turbomachinery,1987,109(1):142-149.
[12]	Shama P B,Jain Y P,Jha N K,et al.Stalling behavior of a counter-rotating stage .ISABE Paper 85-7087,1985.
[13]	Kerrebrock J L,Epstein A H,Merchant A A,et.al.Design and test of an aspirated counter-rotating fan[J].ASME Journal of Turbomachinery,2008,130(2):198-206.
[14]	Donald H.Parametric study of a Mach 2.4 transport engine with supersonic through-flow rotor and supersonic counter-rotating diffuser (SSTR/SSCRD) .NASA/TM-2004-213139,2004.
[15]	Ryojiro M,Toyohiko O,Kiyoshi F,et al.Development of counter rotating axial fan turbojet engine for supersonic unmanned Plane .AIAA 2007-5023,2007.
[16]	林延芳,彭泽琰.反旋超跨音压气机和涡轮气动方案探讨 .北京:中国航空学会第二届动力年会,CSAAP-89-144(T),1989. LIN Yanfang,PENG Zeyan.Disscussion on the aerodynamic scheme of the transonic and supersonic counter-rotating compressors and turbines .Beijing:Chinese Society of Aeronautics and Astronautics,CSAA P-89-144(T),1989.(in Chinese)
[17]	蔡睿贤.轴流对转风扇典型基元级基本分析[J].流体机械,1994,22(12):11-15. CAI Ruixian.The basic analysis of the typical elements of counter-rotating axial fan[J].Fluid Machinery,1994,22(12):11-15.(in Chinese)
[18]	季路成.对转叶轮机技术挑战分析[J].推进技术,2007,28 (1):40-44. JI Lucheng.Analysis for technique challenges on counter-rotating turbomachinery[J].Journal of Propulsion Technology,2007,28(1):40-44.(in Chinese)
[19]	刘波,陈云永,项效镕,等.对转压气机数值模拟及实验研究[J].推进技术,2008,29 (4):454-457. LIU Bo,CHEN Yunyong,XIANG Xiaorong,et al.Experimental and numerical investigation of dual stage counter-rotating compressor[J].Journal of Propulsion Technology,2008,29(4):454-457.(in Chinese)
[20]	Lieblein S,Schwenk F C,Broderick R L.Diffusion factor for estimating losses and limiting blade loadings in axial-flow-compressor blade elements .NACA RM E53D01,1953.
[21]	Miller G R,Lewis G W,Hartmann M J.Shock losses in transonic compressor blade rows[J].ASME Journal of Engineering for Power,1961,83(4):235-242.
[22]	杨小贺,单鹏.风扇与轴流离心压气机一体化通流设计方法[J].航空动力学报,2010,25(2):443-450. YANG Xiaohe,SHAN Peng.Integrative design method of fan and axial-centrifugal compressors[J].Journal of Aerospace Power,2010,25(2):443-450.(in Chinese)
[23]	Frost G R,Wennerstrom A J.The design of axial compressor airfoils using arbitrary camber lines .Aerospace Research Labs 73-0107,AD 765 165,1973.
[24]	Smith L H.Recovery ratio-a measure of the loss recovery potential of compressor stages[J].Transaction of the American Society of Mechanical Engineers,1958,80(3):517-524.