风扇/轴流压气机最大负荷设计技术探索
|
摘要
无论是国防、民用领域的巨大需求驱动,还是遵循叶轮机气动理论和技术的内在发展逻辑,高负荷叶轮机始终是重要发展趋势,力求最大负荷设计是叶轮机气动理论和设计技术研究的永恒主题。
基于对风扇/轴流压气机流动机理及设计流程的认识,本文首次尝试对“什么是最大负荷设计”、“怎样实现最大负荷设计”进行全面地阐释,从基元叶型、叶片基元展向匹配、叶片排排间匹配三个层面分别展示了可使风扇/轴流压气机负荷最大化的技术方向和技术内涵。
一、基元叶型方面,大折转角(亚音)、有限分离(超音)设计是最大负荷设计的努力方向。本文发展了适用于以大折转角为特征的低损失亚音叶型设计方法并编制了相应程序。该方法包含叶片造型及准三维流场分析两部分,论文工作侧重于发展一种特定的叶片造型方法,它基于一种专利叶型厚度分布,依靠调整叶型中弧线弯度分布规律实现负荷最大化的目标。
二、叶片基元展向匹配方面,本研究从影响负荷最大化的叶身展向积迭(注:原指掠弯是裕度定制的一部分,为方便论述,本文将此统一论述为裕度定制)、叶尖间隙、叶片与端壁角区这三个最重要因素出发,探讨了各因素影响负荷最大化的机理,并由此给出了最大负荷设计过程中的技术措施和努力方向。
1)从掌控风扇/轴流压气机裕度方法回顾入手,探析了美国和俄罗斯裕度控制方法及相应特点,结合对“掠/弯”因素的认识提出了裕度定制技术:并开发了能够体现裕度定制思想的二维特性预估方法,可在二维层面下方便快捷地考虑以掠/弯为代表的叶片基元展向积迭以及叶片排间轴向间距带来的影响;
2)借鉴Denton关于不可压叶尖泄漏损失的理论分析,推导出适用于可压缩流动的叶尖泄漏掺混损失计算的基本关系式。在仅考虑泄漏掺混损失情况下,对叶尖基元负荷、间隙、泄漏流量系数整体水平及这些参数的弦向分布等因素的影响进行了理论和数值分析。并基于此对风扇/轴流压气机中叶尖流动控制技术进行了阐述和分析,从叶尖泄漏流控制方面为最大负荷设计提供技术指导:
3)基于角区流动为叶表与端壁附面层交汇流动的物理认识,假设忽略附面层内二次流影响,并且将角区内三维附面层流动等效为二维附面层,建立了角区流动分离预测模型,提出了角区流动控制技术。依据该模型对目前风扇/轴流压气机设计中采用的各种角区分离控制技术进行了分析。
三、叶片排排间匹配方面,除了裕度定制中所涉及的正在日渐成熟的二维、三维定常方法外,缘线匹配是全方位考虑排间匹配的设计自由度。文中以关注不同缘线匹配对压气机的气动、振动影响为出发点,采用数值方法,利用进口边界尾迹和真实叶片两种模型考察了上游叶片尾迹撞击下游叶表的展向轨迹及其在气动和振动方面的影响。研究指出,尽管目前数值模拟研究仍未发现单组缘线匹配存在显著气动影响,但缘线匹配却在控制叶片振动、气动噪声方面显现潜力。
Whether driven by great demands from national defense and civilian fields, or following internal evolution logic of aerodynamic theory and techniques of turbomachinery, high-loaded turbomachinery is always an important development trend, and then, striving hard to maximum loading design is permanent topic in researches on aerodynamic theory and design techniques of turbomachinery.
Based on knowledge of flow mechanisms and design process for fan and axial-flow compressor, this dissertation firstly attempted to explain roundly what "maximum loading design" is and how to develop "maximum loading design". Preliminary explorations on maximum loading design techniques were developed through three aspects such as blade airfoil shape, radial matching between blade sections, and stage matching between blade rows. Main research work would be listed as follows:
1. As to blade airfoil shape design, large turning angle blade (subsonic) and restricted separated blade (supersonic) are the two effort aspects. In the dissertation, a design method of large turning angle subsonic airfoil for use in stator hub section was developed. The method includes quasi-three-dimensional flow analysis, and blade contouring method which the dissertation focused on. Firstly, blade airfoil shape was contoured by adjusting metal angle distribution combined with special thickness distribution from a U.S. patent, and then the blade-to-blade flow was computed by solving the two-dimensional steady Navier-Stokes equations, finally, overall performance and internal flowfield characterization were obtained and analyzed.
2. As to radial matching between blade sections, preliminary investigations were developed from three aspects such as stall margin customizing technique, control technology of tip clearance flow, prediction model and control technology of corner separate.
a) On basis of reviewing on methods of achieving the goal of stall margin in design process of fan and axial-flow compressor, in conjunction of understandings on "Sweep/Dihedral", stall margin customizing technique was put forward; two-dimensional performance prediction method for stall margin customizing was developed, it can consider influences of radial stacking patterns of blade sections and axial distances between blade rows conveniently and rapidly.
b) A simple model for tip leakage mixing loss of unshrouded blades for compressible flow was presented. The work drew ideas, was based on the theoretical analysis of the loss by Denton. Relationship for computing the loss is derived, in terms of blade surface static pressure, chordwise distribution of tip clearance, discharge coefficient and total pressure loss coefficient in the tip region. Parameter studies reveal average level and chordwise distribution of the above factors' contribution to the loss. Finally, combined with conclusions obtained above, explanations were given to various control technology of tip clearance flow.
c) Based on the physical intuition of that the three-dimensional corner boundary layer is the conflux of both blade and end wall boundary layer, with assumptions of ignoring the cross flow effect and three-dimensionality of the nearby main flow, an equivalent two-dimensional corner boundary layer was put forward to predict the behavior of corner boundary layer. And then, a corner separate criterion was established using the boundary layer separate criteria. Finally, combined with conclusions obtained above, explanations were given to various control technology of comer separate.
3. As to stage matching between blade rows, besides growing steady two-dimensional and three-dimensional methods which can could be dealt with by stall margin customizing technique, edge matching is a proper choice for guiding design to consider stage matching. Numerical investigations were presented in order to better understand the influences of edge matching on unsteady flow and performance of fan and axial-flow compressors, moreover, influences of edge matching on vibration and rotor/stator interaction noise were investigated preliminarily.
基于对风扇/轴流压气机流动机理及设计流程的认识,本文首次尝试对“什么是最大负荷设计”、“怎样实现最大负荷设计”进行全面地阐释,从基元叶型、叶片基元展向匹配、叶片排排间匹配三个层面分别展示了可使风扇/轴流压气机负荷最大化的技术方向和技术内涵。
一、基元叶型方面,大折转角(亚音)、有限分离(超音)设计是最大负荷设计的努力方向。本文发展了适用于以大折转角为特征的低损失亚音叶型设计方法并编制了相应程序。该方法包含叶片造型及准三维流场分析两部分,论文工作侧重于发展一种特定的叶片造型方法,它基于一种专利叶型厚度分布,依靠调整叶型中弧线弯度分布规律实现负荷最大化的目标。
二、叶片基元展向匹配方面,本研究从影响负荷最大化的叶身展向积迭(注:原指掠弯是裕度定制的一部分,为方便论述,本文将此统一论述为裕度定制)、叶尖间隙、叶片与端壁角区这三个最重要因素出发,探讨了各因素影响负荷最大化的机理,并由此给出了最大负荷设计过程中的技术措施和努力方向。
1)从掌控风扇/轴流压气机裕度方法回顾入手,探析了美国和俄罗斯裕度控制方法及相应特点,结合对“掠/弯”因素的认识提出了裕度定制技术:并开发了能够体现裕度定制思想的二维特性预估方法,可在二维层面下方便快捷地考虑以掠/弯为代表的叶片基元展向积迭以及叶片排间轴向间距带来的影响;
2)借鉴Denton关于不可压叶尖泄漏损失的理论分析,推导出适用于可压缩流动的叶尖泄漏掺混损失计算的基本关系式。在仅考虑泄漏掺混损失情况下,对叶尖基元负荷、间隙、泄漏流量系数整体水平及这些参数的弦向分布等因素的影响进行了理论和数值分析。并基于此对风扇/轴流压气机中叶尖流动控制技术进行了阐述和分析,从叶尖泄漏流控制方面为最大负荷设计提供技术指导:
3)基于角区流动为叶表与端壁附面层交汇流动的物理认识,假设忽略附面层内二次流影响,并且将角区内三维附面层流动等效为二维附面层,建立了角区流动分离预测模型,提出了角区流动控制技术。依据该模型对目前风扇/轴流压气机设计中采用的各种角区分离控制技术进行了分析。
三、叶片排排间匹配方面,除了裕度定制中所涉及的正在日渐成熟的二维、三维定常方法外,缘线匹配是全方位考虑排间匹配的设计自由度。文中以关注不同缘线匹配对压气机的气动、振动影响为出发点,采用数值方法,利用进口边界尾迹和真实叶片两种模型考察了上游叶片尾迹撞击下游叶表的展向轨迹及其在气动和振动方面的影响。研究指出,尽管目前数值模拟研究仍未发现单组缘线匹配存在显著气动影响,但缘线匹配却在控制叶片振动、气动噪声方面显现潜力。
Whether driven by great demands from national defense and civilian fields, or following internal evolution logic of aerodynamic theory and techniques of turbomachinery, high-loaded turbomachinery is always an important development trend, and then, striving hard to maximum loading design is permanent topic in researches on aerodynamic theory and design techniques of turbomachinery.
Based on knowledge of flow mechanisms and design process for fan and axial-flow compressor, this dissertation firstly attempted to explain roundly what "maximum loading design" is and how to develop "maximum loading design". Preliminary explorations on maximum loading design techniques were developed through three aspects such as blade airfoil shape, radial matching between blade sections, and stage matching between blade rows. Main research work would be listed as follows:
1. As to blade airfoil shape design, large turning angle blade (subsonic) and restricted separated blade (supersonic) are the two effort aspects. In the dissertation, a design method of large turning angle subsonic airfoil for use in stator hub section was developed. The method includes quasi-three-dimensional flow analysis, and blade contouring method which the dissertation focused on. Firstly, blade airfoil shape was contoured by adjusting metal angle distribution combined with special thickness distribution from a U.S. patent, and then the blade-to-blade flow was computed by solving the two-dimensional steady Navier-Stokes equations, finally, overall performance and internal flowfield characterization were obtained and analyzed.
2. As to radial matching between blade sections, preliminary investigations were developed from three aspects such as stall margin customizing technique, control technology of tip clearance flow, prediction model and control technology of corner separate.
a) On basis of reviewing on methods of achieving the goal of stall margin in design process of fan and axial-flow compressor, in conjunction of understandings on "Sweep/Dihedral", stall margin customizing technique was put forward; two-dimensional performance prediction method for stall margin customizing was developed, it can consider influences of radial stacking patterns of blade sections and axial distances between blade rows conveniently and rapidly.
b) A simple model for tip leakage mixing loss of unshrouded blades for compressible flow was presented. The work drew ideas, was based on the theoretical analysis of the loss by Denton. Relationship for computing the loss is derived, in terms of blade surface static pressure, chordwise distribution of tip clearance, discharge coefficient and total pressure loss coefficient in the tip region. Parameter studies reveal average level and chordwise distribution of the above factors' contribution to the loss. Finally, combined with conclusions obtained above, explanations were given to various control technology of tip clearance flow.
c) Based on the physical intuition of that the three-dimensional corner boundary layer is the conflux of both blade and end wall boundary layer, with assumptions of ignoring the cross flow effect and three-dimensionality of the nearby main flow, an equivalent two-dimensional corner boundary layer was put forward to predict the behavior of corner boundary layer. And then, a corner separate criterion was established using the boundary layer separate criteria. Finally, combined with conclusions obtained above, explanations were given to various control technology of comer separate.
3. As to stage matching between blade rows, besides growing steady two-dimensional and three-dimensional methods which can could be dealt with by stall margin customizing technique, edge matching is a proper choice for guiding design to consider stage matching. Numerical investigations were presented in order to better understand the influences of edge matching on unsteady flow and performance of fan and axial-flow compressors, moreover, influences of edge matching on vibration and rotor/stator interaction noise were investigated preliminarily.
引文
[1]刘大响,“航空动力发展的历史机遇”,航空发动机,第31卷第2期,pp.1-3,2005.
[2]江泽民,“对中国能源问题的思考”,上海交通大学学报,第42卷第3期,pp.345-359,2008.
[3]Layne,A.W.,et al.,"The US Department of Energy's Advanced Turbine Systems Program," ASME Paper,98-GT-141,1998.
[4]蒋洪德,“美国高性能涡轮发动机技术(HPTET)计划”,压气机文集第一分册.航空科技情报研究所,pp.252-260,1989.
[5]季路成,陈江,“从IHPTET到VAATE计划的技术方向探析”,中国工程热物理学会热机气动热力学会议论文集,编号:052086,北京,2005.
[6]方昌德,“航空发动机的发展前景”,航空发动机,第30卷第1期,pp.1-5,2004.
[7]刘大响,“世界航空动力技术的现状及发展动向”,北京航空航天大学学报,第28卷第5期,pp.490-496,2002.
[8]Michael T.Tong,Scott M.Jones,et al.,"A Probabilistic Assessment of NASA Ultra-Efficient Engine Technologies for a Large Subsonic Transport," ASME Paper,GT2004-54385,2004.
[9]Michael T.Tong,and Scott M.Jones,"An Updated Assessment of NASA Ultra-Efficient Engine Technologies," ISABE Paper,2005-1163,2005.
[10]Nick Baker,Andrew Rolt,et al.,"New Environmental Friendly Aero Engine Core Concepts," ISABE Paper,2007-1120,2007.
[11]梁春华,“Tech56技术计划即将结束”,航空发动机,第30卷第1期,pp.46,2004.
[12]Jean-Jacques Korsia,"VITAL-European R&D Program for Greener Aero-Engines," ISABE Paper,2007-1118,2007.
[13]Shigeru Hayashi,"An Overview of JAXA's TechCLEAN Project - Technology Development Project for Environmentally Compatible Aeroengines," ISABE Paper,2007-1010,2007.
[14]陈懋章,“中国航空发动机高压压气机发展的几个问题”,航空发动机,第 32卷第2期,pp.5-12,2006.
[15]Jones,M.J.,Birch,N.T.and Bradbrook,S.J.,"Evolutions in Aircraft Engine Design and a Vision for the Future," ISABE Paper,2001-1014,2001.
[16]Cumpsty,N.A.,"Compressor Aerodynamics," Krieger Publishing Company,2004.
[17]Steffens,K.,"Advanced Compressor Technology - Key Success Factor for Competitiveness in Modern Aero-Engines," ISABE Paper,2001-1009,2001.
[18]Manish Chouhan,Kota Venkata Kaundinya,and Bhaskar Roy,"Experimental Study of Stability Improvement by Tip Injection at Mid Chord Region of Axial Compressor," ISABE Paper,2007-1267,2007.
[19]Storer,J.A.,and Cumpsty,N.A.,"An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors," Journal of Turbomachinery,Vol.116,pp.648-655,1994.
[20]邓向阳,“压气机叶顶间隙流的数值模拟研究”,博士论文,中国科学院研究生院,2006.
[21]张靖煊,林峰,陈静宜,聂超群,“旋转进口畸变条件下轴流压气机叶项间隙流非定常特征及其与旋转失速的关联性研究”,工程热物理学报,第29卷第3期,pp.390-394,2008.
[22]徐纲,聂超群,黄伟光,陈静宜,“低速轴流压气机顶部微量喷气控制失速机理的数值模拟”,工程热物理学报,第25卷第1期,pp.37-40,2004.
[23]陈懋章,“风扇/压气机技术发展和对今后工作的建议”,航空动力学报,第17卷第1期,PP.1-15,2002.
[24]Supplee,H.H.,"The Gas Turbine," 1910.
[25]Wisler,D.C.,"Advanced Compressor and Fan Systems," GE Aircraft Engines,1988.
[26]Freeman,J.H.,"Design of A Multi-spool,High-speed,Counter-Rotating,Aspirated Compressor," AD-A385286,2000.
[27]陈懋章,“叶轮机气动力学研究及其发展趋势”,中国航空学会航空百年学术论坛动力分坛论文集(一),pp.19-37,北京,2003.
[28]季路成,王延荣,邵卫卫,王宝臣,“缘线匹配主导的叶轮机非定常设计”,中国工程热物理学会2007年学术会议论文,编号:072012,2007.
[29]Wu,C.H.,"A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-,Radial,and Mixed-Flow Types",NACA TN2604,1952.
[30]Wennerstrom,A.J.,and Frost,G.R.,"Design of a 1500ft/sec,Transonic,High-Through-Flow,Single-Stage Axial-Flow Compressor with Low Hub/Tip Ratio," AFARL TR 76-59,1976.
[31]刘宝杰,邹正平等,“叶轮机计算流体动力学技术现状与发展趋势”,航空学报,第23卷第5期,pp.394-404,2002.
[32]季路成,“轴流叶轮机转子/静子干扰非定常流动探索”,博士学位论文,北京航空航天大学,1998.
[33]陈江,“叶轮机非定常气动设计技术探索”,博士学位论文,北京航空航天大学,2004.
[34]Hobbs,D.,and Weingold,H.,"Development of Controlled Diffusion Airfoils for Multistage Compressor Application," Journal of Engineering for Gas Turbines Power,Vol.106,pp.271-278,1984.
[35]He,L.,Chen,T.,et al.,"Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines," ASME Paper,GT-2002-30355,2002.
[36]Curtis,E.M.,and Hodson,H.P.et al.,"Development of Blade Profiles for Low Pressure Turbine Applications," Journal of Turbomachinery,Vol.119,pp.531-538,1997.
[37]季路成,陈江,黄海波等,“非定常环境下叶栅性能的数值研究”,工程热物理学报,第24卷第2期,pp.211-215,2003.
[38]Wennerstrom,A.J.,"Low Aspect Ratio Axial Flow Compressors - Why and What It Means," SAE,Cliff Garrett Turbomachinery Award Lecture,3~(rd),Long Beach,CA;United States;14 Oct.1986.
[39]http://www.pr.afrl.af.mil/division/prt/ihptet/ihptet.html.
[40]陈光,“航空发动机结构设计分析”,北京航空航天大学出版社,2006.
[41]Stephane Hiernaux,Celine Lebas,et al.,"Next Generation Booster," ISABE Paper,2007-1347,2007.
[42]Gunter Wilfert,Joerg Sieber,et al.,"New Environmental Friendly Aero Engine Core Concepts," ISABE Paper,2007-1120,2007.
[43]Adamczyk,J.J.,"Model Equation for Simulating Flows in Multistage Turbomachinery," NASA TM-86869,1984.
[44]Rhie,C.M.,et al.,"Development and Application of a Multistage Navier-Stokes Solver,Part Ⅰ:Multistage Modeling Using Body-Forces and Deterministic Stresses," ASME paper,95-GT-342.,1995.
[45]周盛,侯安平等,“关于轴流压气机的非定常两代流型”,航空学报,第26卷第1期,pp.1-7,2005.
[46]Ji,L.C.and Chen,J.,"Edge Matching--Part Ⅰ:Theory and Implementation,"ASME paper,GT-2005-68474,2005.
[47]Greitzer,E.M.,"Review--Axial Compressor Stall Phenomena," Journal of Fluids Engineering,Vol.102,pp.134-151,1980.
[48]Johnsen,I.,and Bullock,R.,"Aerodynamical Design of Axial-Flow Compressors," NASA SP-36,1965.
[49]Korn,D.,"Numerical Design of Transonic Cascades," ERDA Research and Development Report C00-3077-72,1975.
[50]Schmidt,E.,"Computation of Supercritical Compressor and Turbine Cascades With a Design Method for Transonic Flows," ASME Paper,79-GT-30,1979.
[51]Bauer F,Garabedian P,and Korn D."Supercdtical Wine Section,Lecture Notes in Economics and Math Systems," Springer-Verlag New York,Section 1.1972,66;Section 2.1975,108.
[52]Garabedian P,and Korn D."A Systematic Method for Computer Design of Supercritical Airfoils in Cascade," Communications on Pure and Applied Mathematics,Vol.29,pp.369-382,1976.
[53]Korn D.,"Numerical Design of Transonic Cascade," ERDA Research and Development Report,Coo- 3077- 72,1975.
[54]Ihor S.Diakunchak,Greg R.Gaul,Gerry McQuiggan,and Leslie R.Southall,"Siemens Westinghouse Advanced Turbine Systems Program Final Summary,"Journal of Engineering for Gas Turbines and Power,Vol.126,pp.524-530,2004.
[55]Dong Y.,Cumpsty N.A.,"Compressor Blade Boundary Layers:Part 1-Test Facility and Measurements with Incident Wakes," Journal of Turbomachinery,Vol.112,pp.222-230,1990.
[56]Schulz H.D.,Gallus H.E.,Lakshminarayana B.,"Three-Dimensional Separated Flow Field in the Endwall Region of An Annular Compressor Cascade in the Presence of Rotor-Stator Interaction.Part 1:Quasi-Steady Flow Field and Comparison with Steady-State Data," Journal of Turbomachinery,Vol.112, pp.669-678,1990.
[57]Schulz H.D.,Gallus H.E.,Lakshminarayana B.,"Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction.Part 2:Unsteady Flow and Pressure Field,"Journal of Turbomachinery,Vol.112,pp.679-690,1990.
[58]Halstead,D.E.,Wisler,D.C.,Okiishi,T.H.,et al.,"Boundary Layer Development in Axial Compressors and Turbines:Part 1:Composite Picture,"Journal of Turbomachinery,Vol.119,pp 114-127,1997.
[59]Halstead,D.E.,Wisler,D.C.,et al.,"Boundary Layer Development in Axial Compressors and Turbines:Part 2 of 4-Compressors," Journal of Turbomachinery,Vol.119,pp.426-444,1997.
[60]Tiedemann,M.,Kost,F.,"Unsteady Boundary Layer Transition on a High Pressure Turbine Rotor Blade",ASME paper,99-GT- 194,1999.
[61]Hodson,H.P.,Huntsman,I.,Steele,A.B.,"An Investigation of Boundary Layer Development in a Multistage LP Turbine," ASME paper,93-GT-310,1993.
[62]Gallimore S.J.,John Bolger,and Cumpsty N.A.,"The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading--Part Ⅰ:University Research and Methods Development," Journal of Turbomachinery,Vol.124,pp.521-532,2002.
[63]Gallimore S.J.,John Bolger,and Cumpsty N.A.,"The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading-Part Ⅱ Low and High-Speed Designs and Test Verification," Journal of Turbomachinery,Vol.124,pp.533-541,2002.
[64]Wadia,A.R.,Szucs,P.N.,and Crall,D.W.,"Inner Workings of Aerodynamic Sweep," Journal of Turbomachinery,Vol.120,pp.671-682,1998.
[65]Denton,J.D.,and Xu L.,"The Effects of Lean and Sweep on Transonic Fan Performance," ASME Paper,GT-2002-30327,2002.
[66]Ji,L.C.,Chen J.,and Lin F.,"Review and Understanding on Sweep in Axial Compressor Design," ASME Paper,GT2005-68473,2005.
[67]王仲奇,苏杰先,钟兢军,“弯曲叶片栅内减少能量损失机理研究的新进展”,工程热物理学报,第15卷第2期,pp.147-152,1994.
[68]钟兢军,苏杰先,王仲奇,“压气机叶栅壁面拓扑和二次流结构分析”,工程热物理学报,第19卷第1期,pp.40-44,1998.
[69]王会社,“不同叶型和叶片积叠线及弯曲角对压气机叶栅流场的影响”,博士学位论文,哈尔滨工业大学工学,2001.
[70]Wang Zhongqi,Lai Shengkai,and Xu Wenyuan."Aerodynamic Calculation of Turbine Stator Cascades with Curvilinear Leaned Blades and Some Experimental Results".Symposium Paper of 5th ISABE,pp.30.1-30.9,India,1981.
[71]Axel Fischer,Walter Riess,and Joerg R.Seume,"Performance of Strongly Bowed Stators in a Four-Stage High-Speed Compressor," Journal of Turbomachinery,Vol.126,pp.333-338,2004.
[72]Wisler D.C.,and Beacher B.F.,"Improved compressor performance using recessed clearance(trenches)over tile rotor",AIAA Paper,AIAA-86-1745.1986.
[73]卢新根等,“梯状间隙结构对轴流压气机影响的试验与数值模拟”,工程热物理学报,第26卷第2期,pp.234-236,2005.
[74]卢新根,楚武利,朱俊强等,“轴流压气机机匣处理研究进展及评述”,力学进展,第36卷第2期,pp.222-232,2006.
[75]Smith,L.H.,"Casing Boundary Layers in Multistage Axial Flow Compressors,"Flow Research in Blading,Edited by Elsevier Publishing Company,1970.
[76]Deregel,P.,and Tan,C.S.,"Impact of Rotor Wakes on Steady-State Axial Compressor Performance," ASME paper,96-GT-253,1996.
[77]Ng,W.F.,and Epstein,A.H.,"Unsteady Losses in Transonic Compressors,"ASME paper,84-GT-183,1984.
[78]Dawes,W.N.,"A Numerical Study of The Interaction of a Transonic Compressor Rotor Over-Tip Leakage Vortex with the Following Stator Blade Row," ASME paper,94-GT-156,1994.
[79]Walker,G.J.and Oliver,A.R.,"The Effect of Interaction Between Wakes from Blade Rows in an Axial Flow Compressor on the Noise Generated by Blade Interaction," ASME paper,72-GT-15,1972.
[80]Huber,F.W.,Johnson,P.D.,Sharma,O.P.,et al.,"Performance Improvement through Indexing of Turbine Airfoils,Part 1-Experimental Investigation,"ASME paper,95-GT-27,1995.
[81]Eulitz,F.,Engel,K.,and Gebing,H.,"Numerical Investigation of the Clocking Effects in a Multistage Turbine," ASME paper,96-GT-26,1996.
[82]Dorney,D.J.,and Sharma,O.P.,"A Study of Turbine Performance Increases through Airfoil Clocking," AIAA paper,96-2816,1996.
[83]Cizmas,P.G.A.,Dorney,D.J.,"The Influence of Clocking on Unsteady Forces of Compressor and Turbine Blades," ISABE paper,99-72,1999.
[84]Tiedemann,M.,and Kost,F.,"Some Aspects of Wake-Wake Interactions Regarding Turbine Stator Clocking," Journal of Turbomachinery,Vol.123,pp.526-533,2001.
[85]Dorney,D.J.,Croft,R.R.,Sondak,D.L.,et al.,"Computational Study of Clocking an Embedded Stage in a 4-Stage Industrial Turbine," ASME paper,2001-GT-0509,2001.
[86]Arnone,A.,Marconcini,M.,Pacciani,R.,et al.,"Numerical Investigation of Airfoil Clocking in a Three-Stage Low Pressure Turbine," ASME paper,2001-GT-0303,2001.
[87]He,L.,Chen,T.,et al.,"Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines," ASME paper,2002-GT-30355,2002.
[88]侯安平,周盛,“轴流式叶轮机时序效应的机理探讨”,航空动力学报,第18卷第1期,pp.70-75,2003.
[89]闫朝,季路成,陈江,徐建中,“轴向间距对时序效应影响的研究”,工程热物理学报,第25卷第2期,pp.220-222,2004.
[90]季路成,阎朝,陈江,“将缘线匹配应用于最大化三维时序效益”,航空动力学报,第21卷第3期,pp.467-473,2006.
[91]阎朝,“关于应用缘线匹配最大化时序效应潜能的初探”,博士学位论文,中国科学院研究生院,2004.
[92]Wennerstrom,A.J.,"Highly Loaded Axial Flow Compressors:History and Current Developments," Journal of Turbomachinery,Vol.112,pp.567-578,1990.
[93]Dunker,R.J.,"A Shock Loss Model for Supercritical Subsonic Flows in Transonic Axial Flow Compressors," Transonic and Supersonic Phenomena in Turbomachines,pp.27.1-27.15,AGARD-CP-401,1987.
[94]余华蔚,兰发祥,程荣辉,“高马赫数、大弯角静叶型设计与分析”,燃气涡轮试验与研究,第13卷第2期,PP.17-21,2000.
[95]Lubenstein,et al.,"Airfoil Shape for Arrays of Airfoils," U.S.Patent:4,431,376,1984.
[96]Dunham,J.,"Aerodynamic Losses in Turbomachines," AGARD-CP-571,Loss Mechanism and Unsteady Flows in Turbomachines,K1-K13,1996.
[97]程荣辉,周拜豪等,“定制叶型技术及其在压气机设计中的应用”,燃气涡轮试验与研究,第13卷第1期,pp.15-22,2000.
[98]Hoheisel,H.and Seyb,N.J.,"The Boundary Layer Behavior of Highly Loaded Compressor Cascade at Transonic Flow Conditions," Transonic and Supersonic Phenomena in Turbomachines,pp.4.1-4.17,AGARD-CP-401,1987.
[99]Koller,U.,Monig,R.,Kusters,B.,and Schreiber,H.,"Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part Ⅰ:Design and Optimization," Journal of Turbomachinery,Vol.122,pp.397-405,2000.
[100]Kusters,B.,Schreiber,H.,Koller,U.,and Monig,R.,"Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part Ⅱ:Experimental and Theoretical Analysis," Journal of Turbomachinery,Vol.122,pp.406-415,2000.
[101]Sonada,T.,Yamaguchi,Y.,Arima,T.,Olhofer,M.,Sendhoff,B.,and Schreiber,H.,"Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition - Part Ⅰ:Design and Optimization," ASME Paper,GT2003-38458,2003.
[102]Schreiber,H.,Steinert,W.,Sonada,T.,and Arima,T.,"Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition - Part Ⅱ:Experimental and Numerical Analysis," ASME Paper,GT2003-38477,2003.
[103]Benini,E.,and Toffolo,A.,"Development of High-Performance Airfoils for Axial Flow Compressors Using Evolutionary Computation," Journal of Propulsion and Power,Vol.18,pp.544-554,2002.
[104]Xu,C.and Amano,R.S.,"A Turbomachinery Blade Design and Optimization Procedure," ASME Paper,GT-2002-30541,2002.
[105]Rai,M.,and Madavan,N.,"Application of Artificial Neural Networks to Design of Turbomachinery Airfoils," Journal of Propulsion and Power,Vol.17,pp.176-183,2001.
[106]Yiu,K.F.C.,and Zangeneh,M.,"Three-Dimensional Automatic Optimization Method for Turbomachinery Blade Design," Journal of Propulsion and Power,Vol.16,pp.1174-1181,2000.
[107]Song B.,and Wing F.Ng,"Performance and Flow Characteristics of an Optimized Supercritical Compressor Stator Cascade," Journal of Turbomachinery, Vol.128, pp.435-443, 2006.
[108] Chima, R.V., "RVCQ3D - Rotor Viscous Code Quasi-3-D User's Manual and Documentation Version 303," 1999.
[109] Chima, R.V., "GRAPE 2-D Grid Generator for Turbomachinery User's Manual and Documentation Version 104," 1999.
[110] Sorenson, R.L., "A Computer Program to Generate Two-Dimensional Grids About Airfoils and Other Shapes by Use of Poisson's Equation," NASA TM-81198,1980.
[111] Steinert, W., Eisenberg, B., and Starken, H., "Design and Testing of a Controlled Diffusion Airfoil Cascade for Industrial Axial Flow Compressor Application," Journal of Turbomachinery, Vol.113, pp.583-590,1991.
[112] Wilcox, D. C, "Turbulence Modeling for CFD," DCW Industries, Inc. La Canada, CA, 1994.
[113] Chima, R.V., "A k-ω Turbulence Model for Quasi-Three-Dimensional Turbomachinery Flows," NASA TM-107051,1996.
[114] Robbins, W.H., and Dugan, J.F., "Prediction of Off-Design Performance of Multistage Compressors", NASA SP-36, Chapter X, pp.297-310,1965.
[115] Howell, A.R. and Bonham, R.P., "Overall and Stage Characteristics of Axial-Flow Compressors", Proceedings of the Institution of Mechanical Engineers, London, Vol.163, pp.235-248,1950.
[116] Novak, R.A., "Flow Field and Performance Map Computations for Axial-Flow Compressors and Turbines," AGARD Lecture Series No.83, pp.5.1-5.27,1976.
[117] Serovy, G.K., "Compressor and Turbine Performance Prediction System Development — Lessons from Thirty Years of History", AGARD Lecture Series No.83, pp.3-1 to 3-19,1976.
[118] Ni, R.H., "A Multiple Grid Scheme for Solving the Euler Equations," AIAA Journal, Vol.20, pp.1565-1571, 1982.
[119] Denton, J.D., "The Use of a Distributed Body Force to Simulate Viscous Effects in 3D Flow Calculations", ASME paper, 86-GT-144,1986.
[120] Rhie, C.M., Gleixner, A.J., et al., "Development and Application of a Multistage Navier-Stokes Solver: Part I—Multistage Modeling Using Body Forces and Deterministic Stresses", Journal of Turbomachinery, Vol.120, pp.215-223, 1998.
[121]LeJambre, C.R., et al., "Development and Application of a Multistage Navier-Stokes Solver: Part II — Application to a High Pressure Compressor Design", Journal of Turbomachinery, Vol.120, pp.205-214, 1998.
[122] Lieblein, S., "Aerodynamic Design of Axial Flow Compressors," NASA SP-36.
[123] Denton, J.D., "The Calculation of Three Dimensional Viscous Flow Through Multistage Turbomachines," ASME paper, 90-GT-19, 1990.
[124] Adamczyk, J.J., "Model Equation for Simulating Flows in Multistage Turbomachinery," ASME paper, 85-GT-220,1985.
[125] Rhie, C.M., et al., "Development and Application of a Multistage Navier-Stokes Solver, Part 1: Multistage Modeling Using Body-Forces and Deterministic Stresses," ASME paper, 95-GT-342, 1995.
[126] Boyer, K.M, O'Brien, W.F., "An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems," Journal of Turbomachinery, Vol.125, pp.475-481, 2003.
[127] Koch, C.C., and Smith, L.H., "Loss Sources and Magnitudes in Axial-Flow Compressors," Journal of Engineering for Power, pp.411-424, July 1976.
[128] Roberts, W.B., Serovy, GK. and Sandercock, D.M. "Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages," Journal of Engineering for Gas Turbines and Power, Vol.108, pp.131-137, 1985.
[129]Konig, W.M., Hennecke, D.K. and Fottner, L., "Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part I- A Model for Subsonic Flow," ASME paper, 94-GT-335,1994.
[130]Konig, W.M., Hennecke, D.K. and Fottner, L., "Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part II- A Model for Supersonic Flow," ASME paper, 94-GT-336, 1994.
[131] Arif Khalid, S., Khalsa, A.S., et al., "Endwall Blockage in Axial Compressors," ASME paper, 98-GT-188,1998.
[132]Hoeger, M., Lahmer, M., Dupslaff, M., and Fritsch, G., "A Correlation for Tip leakage Blockage in Compressor Blade Passages", ASME paper, 99-GT-388, 1999.
[133] Bloch, G. S., Copenhaver, W. W., and O'Brien, W. F., "A Shock Loss Model for Supersonic Compressor Cascades," Journal of Turbomachinery,Vol.121,pp.28-35,1999.
[134]Hah,C.,and Wennerstrom,A.J.,"Three- Dimensional Flowfields Inside a Transonic Compressor with Swept Blades," Journal of Turbomachinery,Vol.113,pp.241-251,1991.
[135]Gümmer,V.,Wenger,U.,and Kau,H.P.,"Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors," ASME Paper,GT2000-0491,2000.
[136]Beknev,V.S.,Egorov,I.N.,and Talyzina,V.S.,"Multicriterion Design Optimization of the Multistage Axial Flow Compressor",5~(th)ASME "COGEN-TURBO-V",Budapest,Hungary,1991.
[137]Gelmedov,F.S.,Talysina,V.S.,et al.,"Multistage Axial Flow Compressor's Development on the Basis of the Numerical Optimization Methods",3rd International Symposium on Aerothermodynamics of Internal Flows,1997.
[138]Talyzina,V.S.,“基于轴对称模型多级轴流压气机的数值优化”,高拯亚译,航空部606所,1993.
[139]桂幸民,“轴流风扇/压气机可控激波跨音级设计模型研究”,博士学位论文,北京航空航天大学,1993.
[140]Miller,G.R.,Lewis,G.W.,Jr.and Hartmann,M.J.,"Shock Losses in Transonic Compressor Blade Rows," Journal of Engineering for Power,pp.235-242,1961.
[141]Wassell,A.B."Reynolds Number Effects in Axial Compressor," Journal of Engineering for Power,Vol.90,1968.
[142]Wright,P.I.,Miller,D.C."An improved compressor performance prediction model," Conference on Turbomachinery.England:London,pp.69-82,1991.
[143]王英锋,胡俊,“雷诺数对轴流风扇/压气机性能和稳定性的影响”,南京航空航天大学学报,第36卷第2期,pp.145-149,2004.
[144]Smith,L.H.,and Yeh,H.,"Sweep and Dihedral Effect in Axial Flow Turbomachinery," Journal of Basic Engineering,Vol.85,1963.
[145]季路成,陈江,林峰,“轴流压气机设计中‘掠'的另类认识--Ⅱ:关于某转子‘掠'的分析”,中国工程热物理学会学术会议论文,编号:042093,2004.
[146]Frost,D.H.,"A Streamline Curvature Through-flow Computer Program for Analyzing the Flow through Axial-flow Turbomachines," R.&M.No.3687,1972.
[147]Denton,J.D.,"Lessons from Rotor 37," In:Proceedings of the 3rd International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows,1996.
[148]Reid L.,and Moore R.D.,"Design and Overall Performance of Four Highly Loaded,High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor," NASA-TP-1337,1978.
[149]陈志鹏,袁新,“全工况性能优化在压气机多级环境中的应用”,工程热物理学报,第29卷第2期,pp.221-224,2008.
[150]尉涵,袁新,“轴流压气机多叶片排的气动优化设计”,热能动力工程,第20卷第6期,pp.603-607,2005.
[151]伊卫林,“风扇/压气机三维气动优化设计方法及其应用研究”,博士学位论文,哈尔滨工业大学,2006.
[152]陈江,季路成,“多级轴流压气机气动特性优化”,工程热物理学报,第28卷第4期,pp.583-585,2007.
[153]Denton,J.D.,"Loss Mechanisms in Turbomachines," Journal of Turbomachinery,Vol.115,pp.621-656,1993.
[154]Smith,G.D.J.,and Cumpsty,N.A.,"Flow Phenomena in Compressor Casing Treatment," Journal of Engineering for Gas Turbines and Power,Vol.106,pp.532-541,1984.
[155]Wisler,D.C.,"Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing," Journal of Engineering for Gas Turbines and Power,Vol.107,pp.354-363,1985.
[156]Dittmar,J.H.,"Method for Noise Generated by Rotor-Wake-Stator Interaction,"AIAA Journal,Vol.15,pp.1342-1354,1977.
[157]Paterson,R.W.,Amiet,R.K.,"Isolated Airfoil-Tip Vortex Interaction Noise,"Journal of Aircraft,Vol.12,pp.34-41,1975.
[158]蔡娜,“非自模化区域内动叶叶尖间隙对气动-声学性能的影响”,空气动力学报,第17卷第3期,pp.257-261,1999.
[159]Booth,T.C.,"Importance of Tip Clearance Flows in Turbine Design," Tip Clearance Effects in Axial Turbomachines,VKI Lectures Series 1985-05.
[160]Bindon,J.P.,"The Measurement and Formation of Tip Clearance Loss," Journal of Turbomachinery,Vol.111,pp.257-263,1989.
[161]Rain,D.A.,"Tip Clearance Flow in Axial Flow Compressor and Pumps,"California Institute of Technology,Hydrodynamics and Mechanical Engineering Laboratories Report No.5,1954.
[162]Kirtley,K.R.,Beach,T.A.,and Adamczyk,J.J.,"Numerical Analysis of Secondary Flow in a Two-stage Turbine",AIAA 90-2356,1990.
[163]Chen,G.T.,Greitzer,E.M.,Tan,C.S.,and Marble,F.E.,"Similarity Analysis of Compressor Tip Clearance Flow Structure," Journal of Turbomachinery,Vol.113,pp.260-271,1991.
[164]Lakshminarayana,B.,and Horlock,J.,"Tip-Clearance Flow and Losses for an Isolated Compressor Blade," ARC R&M 3316,1962.
[165]Betz.A.,"Hydraulische Probleme," V.D.I.Verlag,1926.
[166]Storer,J.A.,and Cumpsty,N.A.,"Tip Leakage Flow in Axial Compressors,"Journal of Turbomachinery,Vol.113,pp.252-259,1991.
[167]Smith,L.H.,Jr.,"The Effect of Tip Clearance on the Peak Pressure Rise of Axial-Flow Fans and Compressors," ASME Symposium on Stall,pp.149-152,1958.
[168]Jinwoo Bae,et al.,"Active Control of Tip Clearance Flow in Axial Compressors," Journal of Turbomachinery,Vol.127,pp.352-362,2005.
[169]贾希诚,“叶轮机械中叶顶泄漏和间隙形态对气动性能影响的数值研究”,博士学位论文,中国科学院研究生院,2001.
[170]Wisler D.C.,and Beacher B.F.,"Improved compressor performance using recessed clearance(trenches)over tile rotor," AIAA Paper AIAA-86-1745,1986.
[171]卢新根等,“梯状间隙结构对轴流压气机影响的试验与数值模拟”,工程热物理学报,第26卷第2期,pp.234-236,2005.
[172]卢新根等,“轴流压气机机匣处理研究进展及评述”,力学进展,第36卷第2期,pp.222-232,2006.
[173]G.Scott McNulty,et al.,"The Impact of Forward Swept Rotors on Tip Clearance Flows in Subsonic Axial Compressors," Journal of Turbomachinery Vol.126,pp.445-454,2004.
[174]Dring, R.P., Joslyn, H.D., and Hardin, L.W., "An Investigation of Compressor Rotor Aerodynamics," Journal of Engineering for Power, Vol.104, pp.84-96, 1982.
[175]Dring, R.P., Joslyn, H.D., and Wagner, J.H., "Compressor Rotor Aerodynamics", AGARD-CP-351, Copenhagen, 1983.
[176] Joslyn, H., and Dring, R., "Axial Compressor Stator Aerodynamics," Journal of Engineering for Gas Turbines and Power, Vol.107, pp.485-493,1985.
[177] Dong, Y., Gallimore, S., and Hodson, H., "Three-Dimensional Flows and Loss Reduction in Axial Compressors," Journal of Turbomachinary, Vol.109, pp.354-360,1987.
[178]Schulz, H., and Gallus, H., "Experimental Investigation of the Three -Dimensional Flow in an Annular Compressor Cascade," Journal of Turbomachinary, Vol.110, pp.467-478,1988.
[179]Breugelmans, F., Carels, Y., and Demuth, M., "Influence of Dihedral on the Secondary Flow in a Two-Dimensional Compressor Cascade," Journal of Engineering for Gas Turbines and Power, pp.578-584, 1984.
[180]Weingold, H., Neubert, R., Behike, R., and Potter, G., "Reduction of Compressor Endwall Losses Through the Use of Bowed Stators," ASME Paper, 95-GT-380,1995.
[181]Barankiewicz, W., and Hathaway, M., "Impact of Variable-Geometry Stator Hub Leakage in a Low Speed Axial Compressor," ASME Paper, 98-GT-194, 1998.
[182] Demargne, A., and Longley, J., "The Aerodynamic Interaction of Stator Shroud Leakage and Mainstream Flows in Compressors," ASME Paper, 2000-GT-570, 2000.
[183] Wellborn, S., and Okiishi, T., "Effects of Shrouded Stator Flows on Multistage Axial Compressor Aerodynamic Performance," NASA CR 198536,1996.
[184] Hah, C., and Loellbach, J., "Development of Hub Corner Stall and its Influence on the Performance of Axial Compressor Blade Rows," Journal of Turbomachinary, Vol.121, pp.67-77,1999.
[185]Gbadebo, S., Cumpsty, N., and Hynes, T., "Three-Dimensional Separations in Axial Compressors," Journal of Turbomachinary, Vol.127, pp.331-339, 2005.
[186] Lei, V., Spakovszky, Z.S., and Greitzer, E.M., "A Criterion for Axial Compressor Hub-Comer Stall".ASME Paper,GT2006-91332,2006.
[187]Nash,J.F.,and MacDonald,A.G.J.,"The Calculation of Momentum Thickness in a Turbulent Boundary Layer at Mach Numbers up to Unity," Aeronautical Research Council C.P.No.963,1967.
[188]吴国钏等,“附面层理论”,航空工业出版社,1989.
[189]Peacock,R.,"Boundary-Layer Suction to Eliminate Comer Separation in Cascades of Airfoils," Tech.rep.,Reports and Memoranda,No.3663,Engineering Department,University of Cambridge,1965.
[190]Stratford,B.,"The prevention of separation and flow reversal in the corners of compressor blade cascades," In Aeronautical Journal,pp.249-256,1973.
[191]Culley,D.,Bright,M.,Prahst,P.,and Strazisar,A.,"Active Flow Separation Control of a Stator Vane Using Embedded Injection in a Multistage Compressor Environment," Journal of Turbomachinary,Vol.126,pp.24-34,2003.
[192]Kirtley,K.,Graziosi,P.,Wood,P.,Beacher,B.,and Shin,H.-W.,"Design and Test of an Ultra-Low Solidity Flow-Controlled Compressor Stator," Journal of Turbomachinary,pp.689-698,2005.
[193]Yamaguchi,N.,et al.,"Secondary-Loss Reduction by Forward-Skewing of Axial Compressor Rotor Blading," Proceedings of 1991 Yokohama International Gas Turbine Congress,2:61-68,1991.
[194]蒋洪德,“美国航空发动机和计算流体力学发展情况介绍”,工程热物理能源利用学科,气动热力学发展战略研讨会专题报告汇编,北京,1989.
[195]Breugelmans,F.,"Influence of Incidence Angle on the secondary Flow in Compressor Cascade with Different Dihedral Distribution," ISABE Paper,85-7078,1985.
[196]Shang,E.,et al.,"The Experimental Investigations on the Compressor Cascades with Leaned and Curved Blades," ASME Paper,93-GT-50,1993.
[197]任汝根,周盛,“叶轮机械中的非定常流动”,燃气涡轮试验与研究,第4卷第4期,pp.1-24,1991.
[198]Chen,J.and Ji,L.C.,"Edge Matching--Part Ⅱ:Numerical Investigations,"ASME Paper,GT-2005-68477,2005.
[199]陈江,季路成,“缘线匹配技术在轴流压气机设计中的应用探索”,工程热物理学报,第25卷增刊1,pp.35-38,2004.
[200]Majjigi,R.K.and Gliebe,P.R.,"Development of a Rotor Wake/Vortex Model,Volume 1-Final Technical Report," NASA CR-174849,Contract NAS3-23681,June 1984.
[201]Nathan J.Heidegger,Edward J.Hall,and Robert A.,"Delaney,Follow-on Low Noise Fan Aerodynamic Study:Task 15-Final Report,"NASA/CR-1999-206599,1999.
[202]Poensgen,C.,and Gallus,H.E.,"Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field.Part 2:Unsteady Flow Field Downstream of Stator," Journal of Turbomachinery,Vol.113,pp.180-197,1991.
[203]侯安平,熊劲松,周盛,“轴流压气机尾流撞击效应机理的数值模拟”,北京航空航天大学学报,第31卷第9期,pp.944-948,2005.
[204]Suder,K.L.,"Blockage Development in a.Transonic,Axial Compressor Rotor,"ASME Paper,97-GT-394,1997.
[205]孙晓峰,周盛,“气动声学”,国防工业出版社,1994.
[206]李妍,景小东,孙晓峰,“降低叶轮机转/静干涉噪声的几种技术途径探讨”,工程热物理学会1999年学术会议论文,编号:992053,1999.
[2]江泽民,“对中国能源问题的思考”,上海交通大学学报,第42卷第3期,pp.345-359,2008.
[3]Layne,A.W.,et al.,"The US Department of Energy's Advanced Turbine Systems Program," ASME Paper,98-GT-141,1998.
[4]蒋洪德,“美国高性能涡轮发动机技术(HPTET)计划”,压气机文集第一分册.航空科技情报研究所,pp.252-260,1989.
[5]季路成,陈江,“从IHPTET到VAATE计划的技术方向探析”,中国工程热物理学会热机气动热力学会议论文集,编号:052086,北京,2005.
[6]方昌德,“航空发动机的发展前景”,航空发动机,第30卷第1期,pp.1-5,2004.
[7]刘大响,“世界航空动力技术的现状及发展动向”,北京航空航天大学学报,第28卷第5期,pp.490-496,2002.
[8]Michael T.Tong,Scott M.Jones,et al.,"A Probabilistic Assessment of NASA Ultra-Efficient Engine Technologies for a Large Subsonic Transport," ASME Paper,GT2004-54385,2004.
[9]Michael T.Tong,and Scott M.Jones,"An Updated Assessment of NASA Ultra-Efficient Engine Technologies," ISABE Paper,2005-1163,2005.
[10]Nick Baker,Andrew Rolt,et al.,"New Environmental Friendly Aero Engine Core Concepts," ISABE Paper,2007-1120,2007.
[11]梁春华,“Tech56技术计划即将结束”,航空发动机,第30卷第1期,pp.46,2004.
[12]Jean-Jacques Korsia,"VITAL-European R&D Program for Greener Aero-Engines," ISABE Paper,2007-1118,2007.
[13]Shigeru Hayashi,"An Overview of JAXA's TechCLEAN Project - Technology Development Project for Environmentally Compatible Aeroengines," ISABE Paper,2007-1010,2007.
[14]陈懋章,“中国航空发动机高压压气机发展的几个问题”,航空发动机,第 32卷第2期,pp.5-12,2006.
[15]Jones,M.J.,Birch,N.T.and Bradbrook,S.J.,"Evolutions in Aircraft Engine Design and a Vision for the Future," ISABE Paper,2001-1014,2001.
[16]Cumpsty,N.A.,"Compressor Aerodynamics," Krieger Publishing Company,2004.
[17]Steffens,K.,"Advanced Compressor Technology - Key Success Factor for Competitiveness in Modern Aero-Engines," ISABE Paper,2001-1009,2001.
[18]Manish Chouhan,Kota Venkata Kaundinya,and Bhaskar Roy,"Experimental Study of Stability Improvement by Tip Injection at Mid Chord Region of Axial Compressor," ISABE Paper,2007-1267,2007.
[19]Storer,J.A.,and Cumpsty,N.A.,"An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors," Journal of Turbomachinery,Vol.116,pp.648-655,1994.
[20]邓向阳,“压气机叶顶间隙流的数值模拟研究”,博士论文,中国科学院研究生院,2006.
[21]张靖煊,林峰,陈静宜,聂超群,“旋转进口畸变条件下轴流压气机叶项间隙流非定常特征及其与旋转失速的关联性研究”,工程热物理学报,第29卷第3期,pp.390-394,2008.
[22]徐纲,聂超群,黄伟光,陈静宜,“低速轴流压气机顶部微量喷气控制失速机理的数值模拟”,工程热物理学报,第25卷第1期,pp.37-40,2004.
[23]陈懋章,“风扇/压气机技术发展和对今后工作的建议”,航空动力学报,第17卷第1期,PP.1-15,2002.
[24]Supplee,H.H.,"The Gas Turbine," 1910.
[25]Wisler,D.C.,"Advanced Compressor and Fan Systems," GE Aircraft Engines,1988.
[26]Freeman,J.H.,"Design of A Multi-spool,High-speed,Counter-Rotating,Aspirated Compressor," AD-A385286,2000.
[27]陈懋章,“叶轮机气动力学研究及其发展趋势”,中国航空学会航空百年学术论坛动力分坛论文集(一),pp.19-37,北京,2003.
[28]季路成,王延荣,邵卫卫,王宝臣,“缘线匹配主导的叶轮机非定常设计”,中国工程热物理学会2007年学术会议论文,编号:072012,2007.
[29]Wu,C.H.,"A General Theory of Three-Dimensional Flow in Subsonic and Supersonic Turbomachines of Axial-,Radial,and Mixed-Flow Types",NACA TN2604,1952.
[30]Wennerstrom,A.J.,and Frost,G.R.,"Design of a 1500ft/sec,Transonic,High-Through-Flow,Single-Stage Axial-Flow Compressor with Low Hub/Tip Ratio," AFARL TR 76-59,1976.
[31]刘宝杰,邹正平等,“叶轮机计算流体动力学技术现状与发展趋势”,航空学报,第23卷第5期,pp.394-404,2002.
[32]季路成,“轴流叶轮机转子/静子干扰非定常流动探索”,博士学位论文,北京航空航天大学,1998.
[33]陈江,“叶轮机非定常气动设计技术探索”,博士学位论文,北京航空航天大学,2004.
[34]Hobbs,D.,and Weingold,H.,"Development of Controlled Diffusion Airfoils for Multistage Compressor Application," Journal of Engineering for Gas Turbines Power,Vol.106,pp.271-278,1984.
[35]He,L.,Chen,T.,et al.,"Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines," ASME Paper,GT-2002-30355,2002.
[36]Curtis,E.M.,and Hodson,H.P.et al.,"Development of Blade Profiles for Low Pressure Turbine Applications," Journal of Turbomachinery,Vol.119,pp.531-538,1997.
[37]季路成,陈江,黄海波等,“非定常环境下叶栅性能的数值研究”,工程热物理学报,第24卷第2期,pp.211-215,2003.
[38]Wennerstrom,A.J.,"Low Aspect Ratio Axial Flow Compressors - Why and What It Means," SAE,Cliff Garrett Turbomachinery Award Lecture,3~(rd),Long Beach,CA;United States;14 Oct.1986.
[39]http://www.pr.afrl.af.mil/division/prt/ihptet/ihptet.html.
[40]陈光,“航空发动机结构设计分析”,北京航空航天大学出版社,2006.
[41]Stephane Hiernaux,Celine Lebas,et al.,"Next Generation Booster," ISABE Paper,2007-1347,2007.
[42]Gunter Wilfert,Joerg Sieber,et al.,"New Environmental Friendly Aero Engine Core Concepts," ISABE Paper,2007-1120,2007.
[43]Adamczyk,J.J.,"Model Equation for Simulating Flows in Multistage Turbomachinery," NASA TM-86869,1984.
[44]Rhie,C.M.,et al.,"Development and Application of a Multistage Navier-Stokes Solver,Part Ⅰ:Multistage Modeling Using Body-Forces and Deterministic Stresses," ASME paper,95-GT-342.,1995.
[45]周盛,侯安平等,“关于轴流压气机的非定常两代流型”,航空学报,第26卷第1期,pp.1-7,2005.
[46]Ji,L.C.and Chen,J.,"Edge Matching--Part Ⅰ:Theory and Implementation,"ASME paper,GT-2005-68474,2005.
[47]Greitzer,E.M.,"Review--Axial Compressor Stall Phenomena," Journal of Fluids Engineering,Vol.102,pp.134-151,1980.
[48]Johnsen,I.,and Bullock,R.,"Aerodynamical Design of Axial-Flow Compressors," NASA SP-36,1965.
[49]Korn,D.,"Numerical Design of Transonic Cascades," ERDA Research and Development Report C00-3077-72,1975.
[50]Schmidt,E.,"Computation of Supercritical Compressor and Turbine Cascades With a Design Method for Transonic Flows," ASME Paper,79-GT-30,1979.
[51]Bauer F,Garabedian P,and Korn D."Supercdtical Wine Section,Lecture Notes in Economics and Math Systems," Springer-Verlag New York,Section 1.1972,66;Section 2.1975,108.
[52]Garabedian P,and Korn D."A Systematic Method for Computer Design of Supercritical Airfoils in Cascade," Communications on Pure and Applied Mathematics,Vol.29,pp.369-382,1976.
[53]Korn D.,"Numerical Design of Transonic Cascade," ERDA Research and Development Report,Coo- 3077- 72,1975.
[54]Ihor S.Diakunchak,Greg R.Gaul,Gerry McQuiggan,and Leslie R.Southall,"Siemens Westinghouse Advanced Turbine Systems Program Final Summary,"Journal of Engineering for Gas Turbines and Power,Vol.126,pp.524-530,2004.
[55]Dong Y.,Cumpsty N.A.,"Compressor Blade Boundary Layers:Part 1-Test Facility and Measurements with Incident Wakes," Journal of Turbomachinery,Vol.112,pp.222-230,1990.
[56]Schulz H.D.,Gallus H.E.,Lakshminarayana B.,"Three-Dimensional Separated Flow Field in the Endwall Region of An Annular Compressor Cascade in the Presence of Rotor-Stator Interaction.Part 1:Quasi-Steady Flow Field and Comparison with Steady-State Data," Journal of Turbomachinery,Vol.112, pp.669-678,1990.
[57]Schulz H.D.,Gallus H.E.,Lakshminarayana B.,"Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction.Part 2:Unsteady Flow and Pressure Field,"Journal of Turbomachinery,Vol.112,pp.679-690,1990.
[58]Halstead,D.E.,Wisler,D.C.,Okiishi,T.H.,et al.,"Boundary Layer Development in Axial Compressors and Turbines:Part 1:Composite Picture,"Journal of Turbomachinery,Vol.119,pp 114-127,1997.
[59]Halstead,D.E.,Wisler,D.C.,et al.,"Boundary Layer Development in Axial Compressors and Turbines:Part 2 of 4-Compressors," Journal of Turbomachinery,Vol.119,pp.426-444,1997.
[60]Tiedemann,M.,Kost,F.,"Unsteady Boundary Layer Transition on a High Pressure Turbine Rotor Blade",ASME paper,99-GT- 194,1999.
[61]Hodson,H.P.,Huntsman,I.,Steele,A.B.,"An Investigation of Boundary Layer Development in a Multistage LP Turbine," ASME paper,93-GT-310,1993.
[62]Gallimore S.J.,John Bolger,and Cumpsty N.A.,"The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading--Part Ⅰ:University Research and Methods Development," Journal of Turbomachinery,Vol.124,pp.521-532,2002.
[63]Gallimore S.J.,John Bolger,and Cumpsty N.A.,"The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading-Part Ⅱ Low and High-Speed Designs and Test Verification," Journal of Turbomachinery,Vol.124,pp.533-541,2002.
[64]Wadia,A.R.,Szucs,P.N.,and Crall,D.W.,"Inner Workings of Aerodynamic Sweep," Journal of Turbomachinery,Vol.120,pp.671-682,1998.
[65]Denton,J.D.,and Xu L.,"The Effects of Lean and Sweep on Transonic Fan Performance," ASME Paper,GT-2002-30327,2002.
[66]Ji,L.C.,Chen J.,and Lin F.,"Review and Understanding on Sweep in Axial Compressor Design," ASME Paper,GT2005-68473,2005.
[67]王仲奇,苏杰先,钟兢军,“弯曲叶片栅内减少能量损失机理研究的新进展”,工程热物理学报,第15卷第2期,pp.147-152,1994.
[68]钟兢军,苏杰先,王仲奇,“压气机叶栅壁面拓扑和二次流结构分析”,工程热物理学报,第19卷第1期,pp.40-44,1998.
[69]王会社,“不同叶型和叶片积叠线及弯曲角对压气机叶栅流场的影响”,博士学位论文,哈尔滨工业大学工学,2001.
[70]Wang Zhongqi,Lai Shengkai,and Xu Wenyuan."Aerodynamic Calculation of Turbine Stator Cascades with Curvilinear Leaned Blades and Some Experimental Results".Symposium Paper of 5th ISABE,pp.30.1-30.9,India,1981.
[71]Axel Fischer,Walter Riess,and Joerg R.Seume,"Performance of Strongly Bowed Stators in a Four-Stage High-Speed Compressor," Journal of Turbomachinery,Vol.126,pp.333-338,2004.
[72]Wisler D.C.,and Beacher B.F.,"Improved compressor performance using recessed clearance(trenches)over tile rotor",AIAA Paper,AIAA-86-1745.1986.
[73]卢新根等,“梯状间隙结构对轴流压气机影响的试验与数值模拟”,工程热物理学报,第26卷第2期,pp.234-236,2005.
[74]卢新根,楚武利,朱俊强等,“轴流压气机机匣处理研究进展及评述”,力学进展,第36卷第2期,pp.222-232,2006.
[75]Smith,L.H.,"Casing Boundary Layers in Multistage Axial Flow Compressors,"Flow Research in Blading,Edited by Elsevier Publishing Company,1970.
[76]Deregel,P.,and Tan,C.S.,"Impact of Rotor Wakes on Steady-State Axial Compressor Performance," ASME paper,96-GT-253,1996.
[77]Ng,W.F.,and Epstein,A.H.,"Unsteady Losses in Transonic Compressors,"ASME paper,84-GT-183,1984.
[78]Dawes,W.N.,"A Numerical Study of The Interaction of a Transonic Compressor Rotor Over-Tip Leakage Vortex with the Following Stator Blade Row," ASME paper,94-GT-156,1994.
[79]Walker,G.J.and Oliver,A.R.,"The Effect of Interaction Between Wakes from Blade Rows in an Axial Flow Compressor on the Noise Generated by Blade Interaction," ASME paper,72-GT-15,1972.
[80]Huber,F.W.,Johnson,P.D.,Sharma,O.P.,et al.,"Performance Improvement through Indexing of Turbine Airfoils,Part 1-Experimental Investigation,"ASME paper,95-GT-27,1995.
[81]Eulitz,F.,Engel,K.,and Gebing,H.,"Numerical Investigation of the Clocking Effects in a Multistage Turbine," ASME paper,96-GT-26,1996.
[82]Dorney,D.J.,and Sharma,O.P.,"A Study of Turbine Performance Increases through Airfoil Clocking," AIAA paper,96-2816,1996.
[83]Cizmas,P.G.A.,Dorney,D.J.,"The Influence of Clocking on Unsteady Forces of Compressor and Turbine Blades," ISABE paper,99-72,1999.
[84]Tiedemann,M.,and Kost,F.,"Some Aspects of Wake-Wake Interactions Regarding Turbine Stator Clocking," Journal of Turbomachinery,Vol.123,pp.526-533,2001.
[85]Dorney,D.J.,Croft,R.R.,Sondak,D.L.,et al.,"Computational Study of Clocking an Embedded Stage in a 4-Stage Industrial Turbine," ASME paper,2001-GT-0509,2001.
[86]Arnone,A.,Marconcini,M.,Pacciani,R.,et al.,"Numerical Investigation of Airfoil Clocking in a Three-Stage Low Pressure Turbine," ASME paper,2001-GT-0303,2001.
[87]He,L.,Chen,T.,et al.,"Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines," ASME paper,2002-GT-30355,2002.
[88]侯安平,周盛,“轴流式叶轮机时序效应的机理探讨”,航空动力学报,第18卷第1期,pp.70-75,2003.
[89]闫朝,季路成,陈江,徐建中,“轴向间距对时序效应影响的研究”,工程热物理学报,第25卷第2期,pp.220-222,2004.
[90]季路成,阎朝,陈江,“将缘线匹配应用于最大化三维时序效益”,航空动力学报,第21卷第3期,pp.467-473,2006.
[91]阎朝,“关于应用缘线匹配最大化时序效应潜能的初探”,博士学位论文,中国科学院研究生院,2004.
[92]Wennerstrom,A.J.,"Highly Loaded Axial Flow Compressors:History and Current Developments," Journal of Turbomachinery,Vol.112,pp.567-578,1990.
[93]Dunker,R.J.,"A Shock Loss Model for Supercritical Subsonic Flows in Transonic Axial Flow Compressors," Transonic and Supersonic Phenomena in Turbomachines,pp.27.1-27.15,AGARD-CP-401,1987.
[94]余华蔚,兰发祥,程荣辉,“高马赫数、大弯角静叶型设计与分析”,燃气涡轮试验与研究,第13卷第2期,PP.17-21,2000.
[95]Lubenstein,et al.,"Airfoil Shape for Arrays of Airfoils," U.S.Patent:4,431,376,1984.
[96]Dunham,J.,"Aerodynamic Losses in Turbomachines," AGARD-CP-571,Loss Mechanism and Unsteady Flows in Turbomachines,K1-K13,1996.
[97]程荣辉,周拜豪等,“定制叶型技术及其在压气机设计中的应用”,燃气涡轮试验与研究,第13卷第1期,pp.15-22,2000.
[98]Hoheisel,H.and Seyb,N.J.,"The Boundary Layer Behavior of Highly Loaded Compressor Cascade at Transonic Flow Conditions," Transonic and Supersonic Phenomena in Turbomachines,pp.4.1-4.17,AGARD-CP-401,1987.
[99]Koller,U.,Monig,R.,Kusters,B.,and Schreiber,H.,"Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part Ⅰ:Design and Optimization," Journal of Turbomachinery,Vol.122,pp.397-405,2000.
[100]Kusters,B.,Schreiber,H.,Koller,U.,and Monig,R.,"Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part Ⅱ:Experimental and Theoretical Analysis," Journal of Turbomachinery,Vol.122,pp.406-415,2000.
[101]Sonada,T.,Yamaguchi,Y.,Arima,T.,Olhofer,M.,Sendhoff,B.,and Schreiber,H.,"Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition - Part Ⅰ:Design and Optimization," ASME Paper,GT2003-38458,2003.
[102]Schreiber,H.,Steinert,W.,Sonada,T.,and Arima,T.,"Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition - Part Ⅱ:Experimental and Numerical Analysis," ASME Paper,GT2003-38477,2003.
[103]Benini,E.,and Toffolo,A.,"Development of High-Performance Airfoils for Axial Flow Compressors Using Evolutionary Computation," Journal of Propulsion and Power,Vol.18,pp.544-554,2002.
[104]Xu,C.and Amano,R.S.,"A Turbomachinery Blade Design and Optimization Procedure," ASME Paper,GT-2002-30541,2002.
[105]Rai,M.,and Madavan,N.,"Application of Artificial Neural Networks to Design of Turbomachinery Airfoils," Journal of Propulsion and Power,Vol.17,pp.176-183,2001.
[106]Yiu,K.F.C.,and Zangeneh,M.,"Three-Dimensional Automatic Optimization Method for Turbomachinery Blade Design," Journal of Propulsion and Power,Vol.16,pp.1174-1181,2000.
[107]Song B.,and Wing F.Ng,"Performance and Flow Characteristics of an Optimized Supercritical Compressor Stator Cascade," Journal of Turbomachinery, Vol.128, pp.435-443, 2006.
[108] Chima, R.V., "RVCQ3D - Rotor Viscous Code Quasi-3-D User's Manual and Documentation Version 303," 1999.
[109] Chima, R.V., "GRAPE 2-D Grid Generator for Turbomachinery User's Manual and Documentation Version 104," 1999.
[110] Sorenson, R.L., "A Computer Program to Generate Two-Dimensional Grids About Airfoils and Other Shapes by Use of Poisson's Equation," NASA TM-81198,1980.
[111] Steinert, W., Eisenberg, B., and Starken, H., "Design and Testing of a Controlled Diffusion Airfoil Cascade for Industrial Axial Flow Compressor Application," Journal of Turbomachinery, Vol.113, pp.583-590,1991.
[112] Wilcox, D. C, "Turbulence Modeling for CFD," DCW Industries, Inc. La Canada, CA, 1994.
[113] Chima, R.V., "A k-ω Turbulence Model for Quasi-Three-Dimensional Turbomachinery Flows," NASA TM-107051,1996.
[114] Robbins, W.H., and Dugan, J.F., "Prediction of Off-Design Performance of Multistage Compressors", NASA SP-36, Chapter X, pp.297-310,1965.
[115] Howell, A.R. and Bonham, R.P., "Overall and Stage Characteristics of Axial-Flow Compressors", Proceedings of the Institution of Mechanical Engineers, London, Vol.163, pp.235-248,1950.
[116] Novak, R.A., "Flow Field and Performance Map Computations for Axial-Flow Compressors and Turbines," AGARD Lecture Series No.83, pp.5.1-5.27,1976.
[117] Serovy, G.K., "Compressor and Turbine Performance Prediction System Development — Lessons from Thirty Years of History", AGARD Lecture Series No.83, pp.3-1 to 3-19,1976.
[118] Ni, R.H., "A Multiple Grid Scheme for Solving the Euler Equations," AIAA Journal, Vol.20, pp.1565-1571, 1982.
[119] Denton, J.D., "The Use of a Distributed Body Force to Simulate Viscous Effects in 3D Flow Calculations", ASME paper, 86-GT-144,1986.
[120] Rhie, C.M., Gleixner, A.J., et al., "Development and Application of a Multistage Navier-Stokes Solver: Part I—Multistage Modeling Using Body Forces and Deterministic Stresses", Journal of Turbomachinery, Vol.120, pp.215-223, 1998.
[121]LeJambre, C.R., et al., "Development and Application of a Multistage Navier-Stokes Solver: Part II — Application to a High Pressure Compressor Design", Journal of Turbomachinery, Vol.120, pp.205-214, 1998.
[122] Lieblein, S., "Aerodynamic Design of Axial Flow Compressors," NASA SP-36.
[123] Denton, J.D., "The Calculation of Three Dimensional Viscous Flow Through Multistage Turbomachines," ASME paper, 90-GT-19, 1990.
[124] Adamczyk, J.J., "Model Equation for Simulating Flows in Multistage Turbomachinery," ASME paper, 85-GT-220,1985.
[125] Rhie, C.M., et al., "Development and Application of a Multistage Navier-Stokes Solver, Part 1: Multistage Modeling Using Body-Forces and Deterministic Stresses," ASME paper, 95-GT-342, 1995.
[126] Boyer, K.M, O'Brien, W.F., "An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems," Journal of Turbomachinery, Vol.125, pp.475-481, 2003.
[127] Koch, C.C., and Smith, L.H., "Loss Sources and Magnitudes in Axial-Flow Compressors," Journal of Engineering for Power, pp.411-424, July 1976.
[128] Roberts, W.B., Serovy, GK. and Sandercock, D.M. "Modeling the 3-D Flow Effects on Deviation Angle for Axial Compressor Middle Stages," Journal of Engineering for Gas Turbines and Power, Vol.108, pp.131-137, 1985.
[129]Konig, W.M., Hennecke, D.K. and Fottner, L., "Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part I- A Model for Subsonic Flow," ASME paper, 94-GT-335,1994.
[130]Konig, W.M., Hennecke, D.K. and Fottner, L., "Improved Blade Profile Loss and Deviation Angle Models for Advanced Transonic Compressor Bladings: Part II- A Model for Supersonic Flow," ASME paper, 94-GT-336, 1994.
[131] Arif Khalid, S., Khalsa, A.S., et al., "Endwall Blockage in Axial Compressors," ASME paper, 98-GT-188,1998.
[132]Hoeger, M., Lahmer, M., Dupslaff, M., and Fritsch, G., "A Correlation for Tip leakage Blockage in Compressor Blade Passages", ASME paper, 99-GT-388, 1999.
[133] Bloch, G. S., Copenhaver, W. W., and O'Brien, W. F., "A Shock Loss Model for Supersonic Compressor Cascades," Journal of Turbomachinery,Vol.121,pp.28-35,1999.
[134]Hah,C.,and Wennerstrom,A.J.,"Three- Dimensional Flowfields Inside a Transonic Compressor with Swept Blades," Journal of Turbomachinery,Vol.113,pp.241-251,1991.
[135]Gümmer,V.,Wenger,U.,and Kau,H.P.,"Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors," ASME Paper,GT2000-0491,2000.
[136]Beknev,V.S.,Egorov,I.N.,and Talyzina,V.S.,"Multicriterion Design Optimization of the Multistage Axial Flow Compressor",5~(th)ASME "COGEN-TURBO-V",Budapest,Hungary,1991.
[137]Gelmedov,F.S.,Talysina,V.S.,et al.,"Multistage Axial Flow Compressor's Development on the Basis of the Numerical Optimization Methods",3rd International Symposium on Aerothermodynamics of Internal Flows,1997.
[138]Talyzina,V.S.,“基于轴对称模型多级轴流压气机的数值优化”,高拯亚译,航空部606所,1993.
[139]桂幸民,“轴流风扇/压气机可控激波跨音级设计模型研究”,博士学位论文,北京航空航天大学,1993.
[140]Miller,G.R.,Lewis,G.W.,Jr.and Hartmann,M.J.,"Shock Losses in Transonic Compressor Blade Rows," Journal of Engineering for Power,pp.235-242,1961.
[141]Wassell,A.B."Reynolds Number Effects in Axial Compressor," Journal of Engineering for Power,Vol.90,1968.
[142]Wright,P.I.,Miller,D.C."An improved compressor performance prediction model," Conference on Turbomachinery.England:London,pp.69-82,1991.
[143]王英锋,胡俊,“雷诺数对轴流风扇/压气机性能和稳定性的影响”,南京航空航天大学学报,第36卷第2期,pp.145-149,2004.
[144]Smith,L.H.,and Yeh,H.,"Sweep and Dihedral Effect in Axial Flow Turbomachinery," Journal of Basic Engineering,Vol.85,1963.
[145]季路成,陈江,林峰,“轴流压气机设计中‘掠'的另类认识--Ⅱ:关于某转子‘掠'的分析”,中国工程热物理学会学术会议论文,编号:042093,2004.
[146]Frost,D.H.,"A Streamline Curvature Through-flow Computer Program for Analyzing the Flow through Axial-flow Turbomachines," R.&M.No.3687,1972.
[147]Denton,J.D.,"Lessons from Rotor 37," In:Proceedings of the 3rd International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows,1996.
[148]Reid L.,and Moore R.D.,"Design and Overall Performance of Four Highly Loaded,High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor," NASA-TP-1337,1978.
[149]陈志鹏,袁新,“全工况性能优化在压气机多级环境中的应用”,工程热物理学报,第29卷第2期,pp.221-224,2008.
[150]尉涵,袁新,“轴流压气机多叶片排的气动优化设计”,热能动力工程,第20卷第6期,pp.603-607,2005.
[151]伊卫林,“风扇/压气机三维气动优化设计方法及其应用研究”,博士学位论文,哈尔滨工业大学,2006.
[152]陈江,季路成,“多级轴流压气机气动特性优化”,工程热物理学报,第28卷第4期,pp.583-585,2007.
[153]Denton,J.D.,"Loss Mechanisms in Turbomachines," Journal of Turbomachinery,Vol.115,pp.621-656,1993.
[154]Smith,G.D.J.,and Cumpsty,N.A.,"Flow Phenomena in Compressor Casing Treatment," Journal of Engineering for Gas Turbines and Power,Vol.106,pp.532-541,1984.
[155]Wisler,D.C.,"Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing," Journal of Engineering for Gas Turbines and Power,Vol.107,pp.354-363,1985.
[156]Dittmar,J.H.,"Method for Noise Generated by Rotor-Wake-Stator Interaction,"AIAA Journal,Vol.15,pp.1342-1354,1977.
[157]Paterson,R.W.,Amiet,R.K.,"Isolated Airfoil-Tip Vortex Interaction Noise,"Journal of Aircraft,Vol.12,pp.34-41,1975.
[158]蔡娜,“非自模化区域内动叶叶尖间隙对气动-声学性能的影响”,空气动力学报,第17卷第3期,pp.257-261,1999.
[159]Booth,T.C.,"Importance of Tip Clearance Flows in Turbine Design," Tip Clearance Effects in Axial Turbomachines,VKI Lectures Series 1985-05.
[160]Bindon,J.P.,"The Measurement and Formation of Tip Clearance Loss," Journal of Turbomachinery,Vol.111,pp.257-263,1989.
[161]Rain,D.A.,"Tip Clearance Flow in Axial Flow Compressor and Pumps,"California Institute of Technology,Hydrodynamics and Mechanical Engineering Laboratories Report No.5,1954.
[162]Kirtley,K.R.,Beach,T.A.,and Adamczyk,J.J.,"Numerical Analysis of Secondary Flow in a Two-stage Turbine",AIAA 90-2356,1990.
[163]Chen,G.T.,Greitzer,E.M.,Tan,C.S.,and Marble,F.E.,"Similarity Analysis of Compressor Tip Clearance Flow Structure," Journal of Turbomachinery,Vol.113,pp.260-271,1991.
[164]Lakshminarayana,B.,and Horlock,J.,"Tip-Clearance Flow and Losses for an Isolated Compressor Blade," ARC R&M 3316,1962.
[165]Betz.A.,"Hydraulische Probleme," V.D.I.Verlag,1926.
[166]Storer,J.A.,and Cumpsty,N.A.,"Tip Leakage Flow in Axial Compressors,"Journal of Turbomachinery,Vol.113,pp.252-259,1991.
[167]Smith,L.H.,Jr.,"The Effect of Tip Clearance on the Peak Pressure Rise of Axial-Flow Fans and Compressors," ASME Symposium on Stall,pp.149-152,1958.
[168]Jinwoo Bae,et al.,"Active Control of Tip Clearance Flow in Axial Compressors," Journal of Turbomachinery,Vol.127,pp.352-362,2005.
[169]贾希诚,“叶轮机械中叶顶泄漏和间隙形态对气动性能影响的数值研究”,博士学位论文,中国科学院研究生院,2001.
[170]Wisler D.C.,and Beacher B.F.,"Improved compressor performance using recessed clearance(trenches)over tile rotor," AIAA Paper AIAA-86-1745,1986.
[171]卢新根等,“梯状间隙结构对轴流压气机影响的试验与数值模拟”,工程热物理学报,第26卷第2期,pp.234-236,2005.
[172]卢新根等,“轴流压气机机匣处理研究进展及评述”,力学进展,第36卷第2期,pp.222-232,2006.
[173]G.Scott McNulty,et al.,"The Impact of Forward Swept Rotors on Tip Clearance Flows in Subsonic Axial Compressors," Journal of Turbomachinery Vol.126,pp.445-454,2004.
[174]Dring, R.P., Joslyn, H.D., and Hardin, L.W., "An Investigation of Compressor Rotor Aerodynamics," Journal of Engineering for Power, Vol.104, pp.84-96, 1982.
[175]Dring, R.P., Joslyn, H.D., and Wagner, J.H., "Compressor Rotor Aerodynamics", AGARD-CP-351, Copenhagen, 1983.
[176] Joslyn, H., and Dring, R., "Axial Compressor Stator Aerodynamics," Journal of Engineering for Gas Turbines and Power, Vol.107, pp.485-493,1985.
[177] Dong, Y., Gallimore, S., and Hodson, H., "Three-Dimensional Flows and Loss Reduction in Axial Compressors," Journal of Turbomachinary, Vol.109, pp.354-360,1987.
[178]Schulz, H., and Gallus, H., "Experimental Investigation of the Three -Dimensional Flow in an Annular Compressor Cascade," Journal of Turbomachinary, Vol.110, pp.467-478,1988.
[179]Breugelmans, F., Carels, Y., and Demuth, M., "Influence of Dihedral on the Secondary Flow in a Two-Dimensional Compressor Cascade," Journal of Engineering for Gas Turbines and Power, pp.578-584, 1984.
[180]Weingold, H., Neubert, R., Behike, R., and Potter, G., "Reduction of Compressor Endwall Losses Through the Use of Bowed Stators," ASME Paper, 95-GT-380,1995.
[181]Barankiewicz, W., and Hathaway, M., "Impact of Variable-Geometry Stator Hub Leakage in a Low Speed Axial Compressor," ASME Paper, 98-GT-194, 1998.
[182] Demargne, A., and Longley, J., "The Aerodynamic Interaction of Stator Shroud Leakage and Mainstream Flows in Compressors," ASME Paper, 2000-GT-570, 2000.
[183] Wellborn, S., and Okiishi, T., "Effects of Shrouded Stator Flows on Multistage Axial Compressor Aerodynamic Performance," NASA CR 198536,1996.
[184] Hah, C., and Loellbach, J., "Development of Hub Corner Stall and its Influence on the Performance of Axial Compressor Blade Rows," Journal of Turbomachinary, Vol.121, pp.67-77,1999.
[185]Gbadebo, S., Cumpsty, N., and Hynes, T., "Three-Dimensional Separations in Axial Compressors," Journal of Turbomachinary, Vol.127, pp.331-339, 2005.
[186] Lei, V., Spakovszky, Z.S., and Greitzer, E.M., "A Criterion for Axial Compressor Hub-Comer Stall".ASME Paper,GT2006-91332,2006.
[187]Nash,J.F.,and MacDonald,A.G.J.,"The Calculation of Momentum Thickness in a Turbulent Boundary Layer at Mach Numbers up to Unity," Aeronautical Research Council C.P.No.963,1967.
[188]吴国钏等,“附面层理论”,航空工业出版社,1989.
[189]Peacock,R.,"Boundary-Layer Suction to Eliminate Comer Separation in Cascades of Airfoils," Tech.rep.,Reports and Memoranda,No.3663,Engineering Department,University of Cambridge,1965.
[190]Stratford,B.,"The prevention of separation and flow reversal in the corners of compressor blade cascades," In Aeronautical Journal,pp.249-256,1973.
[191]Culley,D.,Bright,M.,Prahst,P.,and Strazisar,A.,"Active Flow Separation Control of a Stator Vane Using Embedded Injection in a Multistage Compressor Environment," Journal of Turbomachinary,Vol.126,pp.24-34,2003.
[192]Kirtley,K.,Graziosi,P.,Wood,P.,Beacher,B.,and Shin,H.-W.,"Design and Test of an Ultra-Low Solidity Flow-Controlled Compressor Stator," Journal of Turbomachinary,pp.689-698,2005.
[193]Yamaguchi,N.,et al.,"Secondary-Loss Reduction by Forward-Skewing of Axial Compressor Rotor Blading," Proceedings of 1991 Yokohama International Gas Turbine Congress,2:61-68,1991.
[194]蒋洪德,“美国航空发动机和计算流体力学发展情况介绍”,工程热物理能源利用学科,气动热力学发展战略研讨会专题报告汇编,北京,1989.
[195]Breugelmans,F.,"Influence of Incidence Angle on the secondary Flow in Compressor Cascade with Different Dihedral Distribution," ISABE Paper,85-7078,1985.
[196]Shang,E.,et al.,"The Experimental Investigations on the Compressor Cascades with Leaned and Curved Blades," ASME Paper,93-GT-50,1993.
[197]任汝根,周盛,“叶轮机械中的非定常流动”,燃气涡轮试验与研究,第4卷第4期,pp.1-24,1991.
[198]Chen,J.and Ji,L.C.,"Edge Matching--Part Ⅱ:Numerical Investigations,"ASME Paper,GT-2005-68477,2005.
[199]陈江,季路成,“缘线匹配技术在轴流压气机设计中的应用探索”,工程热物理学报,第25卷增刊1,pp.35-38,2004.
[200]Majjigi,R.K.and Gliebe,P.R.,"Development of a Rotor Wake/Vortex Model,Volume 1-Final Technical Report," NASA CR-174849,Contract NAS3-23681,June 1984.
[201]Nathan J.Heidegger,Edward J.Hall,and Robert A.,"Delaney,Follow-on Low Noise Fan Aerodynamic Study:Task 15-Final Report,"NASA/CR-1999-206599,1999.
[202]Poensgen,C.,and Gallus,H.E.,"Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field.Part 2:Unsteady Flow Field Downstream of Stator," Journal of Turbomachinery,Vol.113,pp.180-197,1991.
[203]侯安平,熊劲松,周盛,“轴流压气机尾流撞击效应机理的数值模拟”,北京航空航天大学学报,第31卷第9期,pp.944-948,2005.
[204]Suder,K.L.,"Blockage Development in a.Transonic,Axial Compressor Rotor,"ASME Paper,97-GT-394,1997.
[205]孙晓峰,周盛,“气动声学”,国防工业出版社,1994.
[206]李妍,景小东,孙晓峰,“降低叶轮机转/静干涉噪声的几种技术途径探讨”,工程热物理学会1999年学术会议论文,编号:992053,1999.