透平式气马达叶栅气动设计与数值模拟的研究
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摘要
透平式气马达是气马达的一种,其工作原理是通过喷嘴将空气的流动能直接转变成工作轮的机械能。透平式气马达具有能容比大,输出轴速度高,可改变喷嘴数目来调节功率等优点,多用于高转速、恒负载工况。本文针对摆角铣头主轴驱动用透平式气马达叶栅的气动设计和数值模拟展开研究。
本文首先对透平式气马达叶片流道的气动性能进行了一元理论计算和气动参数的设计,得出了叶片流道的进出口速度及其方向角、各部分损失系数以及叶轮的理论轮周效率、理论流量等参数。
本文对不同进气角(20 ~25 )情况下的平面叶栅进行了造型设计,在此基础上得到了叶片的三维几何模型,为有限元模型的建立打下基础。
本文应用计算流体动力学(CFD)软件Fluent6.3对透平式气马达叶栅的气动性能进行数值模拟,并对透平式气马达叶栅进行变参数研究。通过对不同参数组合下的叶栅数值模拟结果的分析对比,得出叶栅气动性能随不同叶栅几何参数(进气角、叶片数、叶片高度、叶片顶部径向间隙、冲角)变化的规律,进而得出透平式气马达叶栅的最佳参数组合。
本文确定的最佳参数组合叶栅满足摆角铣头工作力矩的设计要求,并存在较大裕度。
通过对高转速、小尺寸透平式气马达叶栅气动性能的数值模拟研究,本文发现了这种叶栅的一些独特之处,并对此做出了分析,为透平式气马达动态效应的研究打下了基础。
Turbo-air-motor is a kind of air-motor, which can directly change compressed air’s energy to impeller’s kinetic energy. It has a big ratio of energy to capacity, outputs a high rotate speed, and its power can be altered by changing the number of nozzles. So it’s always used in high rotate speed and invariable status. Research is done on aerodynamic design and numerical simulation of turbo-air-motor’s cascade which is the drive of bi-rotary milling head’s principal axis.
Firstly, the unitary-theory calculation on the aerodynamic capability of turbo-air-motor’s flowing channels is done, and aerodynamic parameters are designed, and parameters such as velocity and direction vector of inlet and outlet, loss coefficient, impeller’s theoretical efficiency and flux are educed.
The plane cascade of different ingoing angles (20 ~25 ) are designed, and three-dimensional models of the blade are obtained on which finite element models’construction is based.
At last, numerical simulation for aerodynamic capability of turbo-air-motor’s cascade by CFD software FLUENT6.3 is done, and researches are done on different parameters. Through the analysis & comparison on the simulated result, the rule of aerodynamic capability’s transformation depending on different parameters (ingoing angle, blade number, blade length, radial clearance over blade tip, incidence) is discovered, and the optimal parameters combination is found out.
It is found out that under the optimized parameters combination ,the moment of the cascade satisfies the design requirement and has a biggish margin.
Through the numerical simulation researches on the aerodynamic capability of this high rotate speed and small size turbo-air-motor’s cascade, some unique characteristics are discovered. Analyses on the characteristics will establish a solid foundation for researches on turbo-air-motor's dynamic effect.
本文首先对透平式气马达叶片流道的气动性能进行了一元理论计算和气动参数的设计,得出了叶片流道的进出口速度及其方向角、各部分损失系数以及叶轮的理论轮周效率、理论流量等参数。
本文对不同进气角(20 ~25 )情况下的平面叶栅进行了造型设计,在此基础上得到了叶片的三维几何模型,为有限元模型的建立打下基础。
本文应用计算流体动力学(CFD)软件Fluent6.3对透平式气马达叶栅的气动性能进行数值模拟,并对透平式气马达叶栅进行变参数研究。通过对不同参数组合下的叶栅数值模拟结果的分析对比,得出叶栅气动性能随不同叶栅几何参数(进气角、叶片数、叶片高度、叶片顶部径向间隙、冲角)变化的规律,进而得出透平式气马达叶栅的最佳参数组合。
本文确定的最佳参数组合叶栅满足摆角铣头工作力矩的设计要求,并存在较大裕度。
通过对高转速、小尺寸透平式气马达叶栅气动性能的数值模拟研究,本文发现了这种叶栅的一些独特之处,并对此做出了分析,为透平式气马达动态效应的研究打下了基础。
Turbo-air-motor is a kind of air-motor, which can directly change compressed air’s energy to impeller’s kinetic energy. It has a big ratio of energy to capacity, outputs a high rotate speed, and its power can be altered by changing the number of nozzles. So it’s always used in high rotate speed and invariable status. Research is done on aerodynamic design and numerical simulation of turbo-air-motor’s cascade which is the drive of bi-rotary milling head’s principal axis.
Firstly, the unitary-theory calculation on the aerodynamic capability of turbo-air-motor’s flowing channels is done, and aerodynamic parameters are designed, and parameters such as velocity and direction vector of inlet and outlet, loss coefficient, impeller’s theoretical efficiency and flux are educed.
The plane cascade of different ingoing angles (20 ~25 ) are designed, and three-dimensional models of the blade are obtained on which finite element models’construction is based.
At last, numerical simulation for aerodynamic capability of turbo-air-motor’s cascade by CFD software FLUENT6.3 is done, and researches are done on different parameters. Through the analysis & comparison on the simulated result, the rule of aerodynamic capability’s transformation depending on different parameters (ingoing angle, blade number, blade length, radial clearance over blade tip, incidence) is discovered, and the optimal parameters combination is found out.
It is found out that under the optimized parameters combination ,the moment of the cascade satisfies the design requirement and has a biggish margin.
Through the numerical simulation researches on the aerodynamic capability of this high rotate speed and small size turbo-air-motor’s cascade, some unique characteristics are discovered. Analyses on the characteristics will establish a solid foundation for researches on turbo-air-motor's dynamic effect.
引文
1韩荣第,王扬,张文生.现代机械加工新技术.北京:电子工业出版社,2003,4:1~2
2袁哲俊,王先逵.精密和超精密加工技术.北京:机械工业出版社,2003,1:1~2
3常全富. IMTS 2006展会和美国机床企业考察报告.制造技术与机床.2007, (1):15~18
4丁雪生.CIMT2007海外展品精品介绍.世界制造技术与装备市场.2007,(1):48~54
5丁雪生. CIMT2007参观引导和重点展品介绍.制造技术与机床.2007,(3): 14~20
6鲁方霞,邓朝晖.数控机床的发展趋势及国内发展现状.工具技术.2006,40 (3):44~48
7盛伯浩.我国数控机床现状与技术发展策略.现代金属加工.2005,(6):38~45
8中国机床工具协会.2006年机床工具行业十大新闻.现代金属加工.2007, (3):84~86
9袁国良.国产龙门加工中心和数控龙门镗铣床的现状及发展.机械与金属.2006,(5):82~83
10中国机械工业教育协会.液压与气压传动.北京:机械工业出版社,2001:187~188
11王仲奇,秦仁.透平机械原理.北京:机械工业出版社,1981
12舒士甄,朱力等.叶轮机械原理.北京:清华大学出版社,1991,10
13航空发动机设计手册总编委员会.航空发动机设计手册第十册涡轮分册[M].北京:航空工业出版社,2000
14罗兴锜,廖伟丽,林汝长等.流体机械叶轮设计的研究与发展.力学进展.Vol.27,No.3,1997,8
15 Dunham L.J. A Parametric Method of Turbine Blade Profile Design. ASME Paper 74-GT-119,1974
16 Korkianitis.T. A Parametric Method for Direct Gas-turbine-blade Design. AIAA Paper 87-2171,1987
17 Robbins.W.H, Dugan.J.F. Prediction of Off-design Performance of Multistage Compressors[R]. NASA SP-36,1965
18李颖晨,杨佃亮等.透平叶栅三维形状反问题研究.工程热物理学报. 2007,28(1):33~36
19 Pascoa.J.C, Mendes.A.C. Turbine Blade Duty Re-design by Controlling Lean and Sweep Using an Innovative Iterative Inverse Design Method. 2006 ASME 51st Turbo Expo, Barcelona, Spain,2006. New york: American Socie-ty of Mechanical Engineers,2006
20 Bonaiuti.Duccio, Zangeneh.Mehrdad. On the Coupling of Inverse Design and Optimization Techniques for Turbo-machinery Blade Design. 2006 ASME 51st Turbo Expo, Barcelona, Spain,2006 New york: American Society of Mechanical Engineers,2006
21 Eyi S,Lee K.D. Inverse Airfoil Design Using the Navier-Stokes Equations. AIAA 93-0972,1993
22 Malone J.B, Narramore J.C, Sankar L.N. Airfoil Design Method Using the Navier-Stokes Equations. Journal of Aircraft.Vol.28,No.3,March 1991
23王晓鹏.遗传算法及其在气动优化设计中的应用研究.西北工业大学博士学位论文.2000,12
24赖宇阳.叶片气动设计中组合优化方案的算法研究和系统实现.清华大学硕士学位论文.2002
25 D.G.Ainley, G.C.R.Mathieson. A Method of Performance Estimation for Axial Flow Turbines. Aeronautical Researches Council R&M 2974,1957
26中国工程热物理学会,中国科学院工程热物理研究所.纪念吴仲华教授学术报告会论文集.北京:机械工业出版社,1993,1
27 Chung-Hua Wu. A General Through Flow Theory of Fluid Flow with Subso-nic or Supersonic Velocity in Turbomachines of Arbitrary Hub and Casing Shapes. NASA Technical Note 2302,March,1951
28 Chung-Hua Wu. A General Theory of Three-Dimensional Flow in Subsonic or Supersonic Turbomachines of Axial-, Radial-, and Mixed-Flow Types. Lewis Flight Propulsion Laboratory. NASA Technical Note 2604,January, 1952
29袁宁,张振家,顾中华,冯国泰.涡喷发动机压气机三种S2流面计算程序的比较.推进技术.1998,19(1):50~56
30 Jnnoins I.K, Stow P.L. A Quasi-three-dimensional Turbomachinery Blade Design System: Part I-Through Flow Analysis, ASME Paper 84-GT-26,1984
31 Sandel,Wolfgang. An Integrated Design System for Fans. Compressors andTurbines: Part II-Interactive Interface. ASME Paper 84-GT-27,1984
32 Jennoins I.K, Stow P.L. A Quasi-three-dimensional Turbomachinery Blade Design System: Part II-Computerized System, ASME Paper 84-GT-27,1984
33 Johnson.M.S. One-dimensional, Stage-by-stage, Axial Compressor Perform-ance Modle[R]. ASME Paper 91-GT-192,1991
34兰海.斜流式风机叶轮准三元设计与分析.西北工业大学硕士学位论文. 2004
35王松涛,王仲奇.动静叶互相干涉的三维非定常流场数值模拟.上海理工大学学报,Vol.23,No.3,2001
36 Merchant Ali, Haimes Robert. A CAD-based Blade Geometry Model for Turbomachinery Aero Design Systems. 2003 ASME Turbo Expo, Atlanta, GA, United States, Jun, 2003. New York: American Society of Mechanical Engineers,2003
37 Oksuz Ozhan, Akmandor Lbrrahim Sinan. Turbine Blade Shape Aerodyna-mic Using Artificial Intelligence, ASME Turbo Expo 2005 - Gas Turbine Technology: Focus for the Future, Reno-Tahoe, US, 2005. New York: American Society of Mechanical Engineers,2005
38张涵信,沈孟育.计算流体动力学——差分方法原理和应用.北京:国防工业出版社,2003
39王福军.计算流体动力学分析—CFD软件原理与应用.北京:清华大学出版社,2004,9
40 J.D.Anderson. Computational Fluid Dynamics: The Basics with Applications.McGraw-Hill.1995.北京:清华大学出版社,2002
41韩冰冰.三维湍流流场数值计算方法的研究.西北工业大学硕士学位论文.2006,3
42 Lakshminarayana B. An Assessment of Computational Fluid Dynamics Techniques in the Analysis and Design of Turbo-machinery the Freeman Scholar Lecture ASME J. of Fluids Engineering Paper315~352.Vol.113,1991
43张永学,李振林.流体机械数值模拟方法综述.流体机械.2006,(7):34~38
44 Lieblein S., Schwenk F C. , Broderick F L. Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial Flow Compressor Blade Ele-ments. NASA RME53D01,1953
45 Sydney Goldstein. Some Recent Work on Laminar Boundary Layers. Deve-lopments in Mechanics, Volume 2, Part 1, Fluid Mechanics, Pergamon PressLtd. ,1965
46 H.Schlichting. Boundary Layer Theory.8th ed. McGraw Hill, New york,1979
47 S.V. Patankar, Numerical Heat Transfer and Fluid Flow. Hemisphere, Wash-ington, 1980
48 Anon. Turbomachinery Aral Flow Turbine Aerodynamics: Design Methods and CFD Modeling for Turbo Machinery, 2004 ASME Turbo Expo, Vienna, Austria,2004. New York: American Society of Mechanical Engineers,2004
49 Parvizinia Manuchehr, Truckenmuller Frank, Berlich Carsten, Stuer Heinrich. Numerical and Experimental Investigations into the Aerodynamic Performance of a Supersonic Turbine Blade Profile. 2004 ASME Turbo Expo, Vienna, Austria,Jun,2004. New York: American Society of Mechanical Engi-neers,2004
50 Acharya Sumanta, Yang Huitao, Ekkad Srinath V. Numerical Simulation of Film Cooling on the Tip of A Gas Turbine Blade. ASME TURBO EXPO 2002: Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands, Jun, 2002. New York: American Society of Mechanical Engin-eers,2002
51 Gummer V., Goller M., Swoboda M. Numerical Investigation of Endwall Boundary Layer Removal on Highly-loaded Axial Compressor Cascades. ASME Turbo Expo 2005 - Gas Turbine Technology: Focus for the Future, Reno-Tahoe, NV, United States, Jun, 2005. New York: American Society of Mechanical Engineers,2005
52 Park Kicheol. Numerical Study on the Effects of Blade Leading Edge Shape to the Performance of Supersonic Rotor. 2003 ASME Turbo Expo, Atlanta, GA, United States, Jun, 2003. New York: American Society of Mechanical Engineers,2003
53毛君,张利蓉等.基于Fluent的叶轮机械内部流场数值模拟研究.煤矿机械.2006,(8):23~24
54钟芳源.燃气轮机设计基础.北京:机械工业出版社,1987
55К.В.Холщевников等.多级轴流压气机的参数选择和计算.魏仲犹.北京:国防工业出版社,1964
56 A.J. Glassman.涡轮设计与应用.老文雄.北京:国防工业出版社,1982
57陈懋章.粘性流体动力学基础.北京:高等教育出版社,2002:12~13
2袁哲俊,王先逵.精密和超精密加工技术.北京:机械工业出版社,2003,1:1~2
3常全富. IMTS 2006展会和美国机床企业考察报告.制造技术与机床.2007, (1):15~18
4丁雪生.CIMT2007海外展品精品介绍.世界制造技术与装备市场.2007,(1):48~54
5丁雪生. CIMT2007参观引导和重点展品介绍.制造技术与机床.2007,(3): 14~20
6鲁方霞,邓朝晖.数控机床的发展趋势及国内发展现状.工具技术.2006,40 (3):44~48
7盛伯浩.我国数控机床现状与技术发展策略.现代金属加工.2005,(6):38~45
8中国机床工具协会.2006年机床工具行业十大新闻.现代金属加工.2007, (3):84~86
9袁国良.国产龙门加工中心和数控龙门镗铣床的现状及发展.机械与金属.2006,(5):82~83
10中国机械工业教育协会.液压与气压传动.北京:机械工业出版社,2001:187~188
11王仲奇,秦仁.透平机械原理.北京:机械工业出版社,1981
12舒士甄,朱力等.叶轮机械原理.北京:清华大学出版社,1991,10
13航空发动机设计手册总编委员会.航空发动机设计手册第十册涡轮分册[M].北京:航空工业出版社,2000
14罗兴锜,廖伟丽,林汝长等.流体机械叶轮设计的研究与发展.力学进展.Vol.27,No.3,1997,8
15 Dunham L.J. A Parametric Method of Turbine Blade Profile Design. ASME Paper 74-GT-119,1974
16 Korkianitis.T. A Parametric Method for Direct Gas-turbine-blade Design. AIAA Paper 87-2171,1987
17 Robbins.W.H, Dugan.J.F. Prediction of Off-design Performance of Multistage Compressors[R]. NASA SP-36,1965
18李颖晨,杨佃亮等.透平叶栅三维形状反问题研究.工程热物理学报. 2007,28(1):33~36
19 Pascoa.J.C, Mendes.A.C. Turbine Blade Duty Re-design by Controlling Lean and Sweep Using an Innovative Iterative Inverse Design Method. 2006 ASME 51st Turbo Expo, Barcelona, Spain,2006. New york: American Socie-ty of Mechanical Engineers,2006
20 Bonaiuti.Duccio, Zangeneh.Mehrdad. On the Coupling of Inverse Design and Optimization Techniques for Turbo-machinery Blade Design. 2006 ASME 51st Turbo Expo, Barcelona, Spain,2006 New york: American Society of Mechanical Engineers,2006
21 Eyi S,Lee K.D. Inverse Airfoil Design Using the Navier-Stokes Equations. AIAA 93-0972,1993
22 Malone J.B, Narramore J.C, Sankar L.N. Airfoil Design Method Using the Navier-Stokes Equations. Journal of Aircraft.Vol.28,No.3,March 1991
23王晓鹏.遗传算法及其在气动优化设计中的应用研究.西北工业大学博士学位论文.2000,12
24赖宇阳.叶片气动设计中组合优化方案的算法研究和系统实现.清华大学硕士学位论文.2002
25 D.G.Ainley, G.C.R.Mathieson. A Method of Performance Estimation for Axial Flow Turbines. Aeronautical Researches Council R&M 2974,1957
26中国工程热物理学会,中国科学院工程热物理研究所.纪念吴仲华教授学术报告会论文集.北京:机械工业出版社,1993,1
27 Chung-Hua Wu. A General Through Flow Theory of Fluid Flow with Subso-nic or Supersonic Velocity in Turbomachines of Arbitrary Hub and Casing Shapes. NASA Technical Note 2302,March,1951
28 Chung-Hua Wu. A General Theory of Three-Dimensional Flow in Subsonic or Supersonic Turbomachines of Axial-, Radial-, and Mixed-Flow Types. Lewis Flight Propulsion Laboratory. NASA Technical Note 2604,January, 1952
29袁宁,张振家,顾中华,冯国泰.涡喷发动机压气机三种S2流面计算程序的比较.推进技术.1998,19(1):50~56
30 Jnnoins I.K, Stow P.L. A Quasi-three-dimensional Turbomachinery Blade Design System: Part I-Through Flow Analysis, ASME Paper 84-GT-26,1984
31 Sandel,Wolfgang. An Integrated Design System for Fans. Compressors andTurbines: Part II-Interactive Interface. ASME Paper 84-GT-27,1984
32 Jennoins I.K, Stow P.L. A Quasi-three-dimensional Turbomachinery Blade Design System: Part II-Computerized System, ASME Paper 84-GT-27,1984
33 Johnson.M.S. One-dimensional, Stage-by-stage, Axial Compressor Perform-ance Modle[R]. ASME Paper 91-GT-192,1991
34兰海.斜流式风机叶轮准三元设计与分析.西北工业大学硕士学位论文. 2004
35王松涛,王仲奇.动静叶互相干涉的三维非定常流场数值模拟.上海理工大学学报,Vol.23,No.3,2001
36 Merchant Ali, Haimes Robert. A CAD-based Blade Geometry Model for Turbomachinery Aero Design Systems. 2003 ASME Turbo Expo, Atlanta, GA, United States, Jun, 2003. New York: American Society of Mechanical Engineers,2003
37 Oksuz Ozhan, Akmandor Lbrrahim Sinan. Turbine Blade Shape Aerodyna-mic Using Artificial Intelligence, ASME Turbo Expo 2005 - Gas Turbine Technology: Focus for the Future, Reno-Tahoe, US, 2005. New York: American Society of Mechanical Engineers,2005
38张涵信,沈孟育.计算流体动力学——差分方法原理和应用.北京:国防工业出版社,2003
39王福军.计算流体动力学分析—CFD软件原理与应用.北京:清华大学出版社,2004,9
40 J.D.Anderson. Computational Fluid Dynamics: The Basics with Applications.McGraw-Hill.1995.北京:清华大学出版社,2002
41韩冰冰.三维湍流流场数值计算方法的研究.西北工业大学硕士学位论文.2006,3
42 Lakshminarayana B. An Assessment of Computational Fluid Dynamics Techniques in the Analysis and Design of Turbo-machinery the Freeman Scholar Lecture ASME J. of Fluids Engineering Paper315~352.Vol.113,1991
43张永学,李振林.流体机械数值模拟方法综述.流体机械.2006,(7):34~38
44 Lieblein S., Schwenk F C. , Broderick F L. Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial Flow Compressor Blade Ele-ments. NASA RME53D01,1953
45 Sydney Goldstein. Some Recent Work on Laminar Boundary Layers. Deve-lopments in Mechanics, Volume 2, Part 1, Fluid Mechanics, Pergamon PressLtd. ,1965
46 H.Schlichting. Boundary Layer Theory.8th ed. McGraw Hill, New york,1979
47 S.V. Patankar, Numerical Heat Transfer and Fluid Flow. Hemisphere, Wash-ington, 1980
48 Anon. Turbomachinery Aral Flow Turbine Aerodynamics: Design Methods and CFD Modeling for Turbo Machinery, 2004 ASME Turbo Expo, Vienna, Austria,2004. New York: American Society of Mechanical Engineers,2004
49 Parvizinia Manuchehr, Truckenmuller Frank, Berlich Carsten, Stuer Heinrich. Numerical and Experimental Investigations into the Aerodynamic Performance of a Supersonic Turbine Blade Profile. 2004 ASME Turbo Expo, Vienna, Austria,Jun,2004. New York: American Society of Mechanical Engi-neers,2004
50 Acharya Sumanta, Yang Huitao, Ekkad Srinath V. Numerical Simulation of Film Cooling on the Tip of A Gas Turbine Blade. ASME TURBO EXPO 2002: Heat Transfer, Manufacturing Materials and Metallurgy, Amsterdam, Netherlands, Jun, 2002. New York: American Society of Mechanical Engin-eers,2002
51 Gummer V., Goller M., Swoboda M. Numerical Investigation of Endwall Boundary Layer Removal on Highly-loaded Axial Compressor Cascades. ASME Turbo Expo 2005 - Gas Turbine Technology: Focus for the Future, Reno-Tahoe, NV, United States, Jun, 2005. New York: American Society of Mechanical Engineers,2005
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