基于Φ函数的等熵膨胀过程数学模型
Mathematical model of isentropic expansion process based on Φ function
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摘要: 为了解决航空发动机总体性能计算中,主要的等熵膨胀过程数学模型中存在理想状态值的计算,使计算结果与实际值相比产生一定误差的问题.从过程效率定义式入手,推导出基于Φ函数的等熵膨胀过程数学模型.与基于熵的等熵膨胀过程数学模型以及带理想状态值计算的等熵膨胀过程数学模型的计算结果进行比较与分析之后,得出结论是:①基于Φ函数的等熵膨胀过程数学模型的应用可使计算精度得到提高;②基于Φ函数的等熵膨胀过程数学模型的应用较为简便,可以提高编程效率和计算效率.Abstract: Recently,the calculation of ideal value was involved in the main mathematical model of isentropic expansion process,so compared with the actual value,the results had a certain error.Deriveing the mathematical model of isentropic expansion process based on Φ function by using the definition type of process efficiency.Compared with the results from the mathematical model of isentropic expansion process based on entropy and the mathematical model of isentropic expansion process based on ideal value,concluded that:(1) accuracy can be improved when applying the mathematical model of isentropic expansion process based on Φ function;(2) application of the mathematical model of isentropic expansion process based on Φ function is simple,and can greatly improve the programming efficiency and computational efficiency.
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[1] 曹源,金世龙,孟光.航空发动机系统级仿真研究的回顾与展望[J].航空动力学报,2004,19(4):562-571. CAO Yuan,JIN Xianlong,MENG Guang.Recent development and prospects of system-level modeling of aircraft engine[J].Journal of Aerospace Power,2005,19(4):562-571.(in Chinese) [2] Ramohalli K N R.Isothermal combustion for improved efficiencies. AIAA-1987-1999,1987. [3] Sirignano W,Delplanque A J P,Liu F.Selected challenges in jet and rocket engine combustion research. AIAA-1997-2701,1997. [4] Liu F,Sirignano W A.Turbojet and turbofan engine performance increases through turbine burners. AIAA-2000-0741,2000. [5] Liew K H,Urip E,Yang S L,et al.A complete parametric cycle analysis of a turbofan with interstage turbine burner. AIAA-2003-685,2000. [6] Chen G,Hoffman M A,Davis R L.Improvements in gas-turbine performance through the use of multiple turbine inter-stage burners. AIAA-2004-374,2004. [7] Chiu Y M.A performance study of a super-cruise engine with isothermal combustion inside the turbine. Blacksburg,Virginia,USA:Virginia Polytechnic Institute and State University,2004. [8] Liew K H.Aerothermodynamic cycle analysis of a dual-spool,separate-exhaust turbofan engine with an interstage turbine. Houghton,Michigan,USA:Michigan Technological University,2006. [9] 孙鹏,任静,蒋洪德.基于顺序算法的灵活燃料燃气轮机气动热力性能分析[J].工程热物理学报,2011,32(1):29-32. SUN Peng,REN Jing,JIANG Hongde.Sequential algorithm based flexible-fuel gas turbine thermodynamic analysis[J].Journal of Engineering Thermophysics,2011,32(1):29-32.(in Chinese) [10] 吴虎,廉筱纯,沈韶瀛.某型加力涡扇发动机变几何扩稳优化模拟[J].航空动力学报,2001,16(4):390-393. WU Hu,LIAN Xiaochun,SHEN Shaoying.A study of enlarging surge margin and optimization of variable geometry for afterburning turbofan engines[J].Journal of Aerospace Power,2001,16(4):390-393.(in Chinese) [11] 周文祥,黄金泉.涡扇发动机高空起动模型研究[J].航空动力学报,2007,22(8):1384-1390. ZHOU Wenxiang,HUANG Jinquan.Research on the startup model of turbofan engine at high altitude[J].Journal of Aerospace Power,2007,22(8):1384-1390.(in Chinese) [12] 于龙江,朴英.一种简化算法的航空发动机全状态数学模型[J].航空动力学报,2008,23(3):510-515. YU Longjian,PIAO Ying.Full range modeling of aero engine systems based on a simplified algorithm[J].Journal of Aerospace Power,2008,23(3):510-515.(in Chinese) [13] 黄国平,温泉,李博,等.微型涡喷发动机顶层设计研究[J].航空动力学报,2003,18(6):832-838. HUANG Guoping,WEN Quan,LI Bo,et al.Top level design of micro turbine jet engine[J].Journal of Aerospace Power,2003,18(6):832-838.(in Chinese) [14] 廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005. [15] 骆广琦,桑增产,王如根,等.航空燃气涡轮发动机数值仿真[M].北京:国防工业出版社,2007. [16] 程本林.提高涡轮发动机性能的新概念方法--涡轮通道内补燃循环性能研究. 南京:南京航空航天大学,2011. CHENG Benlin.A new concept of turbojet and turbofan engine performance increases through turbine inter-blade burner. Nanjing:Nanjing University of Aeronautics and Astronautics,2011.(in Chinese) [17] 彭泽琰,刘刚.航空燃气轮机原理:上册[M].北京:国防工业出版社,2000. [18] Walsh P P,Fletcher P.Gas turbine performance [M].Blackwell:Science Ltd.,1998. [19] 沈维道,蒋智敏,童钧耕.工程热力学[M].北京:高等教育出版社,2001. [20] 周勇,赵晓路,徐建中.WP6涡轮部件设计状态及实验状态的数值模拟[J].工程热物理学报,2005,26(5):767-769. ZHOU Yong,CHAO Xiaolu,XU Jianzhong.The numerical simulation of the design condition and test condition in WP6 turbine[J].Journal of Engineering Thermophysics,2005,26(5):767-769.(in Chinese) [21] 方德昌.世界航空发动机手册[M].北京:航空工业出版社,1996. [22] 孙大伟,乔渭阳,许开富,等.低雷诺数条件下涡轮性能的计算研究[J].航空动力学报,2008,23(7):1253-1259. SUN Dawei,QIAO Weiyang,XU Kaifu,et al.Study on turbine performance at low Reynolds number [J].Journal of Aerospace Power,2008,23(7):1253-1259.(in Chinese) [23] Whitney W J,Schum H J,Behning F P.Cold-air investi-gation of a turbine for high-temperature-engine applicationⅣ:two-stage turbine performance. NASA ND -3751,1972. [24] 刘思永,王屏,方祥军,等.无导叶对转涡轮新技术在高推比航空发动机中的运用[J].航空动力学报,2002,17(4):495-499. LIU Siyong,WANG Ping,FANG Xiangjun,et al.Application of contra-rotating turbine without guide vanes to high thrust loading aeroengine[J].Journal of Aerospace Power,2002,17(4):495-499.(in Chinese)
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