Turbine characteristics conversion method of aeroengine
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摘要: 针对以落压比为横坐标,流量与效率为纵坐标,并按不同等转速线区分所表示的涡轮特性在涡轮处于临界状态时换算流量几乎保持不变,使得在航空发动机数学模型中应用该形式涡轮特性通过插值求解共同工作点时存在计算效率降低的不足,根据相似理论及等熵条件下涡轮膨胀功与落压比对应关系,推导了涡轮落压比、涡轮效率与涡轮当量功的关系,并结合抛物线插值方法给出了向以转速为横坐标,涡轮当量功与效率为纵坐标,并按不同等流量线区分所表示的涡轮特性转换方法。实例转换计算表明:采用所提出的转换计算方法,可有效解决以往涡轮特性插值流量基本不变的局限,并且两种格式的涡轮特性转换相对误差小于0.65%,满足工程要求。Abstract: For the turbine characteristics expressed by taking the nozzle pressure ratio as the abscissa, the corrected mass flow and efficiency as the ordinate, and differentiated by different equal rotation speed lines, when the turbine works at critical state, the corrected mass flow of this form of turbine characteristics almost remain unchanged, and had the disadvantage of reducing computational efficiency in solving common working point when it was used in aeroengine mathematical model by interpolation of turbine characteristics. According to similarity theory and the corresponding relationship between turbine expansion work and nozzle pressure ratio under isentropic conditions, the calculation formula between turbine nozzle pressure ratio, turbine efficiency and turbine equivalent work was derived; combined with the parabolic interpolation method, a method for transforming turbine characteristics expressed in the above form was presented, the converted turbine characteristics were expressed by the equal rotation speed as the abscissa, the turbine equivalent work and efficiency as the ordinate, and differentiated by different equal corrected mass flow lines. The conversion calculation shows that with the proposed conversion calculation method, the relative error is less than 0.65% between two forms of turbine characteristics, which meets the engineering requirements, and can effectively avoid the disadvantage of previous turbine characteristics.
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[1] 王波,唐海龙,仲如浩,等.可视化航空发动机性能 仿真模型[J].航空动力学报,2009,24(3):602-607. WANG Bo,TANG Hailong,ZHONG Ruhao,et al.Visual simulation model of aeroengine performance[J].Journal of Aerospace Power,2009,24(3):602-607.(in Chinese) [2] 胡伟波,程邦勤,陈志敏,等.面向对象的通用航空发动机建模技术研究[J].航空动力学报,2015,30(10):2539-2545. HU Weibo,CHENG Bangqin,CHEN Zhimin,et al.Research on object-oriented general aeroengine modeling technology[J].Journal of Aerospace Power,2015,30(10):2539-2545.(in Chinese) [3] 胡宇,张世英,罗雷,等.基于自适应容积卡尔曼滤波方法的涡扇发动机气路部件故障诊断[J].航空动力学报,2016,31(5):243-250. HU Yu,ZHANG Shiying,LUO Lei,et al.Fault diagnosis of pneumatic components of turbofan engine based on adaptive volumetric Kalman filter method[J].Journal of Aerospace Power,2016,31(5):243-250.(in Chinese) [4] 贾惟,赵福佳,王伟.基于数学模型的航空发动机控制系统安全性评估方法[J].科学技术与工程,2018,18(31):91-98. JIA Wei,ZHAO Fujia,WANG Wei.Safety evaluation method of aeroengine control system based on mathematical model[J].Science and Technology and Engineering,2018,18(31):91-98.(in Chinese) [5] 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. [6] 楚武利,刘前智,胡春波.航空叶片机原理[M].西安:西北工业大学出版社,2009. [7] 《航空发动机设计手册》总编委会.航空发动机设计手册:第10册 涡轮[M].北京:航空工业出版社,2001. [8] 陈玉春,徐思远,杨云铠,等.改善航空发动机特性计算收敛性的方法[J].航空动力学报,2008,23(12):2242-2248. CHEN Yuchun,XU Siyuan,YANG Yunkai,et al.A method for improving the convergence of aeroengine characterization[J].Journal of Aerospace Power,2008,23(12):2242-2248.(in Chinese) [9] 陈玉春,徐思远,屠秋野,等.求解航空发动机非线性方程组的变步长牛顿法[J].航空计算技术,2009,39(1):39-41. CHEN Yuchun,XU Siyuan,TU Qiuye,et al.Variable step size newton method for solving nonlinear equations of aeroengine[J].Aviation Computing Technology,2009,39(1):39-41.(in Chinese) [10] 黄旭,王占学,张晓博.基于Broyden改进算法的航空发动机性能模拟研究[J].科学技术与工程,2012,12(21):5231-5234. HUANG Xu,WANG Zhanxue,ZHANG Xiaobo.Simulation of aeroengine performance based on Broyden improved algorithm[J].Science Technology and Engineering,2012,12(21):5231-5234.(in Chinese) [11] 苏三买,陈永琴.航空发动机数学模型中方程解法与局限性分析[J].航空计算技术,2006,36(6):13-15. SU Sanmai,CHEN Yongqin.Solution and limitation analysis of equations in aeroengine mathematical model[J].Aviation Computing Technology,2006,36(6):13-15.(in Chinese) [12] KURZKE J.How to get component maps for aircraft gas turbine performance calculations[R].ASME Paper 96-GT-164,1996. [13] KURZKE J.Propulsion and power:An exploration of gas turbine performance modeling[M].Berlin:Springer Verlag,2018. [14] SHAUN R G.Development of a dynamic modeling and control system design methodology for gas turbines[D].Ottawa:Carleton University Ottawa,2007. [15] BYERLEY A R,ROUSER K P,ODOWD D O.Exploring GasTurb 12 for supplementary use on an introductory propulsion design project[R].ASME Paper GT2017-63465,2017. [16] SELLERS J F,DANIELE C J.DYNGEN:a program for calculating steady-state and transient performance of turbojet and turbofan engines[R].NASA-TND-7901,1975. [17] DANIELE C J,KROSEL S M,SZUCH J R.DIGTEM-digital computer program for generating dynamic turbofan engine models[R].NASA TM-83446,1983. [18] 童凯生.航空涡轮发动机性能变比热计算方法[M].北京:航空工业出版社,1991. [19] 陈伟博.压气机和涡轮特性的转换、修正及扩展研究[D].西安:西北工业大学,2015. CHEN Weibo.Study on the transformation, modification and expansion of compressor and turbine characteristics[D].Xian:Northwestern Polytechnical University,2015.(in Chinese)
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