高涵道比涡扇发动机结构与力学性能定量评估
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摘要
针对高涵道比涡扇发动机结构设计需求,提出转子系统、承力系统和整机的结构效率评估参数,建立了结构设计参数与力学特征参数之间的联系。典型发动机评估结果表明:受大尺寸风扇限制,高涵道比涡扇发动机低压转子系统的平均应力系数在0.2~0.3之间,低于其他类型的航空燃气涡轮发动机。在工作转速范围内,低压转子不可避免地存在弯曲型临界转速,须将转子连接结构设计在低应变能区域。机动飞行中,整机的转静间隙值变化范围为[-1.4,1.0]mm,低压涡轮是间隙控制的重点位置。
The structural efficiency parameters for the rotor system,supporting system and whole engine were put forward respectively according to the structure design requirements of the high bypass ratio turbofan engine,and the relations between the structural design parameters and the mechanics property parameters were established.The evaluation results for one typical engine exhibited that the average stress coefficients for the low pressure rotor of the high bypass ratio turbofan engine were between 0.2and 0.3,lower than those of the other types of aero gas turbo engines because of the particularly large size of the fan.There were several unavoidable critical speeds with bending modes within the operation speed range,therefore the location of the joint structures of the rotor should be designed into the low stain energy zone.During maneuvering,the interval for the clearance between the stator and the rotor was[-1.4,1.0]mm for the whole engine,and the low pressure tur-bine was the key position for the clearance control.
The structural efficiency parameters for the rotor system,supporting system and whole engine were put forward respectively according to the structure design requirements of the high bypass ratio turbofan engine,and the relations between the structural design parameters and the mechanics property parameters were established.The evaluation results for one typical engine exhibited that the average stress coefficients for the low pressure rotor of the high bypass ratio turbofan engine were between 0.2and 0.3,lower than those of the other types of aero gas turbo engines because of the particularly large size of the fan.There were several unavoidable critical speeds with bending modes within the operation speed range,therefore the location of the joint structures of the rotor should be designed into the low stain energy zone.During maneuvering,the interval for the clearance between the stator and the rotor was[-1.4,1.0]mm for the whole engine,and the low pressure tur-bine was the key position for the clearance control.
引文
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[16]CHRISTEN J L,ICHCHOU M,TROCLET B,et al.Global sensitivity analysis of analytical vibroacoustic transmission models[J].Journal of Sound and Vibration,2016,368:121-134.
[17]SONG Xiaomeng,ZHANG Jianyun,ZHAN Chesheng,et al.Global sensitivity analysis in hydrological modeling:review of concepts,methods,theoretical framework,and applications[J].Journal of Hydrology,2015,523:739-757.
[18]唐海龙,朱之丽,罗安阳,等.以已有核心机为基础进行发动机系列发展的初步研究[J].航空动力学报,2004,19(5):636-639.TANG Hailong,ZHU Zhili,LUO Anyang,et al.Preliminary analysis of developing series of engines based on an existing core engine[J].Journal of Aerospace Power,2004,19(5):636-639.(in Chinese)
[19]SANDS J S,KARL A H,MAVRIS D N.Modeling and simulation of common core gas turbine engine variant applications[R].ASME Paper GT2016-56394,2016.
[20]洪杰,马艳红,张大义.航空燃气轮机总体结构设计与动力学分析[M].北京:北京航空航天大学出版社,2014.
[21]TILLMAN D,GAGE R,BARRETT R.Gas turbine engine turbine blade tip active clearance control system and method:US9266618[P].2016-02-23.
[2]吕文林,陈俊粤,田德义.航空涡喷、涡扇发动机结构设计准则[R].北京:中国航空工业总公司发动机系统工程局,2000.
[3]WILSON D G,KORAKIANITIS T.The design of high-efficiency turbomachinery and gas turbines[M].Cambridge:MIT Press,2014.
[4]NORRIS F D,HICKMAN W A.Comparison of the structural efficiency of panels having straight-web and curved-web y-section stiffeners[R].NACA Technical Note No.1787,1949.
[5]STORACE A F.Turbine engine structural efficiency determination[R].AIAA 89-2571,1989.
[6]张大义,马艳红,梁智超,等.整机结构设计的评估方法:结构效率[J].航空动力学报,2010,25(10):2170-2176.ZHANG Dayi,MA Yanhong,LIANG Zhichao,et al.Evaluation method on whole engine structural design-structural efficiency[J].Journal of Aerospace Power,2010,25(10):2170-2176.(in Chinese)
[7]张大义,洪杰,梁智超.航空发动机转子系统的结构效率评估方法研究[C]∥全国第九届转子动力学学术讨论会论文集.贵阳:中国振动工程学会转子动力学专业分会,2010:54-57.
[8]马艳红,陈璐璐,张大义,等.航空发动机转子系统结构效率评估参数及计算方法[J].航空动力学报,2013,28(7):1598-1606.MA Yanhong,CHEN Lulu,ZHANG Dayi,et al.Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine[J].Journal of Aerospace Power,2013,28(7):1598-1606.(in Chinese)
[9]张大义,洪杰,马艳红,等.高结构效率的斜流压气机结构设计[J].航空动力学报,2013,28(4):866-871.ZHANG Dayi,HONG Jie,MA Yanhong,et al.Novel structural design of mixed-flow compressor with high structural efficiency[J].Journal of Aerospace Power,2013,28(4):866-871.(in Chinese)
[10]马艳红,曹冲,李鑫,等.航空发动机承力系统结构效率评估方法[J].航空动力学报,2016,31(2):274-281.MA Yanhong,CAO Chong,LI Xin,et al.Assessment method of structural efficiency on bearing system in aeroengine[J].Journal of Aerospace Power,2016,31(2):274-281.(in Chinese)
[11]于平超,马艳红,王存,等.航空发动机整机结构效率评估参数与计算方法[J].航空动力学报,2016,31(7):1744-1753.YU Pingchao,MA Yanhong,WANG Cun,et al.Evaluation parameters and calculation methods of structural efficiency for whole aero-engine[J].Journal of Aerospace Power,2016,31(7):1744-1753.(in Chinese)
[12]TURAN O.An exergy way to quantify sustainability metrics for a high bypass turbofan engine[J].Energy,2015,86:722-736.
[13]张大义,刘烨辉,洪杰,等.航空发动机整机动力学模型建立与振动特性分析[J].推进技术,2015,36(5):768-773.ZHANG Dayi,LIU Yehui,HONG Jie,et al.Investigation on dynamical modeling and vibration characteristics for aero engine[J].Journal of Propulsion Technology,2015,36(5):768-773.(in Chinese)
[14]赵文涛,陈果,李琼,等.航空发动机机匣支承动刚度有限元计算及验证[J].航空计算技术,2011,41(5):34-38.ZHAO Wentao,CHEN Guo,LI Qiong,et al.Finite element modeling and experiment verification of dynamic stiffness of casing bearing in aircraft engine[J].Aeronautical Computing Technique,2011,41(5):34-38.(in Chinese)
[15]汤茂森,荆建平,周惠文,等.重型燃气轮机支撑结构动刚度计算分析方法[J].噪声与振动控制,2006,36(3):38-41.TANG Maosen,JING Jianping,ZHOU Huiwen,et al.Calculation and test of dynamic stiffness of gas turbine supports[J].Noise and Vibration Control,2006,36(3):38-41.(in Chinese)
[16]CHRISTEN J L,ICHCHOU M,TROCLET B,et al.Global sensitivity analysis of analytical vibroacoustic transmission models[J].Journal of Sound and Vibration,2016,368:121-134.
[17]SONG Xiaomeng,ZHANG Jianyun,ZHAN Chesheng,et al.Global sensitivity analysis in hydrological modeling:review of concepts,methods,theoretical framework,and applications[J].Journal of Hydrology,2015,523:739-757.
[18]唐海龙,朱之丽,罗安阳,等.以已有核心机为基础进行发动机系列发展的初步研究[J].航空动力学报,2004,19(5):636-639.TANG Hailong,ZHU Zhili,LUO Anyang,et al.Preliminary analysis of developing series of engines based on an existing core engine[J].Journal of Aerospace Power,2004,19(5):636-639.(in Chinese)
[19]SANDS J S,KARL A H,MAVRIS D N.Modeling and simulation of common core gas turbine engine variant applications[R].ASME Paper GT2016-56394,2016.
[20]洪杰,马艳红,张大义.航空燃气轮机总体结构设计与动力学分析[M].北京:北京航空航天大学出版社,2014.
[21]TILLMAN D,GAGE R,BARRETT R.Gas turbine engine turbine blade tip active clearance control system and method:US9266618[P].2016-02-23.