大涵道比发动机多级低压涡轮试验技术研究
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摘要
涡轮试验是检验涡轮性能是否达标的重要过程。基于某全尺寸涡轮试验器、现有涡轮试验方法和试验规范,通过对试验器进行适当设备改造,结合试验涡轮的进出口压力、温度、流量和功率等参数的耦合关系,形成针对大涵道比涡扇发动机多级低压涡轮性能试验状态评估、过程控制和数据分析方法,并通过国内某型大涵道比涡扇发动机多级低压涡轮试验进行验证。试验结果表明:基于试验参数耦合关系的试验状态评估、过程控制和数据分析方法有效,填补了国内大涵道比涡扇发动机多级低压涡轮试验方法和试验数据的空白,同时,该型发动机低压涡轮的效率达到设计指标,处于国内先进水平,所述方法可为国内后续多级低压涡轮试验提供参考。
Turbine test is a significant process to test whether turbine characteristics is up to standard. Based on a full-scale turbine tester,the existing turbine test methods and test specifications and combined with the coupling relations of inlet and outlet pressure,temperature,flow rate and power of the test turbine,a method of high bypass ratio turbofan characteristic test evaluation,process control and test data analysis for multistage low pressure turbine was developed through the appropriate equipment modification of the tester. A domestic high bypass ratio turbofan with multistage low pressure turbine test was verified. The test results show that the characteristic test evaluation,process control and data analysis based on the coupling relations of test parameters are effective,and fill the blank of test method and test data for domestic high bypass ratio turbofan with multistage low pressure turbine. At the same time,the efficiency of the low pressure turbine of this type of engine reaches the design target and is advanced in China. The method can be used as a reference for the domestic subsequent multistage low pressure turbine test.
Turbine test is a significant process to test whether turbine characteristics is up to standard. Based on a full-scale turbine tester,the existing turbine test methods and test specifications and combined with the coupling relations of inlet and outlet pressure,temperature,flow rate and power of the test turbine,a method of high bypass ratio turbofan characteristic test evaluation,process control and test data analysis for multistage low pressure turbine was developed through the appropriate equipment modification of the tester. A domestic high bypass ratio turbofan with multistage low pressure turbine test was verified. The test results show that the characteristic test evaluation,process control and data analysis based on the coupling relations of test parameters are effective,and fill the blank of test method and test data for domestic high bypass ratio turbofan with multistage low pressure turbine. At the same time,the efficiency of the low pressure turbine of this type of engine reaches the design target and is advanced in China. The method can be used as a reference for the domestic subsequent multistage low pressure turbine test.
引文
[1]沈锡钢.大涵道比涡扇发动机总体性能与循环参数设计[J].航空科学技术,2011(4):4-7.SHEN Xigang. Design of performance and cycle parameters of high bypass ratio turbofan[J].Aeronautical Science&Technology,2011(4):4-7.(in Chinese)
[2]方昌德.大涵道比涡扇发动机关键技术[J].国际航空,2008(1):38-40.FANG Changde. Key technologies for high by-pass turbofan engines[J]. International Aviation,2008(1):38-40.(in Chinese)
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[5]崔涛.大型涡扇发动机低压涡轮的气动设计及相关问题研究[D].哈尔滨:哈尔滨工业大学,2013.CUI Tao. Aerodynamic design and related problems research of low pressure turbine of a large gas turbofan engine[D].Harbin:Harbin Institute of Technology,2013.(in Chinese)
[6]陈云,王雷,王刚.大涵道比发动机多级低压涡轮气动设计[J].航空发动机,2007,39(4):51-55.CHEN Yun,WANG Lei,WANG Gang.Aerodynamic design of multistage low pressure turbine for high bypass ratio aeroengine[J]. Aeroengine,2007,39(4):51-55.(in Chinese)
[7]卫刚,王永明,王松涛,等.高性能低压涡轮与试验[J].燃气涡轮试验与研究,2013,26(2):6-11.WEI Gang,WANG Yongming,WANG Songtao,et al. Design and experiment of a high performance low-pressure turbine[J]. Gas Turbine Experiment and Research,2013,23(2):6-11.(in Chinese)
[8] Binder A,Schroeder T H,Hourmouziadis J. Turbulence measurements in a multistage low-pressure turbine[R]. A 88-54207.
[9] Hodson H P,Huntsman I.An Investigation of boundary layer development in a multistage LP turbine[R].ASME 93-GT-310.
[10]盖尔哈特·默克尔.燃气轮机性能试验用的康氏水力测功器[J].热能动力工程,2005,20(6):650-654.Gerhard Merkle. Kahn hydraulic dynamometers for performance testing of gas turbines[J]. Journal of Engineering for Thermal Energy and Power,2005,20(6):650-654.(in Chinese)
[11]刘志刚,曾军,赵旺东,等.全尺寸对转涡轮若干关键试验技术的应用验证[J].燃气涡轮试验与研究,2017,30(1):1-6.LIU Zhigang,ZENG Jun,ZHAO Wangdong,et al. Investigation and verification of key technologies in full scale contrarotating turbine experiment[J]. Gas Turbine Experiment and Research,2017,30(1):1-6.(in Chinese)
[12]张健新,武卉,付鑫.水力测功器在燃气轮机性能试验中的应用[M]//中国航空学会.第六届中国航空学会青年科技论坛文集.北京:航空工业出版社,2014,1042-1047.ZHANG Jianxin,WU Hui,FU xin. Application of hydraulic dynamometer for performance testing of gasturbine[C]//the proceedings of the sixth Chinese Society of Aeronautice and Astronautics Science of Technique Youth forum,Aviation Industry Book Concern,2014:1042-1047.(in Chinese)
[13]周世英,段连丰,郭呈义.HB 7081-1994轴流涡轮气动性能试验[S].北京:中国航空工业总公司,1994:14-22.ZHOU Shiying,DUAN Lianfeng,GUO Chengyi.HB7081-1994 axial turbine aerodynamic performance test[S].Beijing:China Aviation Industry Corporation,1994:14-22.(in Chinese)
[14]田夫.叶轮机机械气动性能的实验研究方法[M].北京:清华大学出版社,2013:89-90.TIAN Fu.Experimental research method of aerodynamic performance of Turbomachinery[M]. Beijing:Tsinghua University Press,2013:89-90.(in Chinese)
[15]张清,郝勇,张大义,等.大涵道比发动机低压涡轮间隙分析与设计[J].航空发动机,2014,40(2):56-60.ZHANG Qing,HAO Yong,ZHANG Dayi,et al.Anasis and design of low pressure turbine tip clearance for high bypasss ratio engine[J].Aeroengine,2014,40(2):56-60.(in Chinese)
[16]谭洪川,乔渭阳,赵磊,等.低压涡轮气动/声学一体化设计—总体参数优化[J].推进技术,2012,33(4):573-578.TAN Hongchuan,QIAO Weiyang,ZHAO lei,et al. Aerodynamics/acoustics integration design method of low pressure turbine—overall parameters optimization[J]. Journal of Propulsion Technology,2012,33(4):573-578.(in Chinese)
[17]刘勋.低雷诺数低压涡轮气动性能分析[D].哈尔滨:哈尔滨工业大学,2008.LIU Xun. Aerodynamic performance analysis of low pressure turbine at low Reynolds Numbers[D]. Harbin:Harbin Institute of Technology,2008.(in Chinese)
[2]方昌德.大涵道比涡扇发动机关键技术[J].国际航空,2008(1):38-40.FANG Changde. Key technologies for high by-pass turbofan engines[J]. International Aviation,2008(1):38-40.(in Chinese)
[3]张生,李长晖,任文成,等.部件性能变化对大涵道比发动机台架性能的影响[J].航空发动机,2007,36(4):22-25.ZHANG Sheng,LI Changhui,REN Wencheng,et al. Effect of component performance variation on the performance of high bypass ratio engine on testbed[J]. Aeroengine,2010,36(4):22-25.(in Chinese)
[4] Vázquez R,Cadrecha D,Torre D. High stage loading low pressure turbines:a new proposal for an efficency chart[R].ASME 2003-GT-8374.
[5]崔涛.大型涡扇发动机低压涡轮的气动设计及相关问题研究[D].哈尔滨:哈尔滨工业大学,2013.CUI Tao. Aerodynamic design and related problems research of low pressure turbine of a large gas turbofan engine[D].Harbin:Harbin Institute of Technology,2013.(in Chinese)
[6]陈云,王雷,王刚.大涵道比发动机多级低压涡轮气动设计[J].航空发动机,2007,39(4):51-55.CHEN Yun,WANG Lei,WANG Gang.Aerodynamic design of multistage low pressure turbine for high bypass ratio aeroengine[J]. Aeroengine,2007,39(4):51-55.(in Chinese)
[7]卫刚,王永明,王松涛,等.高性能低压涡轮与试验[J].燃气涡轮试验与研究,2013,26(2):6-11.WEI Gang,WANG Yongming,WANG Songtao,et al. Design and experiment of a high performance low-pressure turbine[J]. Gas Turbine Experiment and Research,2013,23(2):6-11.(in Chinese)
[8] Binder A,Schroeder T H,Hourmouziadis J. Turbulence measurements in a multistage low-pressure turbine[R]. A 88-54207.
[9] Hodson H P,Huntsman I.An Investigation of boundary layer development in a multistage LP turbine[R].ASME 93-GT-310.
[10]盖尔哈特·默克尔.燃气轮机性能试验用的康氏水力测功器[J].热能动力工程,2005,20(6):650-654.Gerhard Merkle. Kahn hydraulic dynamometers for performance testing of gas turbines[J]. Journal of Engineering for Thermal Energy and Power,2005,20(6):650-654.(in Chinese)
[11]刘志刚,曾军,赵旺东,等.全尺寸对转涡轮若干关键试验技术的应用验证[J].燃气涡轮试验与研究,2017,30(1):1-6.LIU Zhigang,ZENG Jun,ZHAO Wangdong,et al. Investigation and verification of key technologies in full scale contrarotating turbine experiment[J]. Gas Turbine Experiment and Research,2017,30(1):1-6.(in Chinese)
[12]张健新,武卉,付鑫.水力测功器在燃气轮机性能试验中的应用[M]//中国航空学会.第六届中国航空学会青年科技论坛文集.北京:航空工业出版社,2014,1042-1047.ZHANG Jianxin,WU Hui,FU xin. Application of hydraulic dynamometer for performance testing of gasturbine[C]//the proceedings of the sixth Chinese Society of Aeronautice and Astronautics Science of Technique Youth forum,Aviation Industry Book Concern,2014:1042-1047.(in Chinese)
[13]周世英,段连丰,郭呈义.HB 7081-1994轴流涡轮气动性能试验[S].北京:中国航空工业总公司,1994:14-22.ZHOU Shiying,DUAN Lianfeng,GUO Chengyi.HB7081-1994 axial turbine aerodynamic performance test[S].Beijing:China Aviation Industry Corporation,1994:14-22.(in Chinese)
[14]田夫.叶轮机机械气动性能的实验研究方法[M].北京:清华大学出版社,2013:89-90.TIAN Fu.Experimental research method of aerodynamic performance of Turbomachinery[M]. Beijing:Tsinghua University Press,2013:89-90.(in Chinese)
[15]张清,郝勇,张大义,等.大涵道比发动机低压涡轮间隙分析与设计[J].航空发动机,2014,40(2):56-60.ZHANG Qing,HAO Yong,ZHANG Dayi,et al.Anasis and design of low pressure turbine tip clearance for high bypasss ratio engine[J].Aeroengine,2014,40(2):56-60.(in Chinese)
[16]谭洪川,乔渭阳,赵磊,等.低压涡轮气动/声学一体化设计—总体参数优化[J].推进技术,2012,33(4):573-578.TAN Hongchuan,QIAO Weiyang,ZHAO lei,et al. Aerodynamics/acoustics integration design method of low pressure turbine—overall parameters optimization[J]. Journal of Propulsion Technology,2012,33(4):573-578.(in Chinese)
[17]刘勋.低雷诺数低压涡轮气动性能分析[D].哈尔滨:哈尔滨工业大学,2008.LIU Xun. Aerodynamic performance analysis of low pressure turbine at low Reynolds Numbers[D]. Harbin:Harbin Institute of Technology,2008.(in Chinese)