新型超紧凑双级离心一体化压气机概念设计技术研究
|
摘要
在常规双级离心压气机的基础上,提出了双级离心一体化压气机设计概念,可在不增加叶轮出口切线速度的前提下,用单个一体化离心叶轮实现双级离心压气机的增压比。对某原型双级离心压气机开展离心压气机一体化设计结果表明,重量(质量)可减少19%,设计点除效率略有降低之外,堵点流量与喘点压比与原型基本一致,同时缩短了转子系统27%的轴向长度,可显著改善转子动力特性,降低制造成本,具有较好的工程应用前景。
On the basis of conventional two-stage centrifugal compressor, a design concept of two-stage centrifugal integrated compressor was proposed. The pressure ratio of two-stage centrifugal compressor can be achieved by a single integrated double sided centrifugal impeller without increasing the tangent velocity of the impeller outlet. The results of new centrifugal compressor integrated design for a prototype two-stage centrifugal compressor show that the weight can be greatly reduced by 19%. Besides a slight decrease in efficiency at the design point, the flow rate and surge point pressure ratio are basically the same as the prototype, and the axial length of the rotor system is reduced by 27%. The dynamic characteristics of the rotor can be significantly improved and the cost can be reduced. The new super-compact design shows good prospects for engineering application.
On the basis of conventional two-stage centrifugal compressor, a design concept of two-stage centrifugal integrated compressor was proposed. The pressure ratio of two-stage centrifugal compressor can be achieved by a single integrated double sided centrifugal impeller without increasing the tangent velocity of the impeller outlet. The results of new centrifugal compressor integrated design for a prototype two-stage centrifugal compressor show that the weight can be greatly reduced by 19%. Besides a slight decrease in efficiency at the design point, the flow rate and surge point pressure ratio are basically the same as the prototype, and the axial length of the rotor system is reduced by 27%. The dynamic characteristics of the rotor can be significantly improved and the cost can be reduced. The new super-compact design shows good prospects for engineering application.
引文
[1]胡晓煜.世界中小型航空发动机手册[M].北京:航空工业出版社,2006.Hu Xiaoyu.The world’s small and medium aircraft engine handbook[M].Beijing:Aviation Industry Press,2006.(in Chinese)
[2]方昌德.航空发动机百年回顾[J].燃气涡轮试验与研究,2003,16(4):155-161.Fang Dechang.Aero-engine centennial review[J].Gas Turbine Experiment and Research,2003,16(4):155-161.(in Chinese)
[3]Whitfield B.Design of radial turbo-machines[M].UK:Longman Singapore Publishers,1990.
[4]Cousins W T,Dalton K K,Andersen T T,et al.Pressure and temperature distortion testing of a two-stage centrifugal compressor[J].Journal of Engineering for Gas Turbines and Power,1994,116(3):567-573.
[5]Palmer D L,Waterman W F.Design and development of an advanced two-stage centri-fugal compressor[J].Journal of Turbo-machinery,1995,117:205-212.
[6]杨策,刘磊,胡良军,等.两级离心压气机设计及内部流场分析[C]//工程热物理学会热机气动热力学2006年年会,2006.Yang Ce,Liu Lei,Hu Liangjun,et al.Design and flow analysis of two stage centrifugal compressor field[C]//2016Thermodynamic Aerodynamics Annual Conference of Chinese Society of Engineering Thermophysics,2006.(in Chinese)
[7]Osborne C.Aerodynamic and mechanical design of an 8:1 pressure ratio centrifugal compressor[R].NASA CR-134782,1975.
[8]李燕生,陆桂林.向心透平与离心压气机[M].北京:机械工业出版社,1987.Li Yansheng,Lu Guilin.Centripetal turbine and centrifugal compressor[M].Beijing:China Machine Press,1987.(in Chinese)
[9]黄生勤,邬国凡.单级离心压气机:中国,CN105275874A[P].2016-01-27.Huang Shengqin,Wu Guofan.Single stage centrifugal compressor:China,CN105275874A[P].2016-01-27.(in Chinese)
[10]黄生勤,李维.一种双面离心叶轮及其加工方法:中国,CN106050735A[P].2016-06-03.Huang Shengqin,Li Wei.A double-sided centrifugal impeller and processing method:China,CN106050735A[P].2016-06-03.(in Chinese)
[2]方昌德.航空发动机百年回顾[J].燃气涡轮试验与研究,2003,16(4):155-161.Fang Dechang.Aero-engine centennial review[J].Gas Turbine Experiment and Research,2003,16(4):155-161.(in Chinese)
[3]Whitfield B.Design of radial turbo-machines[M].UK:Longman Singapore Publishers,1990.
[4]Cousins W T,Dalton K K,Andersen T T,et al.Pressure and temperature distortion testing of a two-stage centrifugal compressor[J].Journal of Engineering for Gas Turbines and Power,1994,116(3):567-573.
[5]Palmer D L,Waterman W F.Design and development of an advanced two-stage centri-fugal compressor[J].Journal of Turbo-machinery,1995,117:205-212.
[6]杨策,刘磊,胡良军,等.两级离心压气机设计及内部流场分析[C]//工程热物理学会热机气动热力学2006年年会,2006.Yang Ce,Liu Lei,Hu Liangjun,et al.Design and flow analysis of two stage centrifugal compressor field[C]//2016Thermodynamic Aerodynamics Annual Conference of Chinese Society of Engineering Thermophysics,2006.(in Chinese)
[7]Osborne C.Aerodynamic and mechanical design of an 8:1 pressure ratio centrifugal compressor[R].NASA CR-134782,1975.
[8]李燕生,陆桂林.向心透平与离心压气机[M].北京:机械工业出版社,1987.Li Yansheng,Lu Guilin.Centripetal turbine and centrifugal compressor[M].Beijing:China Machine Press,1987.(in Chinese)
[9]黄生勤,邬国凡.单级离心压气机:中国,CN105275874A[P].2016-01-27.Huang Shengqin,Wu Guofan.Single stage centrifugal compressor:China,CN105275874A[P].2016-01-27.(in Chinese)
[10]黄生勤,李维.一种双面离心叶轮及其加工方法:中国,CN106050735A[P].2016-06-03.Huang Shengqin,Li Wei.A double-sided centrifugal impeller and processing method:China,CN106050735A[P].2016-06-03.(in Chinese)