[1] 《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,2001:11.Aero-engine Design Handbook Editorial Board.Aero engine design handbook, Volume10:Turbine[M].Beijing:Aviation Industry Press,2001:11(in Chinese).
[2] DOWNS J P,LANDIS K K.Turbine cooling systems design:Past,present and future[C]//ASME Turbo Expo 2009:Power for Land,Sea,and Air.New York:ASME,2009:819-828.
[3] 朱莉娅,徐国强.涡轮冷却技术对航空发动机性能的影响[J].推进技术,2014,35(6):793-798.ZHU L Y,XU G Q.Effect of turbine cooling technology on aeroengine performance[J].Propulsion Technology,2014,35(6):793-798(in Chinese).
[4] 曹玉璋.航空发动机传热学[M].北京:北京航空航天大学出版社,2005:57.CAO Y Z.Aeroengine heat transfer[M].Beijng:Beihang University Press,2005:57(in Chinese).
[5] 吴大观.航空发动机研制工作论文集[M].北京:航空工业出版社,2009:69.WU D G.Aerospace development work paper collection[M].Beijing:Aviation Industry Press,2009:69(in Chinese).
[6] 王潘,隋岩峰,程农.涡扇发动机整机仿真平台设计及实现方法[J].系统仿真学报,2014,26(5):986-990.WANG P,SUI Y F,CHENG N.Design and implementation of turbofan engine simulation patform[J].Journal of System Simulation,2014,26(5):986-990(in Chinese).
[7] DEES J E,BOGARD D G,LEDEZMA G A,et al.Overall and adiabatic effectiveness values on a scaled up,simulated gas turbine vane[J].Journal of Turbomachinery-Transactions of the ASME,2013,135(5):595-605.
[8] 迟重然,温风波,王松涛,等.涡轮动叶冷却结构设计方法Ⅲ:气热耦合计算[J].工程热物理学报,2011,32(9):1485-1488.CHI Z R,WEN F B,WANG S T,et al.Turbine blade cooling structure design method Ⅲ:Conjugated heat transfer numerical simulation[J].Journal of Engineering Thermophysics,2011,32(9):1485-1488(in Chinese).
[9] KUSTERER K,HAGEDORN T,BOHN D,et al.Improvement of a film-cooled blade by application of the conjugate calculation technique[J].Journal of Turbomachinery,2006,128(3):572-578.
[10] 叶莹.气冷涡轮流热耦合模拟及冷却结构优化设计[D].北京:中国科学院大学,2017.YE Y.Conjugated heat transfer numerical simulation of air-cooled turbine flow and optimal design of cooling structure[D].Beijing:University of Chinese Academy of Sciences,2017(in Chinese).
[11] 王松涛,迟重然,温风波,等.涡轮动叶冷却结构设计方法Ⅰ:参数化设计[J].工程热物理学报,2011,32(4):581-584.WANG S T,CHI Z R,WEN F B,et al.Turbine blade cooling structure design method I:Parametric design[J].Journal of Engineering Thermophysics,2011,32(4):581-584(in Chinese).
[12] 虞跨海,李立州,岳珠峰.基于解析及特征造型的涡轮冷却叶片参数化设计[J].推进技术,2007,28(6):637-640.YU K H,LI L Z,YUE Z F.Parametric design of turbine cooling blades based on analytic and characteristic modeling[J].Propulsion Technology,2007,28(6):637-640(in Chinese).
[13] 宋玉旺,席平.基于特征造型技术的涡轮叶片参数化设计[J].北京航空航天大学学报,2004,30(4):321-324.SONG Y W,XI P.Parametric design of turbine blade based on feature modeling[J].Journal of Beijing University of Aeronautics and Astronautics,2004,30(4):321-324(in Chinese).
[14] 李吉星,席平.涡轮叶片导管快速建模[J].北京航空航天大学学报,2016,42(6):1149-1155.LI J X,XI P.Rapid modeling of impingement pipe in turbine blade[J].Journal of Beijing University of Aeronautics and Astronautics,2016,42(6):1149-1155(in Chinese).
[15] NOWAK G,WRÓBLEWSKI W.Optimization of blade cooling system with use of conjugate heat transfer approach[J].International Journal of Thermal Sciences,2011,50(9):1770-1781.
[16] 罗磊,卢少鹏,迟重然,等.气热耦合条件下涡轮动叶叶型与冷却结构优化[J].推进技术,2014,35(5):603-609.LUO L,LU S P,CHI Z R,et al.Conjugate heat transfer optimization for blade profiles and cooling structure in turbine rotor[J].Advance Technology,2014,35(5):603-609(in Chinese).
[17] 付光辉,席平,张宝源,等.涡轮气冷叶片传热分析数据提取技术研究[J].图学学报,2015,36(3):384-391.FU G H,XI P,ZHANG B Y,et al.Data extraction technology for heat transfer analysis of air-cooled turbine blades[J].Journal of Graphics,2015,36(3):384-391(in Chinese).
[18] 席平,王添.面向分析的产品建模技术概述[J].航空制造技术,2017,540(21):16-20.XI P,WANG T.An analysis-oriented product modeling technology[J].Aeronautical Manufacturing Technology,2017,540(21):16-20(in Chinese).
[19] 龚勋.涡轮冷却叶片结构网格参数化方法研究[D].南京:南京航空航天大学,2016.GONG X.Research on parameterization method of turbine cooling blade structure grid[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2016(in Chinese).
[20] CHI Z R,LIU H Q,ZANG S S.Geometrical optimization of nonuniform impingement cooling structure with variable-diameter jet holes[J].International Journal of Heat & Mass Transfer,2017,108:549-560. |