Development trends of aero turboshaft engines
-
摘要: 基于国际上典型航空涡轴发动机的发展历程,概括了航空涡轴发动机产业发展趋势,其所呈现的系列化、军民两用化和国际合作化特点十分鲜明,国家层面实施的发展计划对航空涡轴发动机的发展起到了重要引领作用。基于统计分析,展望了航空涡轴发动机结构布局和性能发展趋势。研究表明:在结构布局方面,航空涡轴发动机朝着结构紧凑化方向发展,压气机和涡轮级数呈现不断减少的趋势。1 500 kW级以下的航空涡轴发动机将更普遍地采用单级/双级离心压气机和单级涡轮,1 500 kW以上的航空涡轴发动机将更普遍地采用轴流+离心组合压气机和双级涡轮,同心轴前输出功率型式成为主流功率输出型式。在性能方面,未来先进航空涡轴发动机的压比将达到30,涡轮前温度将达到1 900 K,油耗将低至0.20 kg/(kW·h),单位功率将达到400 kW/(kg/s),功质比将达到14 kW/kg。Abstract: Based on the history of the internationally famous turboshaft engines, the development trends of turboshaft engine industry were summarized, showing distinctive features of serialization, dual-use and international cooperation. Basides, the national-level development programs have played a leading role in the progress of turboshaft engines. Based on the statistical analysis method, the future trends of turboshaft engine structural layout and performance were predicted. In terms of structural layout, turboshaft engines would be developed towards the direction of compact layout, and the stage numbers of compressor and turbine show a decreasing trend. More specifically, single-stage/two-stage centrifugal compressors and single-stage turbines would be more extensively used in turboshaft engines with power output less than 1 500 kW, while axial-centrifugal compressors and two-stage turbines would be more commonly used in engines with power output greater than 1 500 kW. In addition, forward facing output with concentric shaft would become the main power output layout. In terms of engine performance, for the advanced turboshaft engines in the future, the pressure ratio and turbine inlet temperature would be up to 30 and 1 900 K, respectively, the specific fuel consumption would be as low as 0.20 kg/(kW·h), the specific power and power to mass ratio would reach 400 kW/(kg/s) and 14 kW/kg, respectively.
-
Key words:
- helicopter /
- turboshaft engine /
- development trends /
- structural layout /
- engine performance
-
[1] 方昌德.航空发动机的发展历程[M].北京:航空工业出版社,2007. [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):1-5. FANG Changde.A century of aero-engine in retrospect[J].Gas Turbine Experiment and Research,2003,16(4):1-5.(in Chinese) [3] 蒋建军,冯国颂.涡轴发动机的系列化发展[C]∥第13届燃烧与传热传质专业学术讨论会论文集.北京:中国航空学会,2005:345-351. [4] 王巍巍.航空发动机领域军民融合发展的思考[J].航空动力,2018,3(3):53-56. WANG Weiwei.Thoughts on the civil-military integration development of aero engine[J].Aerospace Power,2018,3(3):53-56.(in Chinese) [5] PETER J S.The history of aircraft gas turbine engine development in the United States:a tradition of excellence[M].New York:ASME Press,1999. [6] AIAA Air Breathing Propulsion Technical Committee.The versatile affordable advanced turbine engines (VAATE) initiative[R].Reston,Virginia,USA:AIAA,2006. [7] 尹泽勇,曾源江,石建成,等.涡轴(涡桨)/涡扇(涡喷)发动机通用核心机技术[J].航空动力学报,2008,23(11):2088-2094. YIN Zeyong,ZENG Yuanjiang,SHI Jiancheng,et al.Versatile core engine technology for turboshaft (turboprop)/turbofan (turbojet) engines[J].Journal of Aerospace Power,2008,23(11):2088-2094.(in Chinese) [8] 黄顺洲,胡骏,江和甫.核心机及其派生发动机发展的方法[J].航空动力学报,2006,21(2):241-247. HUANG Shunzhou,HU Jun,JIANG Hefu.Investigation of core engine and derivative aero-engine development[J].Journal of Aerospace Power,2006,21(2):241-247.(in Chinese) [9] 王道荫.迈向21世纪的航空科学技术[M].北京:航空工业出版社,1994. [10] 李建华,蔡建兵,申余兵.涡轴发动机发展展望[J].国际航空,2013(9):75-77. LI Jianhua,CAI Jianbing,SHEN Yubing.Outlook of turboshaft engine development[J].International Aviation,2013(9):75-77.(in Chinese) [11] 郭允良.国内外涡轮轴发动机性能、结构特点及其技术发展[M].北京:蓝天出版社,1990. [12] 梁琴琴.美国典型航空发动机发展计划及对技术创新的影响[J].全球科技经济瞭望,2015,30(7):68-76. LIANG Qinqin.U.S.’ typical aeroengine development program and the influence on technology innovation[J].Global Science,Technology and Economy Outlook,2015,30(7):68-76.(in Chinese) [13] 肖蔓.AATE和ITEP计划下的涡轴发动机分阶段研发综述[J].航空发动机,2016,42(2):98-102. XIAO Man.Review of research and development for turboshaft engine based on AATE and ITEP program[J].Journal of Aeroengine,2016,42(2):98-102.(in Chinese) [14] HIRSCHBERG M.The case for ITEP-power for the future[EB/OL].[2019-05-06].https:∥vtol.org/news/commentary-the-case-for-itep-power-for-the-future. [15] GIRAUD M.Power level influence on architecture of small helicopter turboshaft engines[R].ASME Paper 86-GT-191,1986. [16] PALMER D L,WATERMAN W F.Design and development of an advanced two-stage centrifugal compressor[J].Journal of Turbomachinery,1995,117(2):205-212. [17] 《航空发动机设计手册》总编委会.航空发动机设计手册:第六册 涡桨及涡轴发动机总体[M].北京:航空工业出版社,2001. [18] SCHINZL P,MALZACHER F,MONCOUTIE P,et al.The successful development history of the MTR390 turboshaft engine from the definition of the design to the series production[EB/OL].[2019-05-06].http:∥vbt.ebi.kit.edu/index.pl/Haupt_Menu_all/professor/zarzalis/DGLR-MTR-2000.pdf. [19] 林左鸣.世界航空发动机手册[M].北京:航空工业出版社,2012. [20] 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. [21] 黄维娜,李忠祥.国外航空发动机简明手册[M].西安:西北工业大学出版社,2014. [22] GUNSTON B.Jane’s aero-engines[M].Coulsdon,Surrey,UK:Jane’s Information Group,2001. [23] LEYES R A,FLEMING W A.The history of North American small gas turbine aircraft engines[M].Reston,Virginia,USA:AIAA,1999. [24] DONOHIE H G.T700/CT7 growth engine for European helicopters[R].London:the 11th European Rotorcraft Forum,1985. [25] EL HADIK A A.The impact of atmospheric conditions on gas turbine performance[J].Journal of Engineering for Gas Turbines and Power,1990,112(4):590-596. [26] 任智勇,李志鹏,王俊琦.湿热盐雾对涡轴发动机性能的影响分析[J].机械研究与应用,2017,30(4):27-29. REN Zhiyong,LI Zhipeng,WANG Junqi.Analysis on effect of hot moisture and salt spray on the performance of turboshaft engine[J].Mechanical Research and Application,2017,30(4):27-29.(in Chinese)
点击查看大图
计量
- 文章访问数: 800
- HTML浏览量: 24
- PDF量: 416
- 被引次数: 0