航空涡轴发动机发展趋势

邹望之; 郑新前

doi:10.13224/j.cnki.jasp.2019.12.006

航空涡轴发动机发展趋势

doi: 10.13224/j.cnki.jasp.2019.12.006

邹望之^1,2,
郑新前^1,2

基金项目: 国家科技重大专项(2017-Ⅱ-0004-0016); 国家自然科学基金(51876097)

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出版历程
- 收稿日期: 2019-05-26
- 刊出日期: 2019-12-28

Development trends of aero turboshaft engines

ZOU Wangzhi^1,2,
ZHENG Xinqian^1,2

1.
State Laboratory of Automotive Safety and Energy,School of Vehicle and Mobility,Tsinghua University,Beijing 100084,China
2.
Institute for Aero Engine,Tsinghua University,Beijing 100084,China

摘要

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。
- 直升机 /
- 涡轴发动机 /
- 发展趋势 /
- 结构布局 /
- 发动机性能
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.
- helicopter /
- turboshaft engine /
- development trends /
- structural layout /
- engine performance

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