文章摘要
李建锋,吕俊复.短距起飞/垂直降落战斗机升力风扇驱动方案研究[J].,2020,19(2):193-204
短距起飞/垂直降落战斗机升力风扇驱动方案研究
Research on drive mode of lift fan of STOVL fighter
投稿时间:2018-11-01  修订日期:2019-07-29
DOI:10.13738/j.issn.1671-8097.018210
中文关键词: 短距起飞/垂直降落  战斗机 升力风扇  升力 效率  外涵道
英文关键词: STOVL  fighter  lift fan  lift  efficiency  ducted outside
基金项目:
作者单位E-mail
李建锋 中国电力企业联合会 qhlijf@163.com 
吕俊复 清华大学热科学和动力工程教育部重点实验室  
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中文摘要:
      为了降低短距起飞/垂直降落战斗机轴驱动升力风扇驱动系统的设计制造难度,本文提出了利用发动机外涵道抽气,经小燃烧室提升温度后,通过在小涡轮内做功驱动升力风扇的方式,并建立了小涡轮驱动方式总升力和热效率的计算模型。对总升力和热效率的计算结果表明,在抽气比为0.3时,小涡轮进气温度1800K时;或者在增加抽气比至0.6时,即使小涡轮进口气温为1370K时,小涡轮驱动方式所产生的总升力与轴驱动相当。不过小涡轮驱动方式的系统热效率小于轴驱动方式。采用小涡轮驱动方式具有质量较小、设计与控制难度较小等特点,也更有利于升力风扇在机体内的布置。
英文摘要:
      In order to reduce the difficulty of short takeoff and vertical landing(STOVL) aircraft design and manufacture of the lift fan shaft drive system, the way by extracting air from ducted outside of engine, after a small chamber elevated temperatures, the air acting within the small turbine to drive the lift fan was proposed and the computational model of total lift and thermal efficiency of small turbine-driven mode were established. The calculation results of total lift and thermal efficiency show that, when the suction flow rate was 0.3 and the turbine inlet temperature was 1800K, or the suction flow rate increasing to 0.6, total lift of small turbine-driven mode quite with the shaft drive mode in spite of the drive turbine inlet temperature was 1370K. However, system thermal efficiency of the small turbine-driven mode is slightly smaller than the shaft drive mode. A small turbine-driven mode also has a smaller mass, smaller difficult to design and control and other features, but also more conducive to the lift fan is arranged in the fighter.
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