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

作　　者：李建锋[1] 吕俊复[2] 黄少江 LI Jianfeng;LüJunfu;Huang Shaojiang(China Electricity Council,Beijing 100761,China;Key Laboratory for Thermal Science and Power Engineering of Ministry of Education,Tsinghua University,Beijing 100084,China;66350 Troop,Baoding 071000,China)

机构地区：[1]中国电力企业联合会,北京100761 [2]清华大学热科学和动力工程教育部重点实验室,北京100084 [3]66350部队,河北保定071000

出　　处：《热科学与技术》2020年第2期193-204,共12页Journal of Thermal Science and Technology

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,提出了一种利用发动机外涵道抽气在小涡轮中做功以驱动升力风扇的新方案,并建立了小涡轮驱动方式下的总升力和热效率计算模型。对总升力和热效率的计算结果表明,在选取合适的抽气比及小涡轮进气温度时,小涡轮驱动方式所产生的总升力与轴驱动方式相当或更大。小涡轮驱动方式除垂直起降阶段系统热效率略低外,在质量控制、设计开发难度、调节与控制、升力风扇布置灵活性等方面均具有优势。In order to reduce the design and manufacture difficulty of of the liftfan shaft drive system of short takeoff and vertical landing(STOVL)fighter, the way of extracting air from ducted outside of engine and making the air act within the small turbine to drive the lift fan was proposed.The computational model of total lift and thermal efficiency of small turbine-driven mode were established. The results show that, when the suction flow rate and small turbine inlet temperatureare appropriate, the total lift generated by the small turbine drive mode is comparable to or greater than that generated by the shaft drivemode. In addition to the slightly lower thermal efficiency of the system in vertical takeoff and landing stage, the small turbine drive mode has advantages in quality control, design and development difficulty, adjustment and control, and lift fan layout flexibility.

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 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]