短距起飞/垂直降落战斗机升力风扇驱动方案研究

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。

Research on drive mode of lift fan of STOVL fighter

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.