摘要：空气涡轮火箭或涡轮基组合冲压发动机中,混合装置对于提高燃烧效率具有重要的作用。为了提高燃气与空气的混合效率,针对波瓣型混合器提出了混合器出口轴向速度一致的原则来指导设计混合器。设计了两种不同类型的波瓣型混合器,并通过数值模拟分析了混合器出口截面形式和中心体端面对混合效率的影响。结果表明:混合器燃气与空气出口截面的面积比是波瓣型混合器设计的关键因素,恰当调整出口面积比使出口速度接近可以明显提高混合效率;中心体截面缩进和凸出会使混合效率降低。

摘要：Solid propellant air-turbo-rocket(SPATR) is an air-breathing propulsion system.A numerical model of performance and characteristics analysis for SPATR was presented and the corresponding computer program was written according to the operation characteristics of *** influence on the SPATR performance at design point caused by the gas generator exit parameters and compressor pressure ratio had been computed and analyzed in *** off-design performance of SPATR at sea level and high altitude had also been *** performance of thrust and specific impulse for SPATR with different solid propellant had been compared at off-design points,and the off-design performance comparison had been made between fuel-rich and *** computation results indicated that SPATR operates within wide range of Mach number(0~3) and altitude(0~12 km),and SPATR possesses high specific thrust(1 200 N/(kg/s)) and high specific impulse(7 000 N/(kg/s)) when fuel-air ratio of combustor equals fuel-air ratio.