纯净空气液态煤油超声速燃烧室性能研究

液态煤油高热值、高密度,还容易储存、便于携带,在飞行Ma数小于8的飞行条件下,煤油是超燃冲压发动机的理想燃料,如何实现煤油在超声速燃烧室中稳定燃烧是关键。本文在西北工业大学电阻加热超燃冲压发动机实验台上,针对给定的燃烧室,对以航空煤油为燃料的超声速燃烧冲压发动机燃烧室性能进行初步试验研究。实验来流空气总温为870-930 K,总压保持在77 kPa左右,燃烧室进口Ma数为2。同时结合CFD模拟,对3个不同油气比下燃烧室性能参数进行了对比分析。研究结果认为:要成功地实验煤油点火并稳定燃烧,成功设计凹槽及分布位置是关键;选择合适的油气比,可在提高燃烧室性能的同时保持隔离段的抗扰动能力。

Investigation of Performance of Scramjet Combustion Using Kerosene

The aviation kerosene is a practical candidate fuel for scram-jet engine in the flight regimes of Mach number less than 8, because of the characteristic of high energy, high density, safety and portable. The key is how to achieve shabbily burning in super combustor. In this paper, the ignition characteristics of a scramjet combustor model fueled by aviation kerosene is experimentally investigated by using the resistance heating direct-connected supersonic combustion facility of Northwestern Polytechnical University. The inflow conditions at the direct-connected combustor entrance are specified as: the nominal Mach of 2, the total temperature of 870-930 K and the total pressure of about 770 kPa. Three combustor performances of different ER are compared and analyzed by applying CFD simulation. The experimental results suggest that the cavity design is a key problem for kerosene successful ignition in the combustor. The choice of appropriate gas-oil ratio can increase the performance of combustor and keep the isolator from being interfered by gas.