高超声速进气道中壁龛式预燃室进气特性

Characteristic of the entry of niche-like preburner in the hypersonic inlet

关键词:  煤油  进气道  预燃室  超音速燃烧

Key words:  Kerosene  Inlet  Precombustion chamber  Supersonic combustion

摘要:

在空气流量 4 6 9kg/s左右的地面连管试验台上 ,研究了高超声速进气道中壁龛式预燃室内外流场的气流特性。试验发现 ,壁龛式预燃室中流动状态的变化与激波 附面层之间相互作用关系密切。虽然在壁龛式预燃室中测得的总压值较低 ,气流总压损失较大 ,但仍满足两股气流之间超燃点火的压力匹配要求。因此 ,提出的壁龛式预燃室方案是可行的。

Abstract:

The experiments were set on the ground connected pipe test station with air mass rate of 4 69kg/s The internal flow field of the niche-like preburner in the inlet was investigated by means of pressure measurement The static pressure and total pressure measured in the internal flow field show that the total pressure in the niche-like preburner is low, which means it has the great total pressure loss in the inlet of preburner, dealing with the interaction of shock waves with boundary layers However, the total pressure in the niche-like preburner still satisfies the pressure requirement for supersonic ignition