中心锥体结构脉冲爆震火箭发动机初步实验

Preliminary experimental investigation on pulse detonation rocket engine with central cone configuration

为了改善采用液态燃料的脉冲爆震火箭发动机内部燃料的雾化以及燃料混合物的掺混状况,采用了一种中心锥体结构.该结构发动机不采用Shchelkin螺旋增爆装置,而采用中心锥体结构、二级供应方式.采用航空煤油为燃料、压缩氧气为氧化剂、压缩氮气为隔离气体,在该结构脉冲爆震火箭发动机上获得了充分发展的爆震波并且能够在多循环条件下稳定工作.实验结果表明,该结构可以大大缩短DDT(deflagra-tion to detonation transition)距离,在实验条件下爆燃向爆震转变距离约为管径的5倍.较之同一管径采用Shchelkin螺旋增爆装置的脉冲爆震火箭发动机,该结构发动机的爆燃向爆震转变距离缩短了57.5%.

In order to improve the atomization of liquid fuel and mixing of reactants in side the pulse detonation rocket engine using liquid fuel, a pulse detonation rocket engine with a different configuration was invented. A central cone instead of Shchelkin spiral was used in this engine. Reactants could be injected into the engine both through the engine head and the central cone. With kerosene used as fuel, oxygen as oxidizer and nitrogen as purge gas, fully developed detonation waves were generated in this engine, which could operate steadily on multi cycle mode. The result also indicates that this engine could greatly shorten the DDT （deflagration to detonation transition） run-up distance, and the DDT ruwup distance is approximately five times of the inner diameter of detonation tube. Compared with the approach of installing Shchelkin spiral in the detonation tube as DDT enhancement de vice, the DDT run-up distance of this engine was shortened by 57.5%.