固体火箭超燃冲压发动机点火燃烧过程实验研究

Experimental study on ignition and combustion process of solid rocket scramjet

关键词:  固体火箭超燃冲压发动机  含硼贫氧燃料  掺混增强装置  燃烧性能  补燃室

Key words:  Solid rocket scramjet  Boron based oxygen-poor solid propellant  Mixing enhancement device  Combustion performance  Secondary combustor

摘要:

为解决硼基贫氧燃料固体火箭超燃冲压发动机补燃室内硼颗粒超声速点火燃烧难题，设计制造了在超声速燃气射流掺混区域开设观察窗的点火燃烧过程试验样机，开展了含硼贫氧固体燃料的超声速点火试验。试验模拟了26 km，Ma5.9的飞行工况并通过高速摄像获得了点火燃烧过程的火焰形态。试验结果表明：掺混增强装置可以显著改善补燃室内存在的分层流动和一次燃气气固两相分离的现象，为硼颗粒提供良好的点火条件从而提升其附近硼颗粒的点火燃烧性能。通过合理设计掺混增强装置位置，将硼颗粒在一次燃气喷注口附近的高温点火区点燃比在补燃室中段点燃具有更高的燃烧效率，本文设计的燃烧组织结构在试验中实现了硼贫氧固体燃料0.812的燃烧效率。

Abstract:

In order to solve the problem of boron particle supersonic ignition combustion in the combustion chamber of boron-based oxygen-poor solid rocket scramjet， a test prototype with an observation window in the mixing area of supersonic gas jet was designed and manufactured and the supersonic ignition test of boron-based oxygen-poor solid fuel was carried out. The flight condition of 26 km and Ma5.9 was simulated and the flame morphology of ignition and combustion process was obtained by high-speed camera. Experiment result show that，the mixing enhancement device can significantly improve the stratified flow and the separation of gas and solid phases of the primary combustion in the combustion chamber， provide good ignition conditions for boron particles so as to improve the ignition and combustion performance of boron particles nearby. The ignition of boron particles in the high temperature ignition area near the primary gas injection has higher combustion efficiency than ignition in the middle of the combustion chamber. The combustion structure designed in this paper achieved the combustion efficiency of 0.812 for boron oxygen-poor solid fuel in the test.