适于航天应用的先进可靠的气动谐振点火研究

The gas dynamic resonance tube heating phenomenon emerges in some conditions when the open end of a semi-open cylindrical tube is placed in a co-axial, under-expanded sonic or supersonic free jet. The experimental measurement of gaseous pressure and temperature histories in the end of the resonance cavities of three types of resonance tubes, i.e., cylindrical, cone and cone-cylinder shaped tubes were carried out by employing high frequency heat-resistant pressure transducers and thermocouples, the pressure oscilating waves and major heating laws are obtained, and the gas dynamic and structural conditions of the nozzle-resonance tube system for generating resonance heating are determined. The two dimensional axisymmetrical Euler equations and N-S equations were used to simulate the non-stationary oscilating flow field in a resonance tube. The results delineat the interactions between shock waves and expansion waves, and the oscillating flow field characteristics inside and outside the resonance tube, and predict the resonance heating laws. The experimental and numerical results confirm that the intense oscillating shock wave accumulating dissipation is surely the major heating mechanism of the resonance tube. The gas in the tube is irreversibly compressed to a high time-averaged temperature which exceeds the stagnation temperature of the jet greatly. The new technique of gas dynamic resonance tube non-electric ignition for liquid rocket engines is just based on effective use of gas dynamic resonance thermal effect. This research work accumates many experimental data, determines the general criteria for engineering design and establishes the theoretical and technical basis for developing practical gas dynamic resonance tube igniters for liquid rocket engines.

本课题研究适用于航天应用的一种先进可靠的非电点火方式---气动谐振点火。所依据的物硐窒笫牵悍胖迷诟咚倥缌髁鞒≈械男痴窆茉谛痴裉跫鹿苣?气体发生强烈的气动谐振加热效应。拟通过实验研究和数值模拟揭示谐振管内外三维复杂振荡流场的流动机理、谐振条件和影响因素，为形成实用的航天非电点火新技术奠定理论和设计基础。