CAJ | 학술논문

采用气压驱动供粉方式,开展了Metal/N2 O火箭发动机点火实验。通过分析活塞位移及燃烧室压强振荡,研究了两相流动特性。根据液滴燃烧模型,分析了燃烧室压强、颗粒滞留时间、氧燃比等因素对发动机燃烧效率的影响。通过以上研究,验证了此种发动机的优良性能。结果表明,输送管路中固相浓度脉动幅度在颗粒粒径40μm、两相流空隙率97%、氮气流动速度27 m/s 情况下小于±0.36%；Mg/N2 O 实验平均特征速度效率在燃烧室压强0.5 MPa 情况下高达96.4%,Al/N2 O实验在燃烧室0.91 MPa情况下燃烧效率达到88.5%；提高燃烧室压强、颗粒滞留时间,可提高燃烧效率,但氧燃比对燃烧效率影响较为复杂。
채용기압구동공분방식,개전료Metal/N2 O화전발동궤점화실험。통과분석활새위이급연소실압강진탕,연구료량상류동특성。근거액적연소모형,분석료연소실압강、과립체류시간、양연비등인소대발동궤연소효솔적영향。통과이상연구,험증료차충발동궤적우량성능。결과표명,수송관로중고상농도맥동폭도재과립립경40μm、량상류공극솔97%、담기류동속도27 m/s 정황하소우±0.36%；Mg/N2 O 실험평균특정속도효솔재연소실압강0.5 MPa 정황하고체96.4%,Al/N2 O실험재연소실0.91 MPa정황하연소효솔체도88.5%；제고연소실압강、과립체류시간,가제고연소효솔,단양연비대연소효솔영향교위복잡。
Hot fire tests of metal/N2O rocket engine were carried out,using pneumatic driving powder feeding device.The two-phase flow characteristics were investigated through analyzing piston displacement and combustion pressure oscillation.According to droplet combustion model,the influence of factors such as combustion chamber pressure,particle residence time and O/F ratio were analyzed.The study verifies good performance of the engine. The results show that the concentration pulsating amplitude of solid phase in pipeline is less than ±0.36% when two-phase flow void ratio is 97% and flow velocity is 27 m/s.The average characteristic velosity efficiency of Mg/N2 O tests are about 96.4% at 0.5 MPa combustion chamber pressure,and reaches 88.5% of Al/N2 O tests at 0.91 MPa. Increasing combustion chamber pressure and particle residence time can improve combustion efficiency,but the effect of O/F ratio on combustion efficiency is relatively complex.