CAJ | 학술논문

扩张型双喉道喷管存在起动问题,使喷管推力性能显著下降。为此,提出了扩张段注气解决喷管起动问题的方案,并利用数值模拟方法,针对二元扩张型双喉道喷管,研究了扩张段注气压比、注气位置等对喷管流动和性能的影响。研究结果表明：扩张段注气可以产生斜激波系和大的分离区,改变了扩张型双喉道喷管主气流通道的形状,减小了激波损失,解决了喷管的起动问题,并使喷管性能显著提高;注气缝位于扩张段中间时,容易形成连续扩张的主流通道,有利于主流的加速和产生推力,因此其推力性能最好。
확장형쌍후도분관존재기동문제,사분관추력성능현저하강。위차,제출료확장단주기해결분관기동문제적방안,병이용수치모의방법,침대이원확장형쌍후도분관,연구료확장단주기압비、주기위치등대분관류동화성능적영향。연구결과표명：확장단주기가이산생사격파계화대적분리구,개변료확장형쌍후도분관주기류통도적형상,감소료격파손실,해결료분관적기동문제,병사분관성능현저제고;주기봉위우확장단중간시,용역형성련속확장적주류통도,유리우주류적가속화산생추력,인차기추력성능최호。
A scheme of injection at the divergent section is put forward to solve the starting problem in the divergent dual throat nozzle.The effects of the injection flow at the divergent section and the injection location on the flow and the performance of the nozzle are studied by two-dimensional divergent numerical simulation.Results indicate that oblique shock series and large separation areas can be made by the injection at the divergent section and change the flow channel shape of the divergent dual throat nozzle,so that the shock losses are reduced,the nozzle starting problem is solved,and the dual throat nozzle performance is remarkably improved.When the injection slot is in the middle of the divergent section,the continuous divergent channel is easily formed,it is helpful to accelerate the main stream and to generate the thrust,and the best thrust performance can be obtained on this condition.