液体火箭发动机涡轮火药燃气供应系统性能研究  

Performance research on turbine powder gas feed system in liquid rocket engine

作　　者：李应强[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2008年第6期14-18,共5页Journal of Rocket Propulsion

摘　　要：采用变燃面装药固体火箭发动机的"瞬时压强平衡法"和流量平衡的关系式,较准确地对涡轮喷嘴前火药燃气性能进行了计算,得到了涡轮喷嘴前火药燃气性能的各种参数,这些参数有助于对涡轮起动性能和发动机加速性的研究。This article adopts the method of instantaneous pressure equilibrium of variational burning surface of powder in solid rocket engine and flow-rate equilibrium relation to calculate exactly the performance of powder gas in the front of the turbine nozzle. Various performance parameters of the powder gas in the front of the turbine nozzle were obtained. These parameters will be helpful to the research of turbine start and engine acceleration performances.

关 键 词：液体火箭发动机 涡轮喷嘴 火药燃气 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]