富氧补燃循环液氧煤油发动机深度推力调节方案对比分析  

Comparison of Deep Thrust Throttling Schemes of Oxidizer-rich Gas Staged Combustion Liquid Oxidizer/Kerosene Engine

作　　者：王海燕[1] 邢理想[1] 高玉闪[1] 陈文 WANG Haiyan;XING Lixiang;GAO Yushan;CHEN Wen(Xi'an Aerospace Propulsion Institute,Xi'an 710100, China)

机构地区：[1]西安航天动力研究所

出　　处：《载人航天》2019年第3期389-396,共8页Manned Spaceflight

摘　　要：针对富氧补燃循环液氧煤油发动机目前推力调节范围窄的问题,以某型富氧补燃循环液氧煤油发动机为原型,建立了发动机非线性静态数学模型,利用Matlab计算分析了5种推力调节方案,其中调节推力室供应路流量的方案不可行;调节燃气发生器燃料路流量会引起燃气发生器混合比严重偏离稳定工作点;联合调节燃气发生器燃料路和氧路流量使得系统复杂;调节涡轮燃气流量可获得较宽推力调节范围,未来将针对该调节方案开展技术研究。Thrust of the oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine should be able to vary over a wide range to meet the requirements of deep space exploration in the future, however the thrust can only vary over a small range at present. A nonlinear mathematical model of oxidizer-rich gas staged combustion liquid oxidizer/kerosene engine was established to solve the problem. Five types of thrust throttling schemes were calculated and analyzed with Matlab. The results showed that regulating the fuel flow rate of the combustion chamber was impossible;Adjusting the fuel flow rate of gas generator resulted in a serious deviation of mixture ratio which would cause unsteady operation. A combined regulation of the oxidizer and fuel supply of the gas generator increased the complexity of the system. Changing the gas flow through the turbine was feasible to accomplish deep throttling which will be further investigated in the future.

关 键 词：富氧补燃循环 液氧煤油发动机 推力深度调节特性 涡轮燃气分流 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]