开式循环液氧煤油发动机推力调节特性分析  

Investigation of thrust adjustment characteristics of open-cycle LOX/kerosene engine

作　　者：王通 刘上 姜垒 韩红伟 WANG Tong;LIU Shang;JIANG Lei;HAN Hongwei(Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所液体火箭发动机技术重点实验室,陕西西安710100

出　　处：《火箭推进》2023年第2期57-65,82,共10页Journal of Rocket Propulsion

摘　　要：以开式循环液氧煤油发动机为研究对象,重点建立了冷却套传热模型,并嵌入发动机系统静态模型,通过试车数据验证了静态模型的准确性。通过静态调节仿真计算,对比5种不同推力调节方案的特性。结果表明:氧副路调节方案和涡轮燃气分流方案不能满足要求;主路节流方案、副路双路调节方案和氧副路双工位阀+燃料副路调节器方案均可以实现发动机推力的大范围调节;综合考虑调节元件的设计难度和发动机应用需求,氧副路双工位阀+燃料副路调节器方案有望在工程研制中得到应用。A cooling jacket heat transfer model was established for the open-cycle LOX/kerosene engine and embedded in the engine system static model.The accuracy of the static model was verified by the test data.The characteristics of five different thrust adjustment schemes were compared by static control simulation calculation.The results show that it is not feasible to adjust the oxidizer path scheme of the gas generator and the flow rate scheme of the gas turbine.The main throttling scheme,the secondary double-way regulating scheme and the gas generator oxygen path setting double-position valve with the fuel path setting regulator scheme can realize the large-scale adjustment of the engine thrust.Considering the difficulty of the design of the adjusting element and the requirement of the engine application,the gas generator oxygen path setting double-position valve with the fuel path setting regulator scheme is expected to be applied in the engineering development.

关 键 词：开式循环 液氧煤油发动机 静态特性 系统仿真 推力调节方案 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]