基于金属陶瓷堆芯1000 kN核热火箭发动机系统及组件参数研究

Thruster System and Component Parameters of a 1000 kN Nuclear Thermal Rocket Thruster Based on Ceramic-Metallic Reactor Core

针对大推力核热火箭发动机系统设计问题,开展了基于金属陶瓷(CERMET)堆芯1000 kN核热火箭发动机系统方案研究。通过对比闭式膨胀、开式膨胀和抽气三种循环方式的发动机系统性能,确定闭式膨胀循环为最佳系统循环方案;进行了反应堆堆芯、推力室、氢涡轮泵和再生冷却段的组件方案设计及数值仿真分析,得到反应堆氢出口温度2750 K,室压4.997 MPa,氢涡轮泵轴功43 MW,再生冷却段总温升和总流阻分别为190 K和3.3 MPa。最终获得比冲908 s的发动机系统参数。

To solve the system design problem of the nuclear thermal rocket engine with large thrust,a systematic study on the 1000 kN thrust Nuclear Thermal Rocket Engine based on a ceramic-metal-lic（CERMET） reactor core was carried out. A comparative study of three different system cycles in-cluding the closed expander cycle, the open expander cycle and the hot bleed cycle was carried out.The closed cycle was determined to be the best system cycle. In addition, the schematic design andthe numerical simulation of the reactor core, the thrust chamber, the hydrogen turbo-pump assemblyand the regeneration cooling section were analyzed. The simulation results showed that the reactoroutlet temperature was 2750 K, the chamber pressure was 4. 997 MPa, the shaft work of turbopumpwas 43 MW, while the total temperature rise and the total flow resistance of the regenerative coolingsection were 190 K and 3. 3 MPa respectively. In the end, the engine system parameters with specif-ic impulse of 908 s were obtained.