火箭推进

针对核热火箭发动机系统方案展开深入研究,提出了3种液体火箭发动机系统循环选型和3种系统流路设计方案。以高比冲和经济性为优化目标进行系统热力循环选型和系统参数优化设计,最终选择了一种基于带驱动元件金属陶瓷(CERMET)快堆的闭式膨胀循环高性能系统方案。采用遗传算法进行该优化方案下系统参数最优化分析,结合工程实际最终得到室压5 MPa,涡轮前温度400 K,比冲大于900 s的优化设计系统方案,并对相关组合件理论特性进行分析,提出未来组件优化方向,为后续核热火箭发动机设计提供基础。

Based on the further research of nuclear thermal rocket engine system, three types of thermal cycle selection and flow path design of liquid rocket engines have been proposed. Aiming to obtain the high specific impulse and economy, a closed-expansion-cycle based on CERMET with a driver was finally selected. The genetic optimization algorithm was adopted to optimize the engine system. Combined with the engineering practice, the final scheme is obtained with a chamber pressure of 5 MPa, a turbine inlet temperature of 400 K and a specific impulse greater than 900 s. In addition, the theoretical characteristics of related components are analyzed and the future component optimization direction is proposed, which provides the basis for the subsequent design of nuclear thermal rocket engine.

引言
1 系统热力循环方案选择
2 系统参数选取及优化设计方法研究
3 组合件性能特性分析
4 结论与展望

图1 美国“涅尔瓦”(NERVA)核热推进发动机<br/>Fig.1 “NERVA”nuclear thermal rocket engine in the United States

图1 美国“涅尔瓦”(NERVA)核热推进发动机
Fig.1 “NERVA”nuclear thermal rocket engine in the United States

图2 SNTP核热推进发动机系统<br/>Fig.2 System of “SNTP” engine

图2 SNTP核热推进发动机系统
Fig.2 System of “SNTP” engine

图3 RD-0140原理样机<br/>Fig.3 Prototype of RD-0140

图3 RD-0140原理样机
Fig.3 Prototype of RD-0140

图4 适用于核热火箭发动机的3种系统循环方式<br/>Fig.4 Three thermodynamic cycles for nuclear thermal rocket engines

图4 适用于核热火箭发动机的3种系统循环方式
Fig.4 Three thermodynamic cycles for nuclear thermal rocket engines

表1 3种循环方式系统及参数特点[19-20]<br/>Tab.1 Characteristics of three types of thermodynamic cycles[19-20]

表1 3种循环方式系统及参数特点[19-20]
Tab.1 Characteristics of three types of thermodynamic cycles[19-20]

图5 典型CERMET堆芯与带驱动元件CERMET堆芯<br/>Fig.5 Typical CERMET rectors cores with and without drivers

图5 典型CERMET堆芯与带驱动元件CERMET堆芯
Fig.5 Typical CERMET rectors cores with and without drivers

图6 3种流路设计方案<br/>Fig.6 Design scheme of three kinds of flow path

图6 3种流路设计方案
Fig.6 Design scheme of three kinds of flow path

表2 3种不同流路设计的闭式膨胀循环系统方案参数<br/>Tab.2 Scheme parameters of three types of closed-expansion-cycle system with different fluid path design

表2 3种不同流路设计的闭式膨胀循环系统方案参数
Tab.2 Scheme parameters of three types of closed-expansion-cycle system with different fluid path design

图7 最终系统方案
Fig.7 Final system scheme

图8 基于遗传算法的核热火箭发动机系统参数优化流程<br/>Fig.8 Parametric optimization flow of nuclear thermal rocket engine based on genetic algorithm(GA)

图8 基于遗传算法的核热火箭发动机系统参数优化流程
Fig.8 Parametric optimization flow of nuclear thermal rocket engine based on genetic algorithm(GA)

表3 系统优化算法结果<br/>Tab.3 Results of system optimization

表3 系统优化算法结果
Tab.3 Results of system optimization

图9 室压、室温和喷管面积比对比冲的影响<br/>Fig.9 Influence of chamber pressure, chamber temperature and nozzle area ratio on specific impulse

图9 室压、室温和喷管面积比对比冲的影响
Fig.9 Influence of chamber pressure, chamber temperature and nozzle area ratio on specific impulse

图10 涡轮入口温度对涡轮泵的影响<br/>Fig.10 Influence of turbine inlet temperature on turbo pump

图10 涡轮入口温度对涡轮泵的影响
Fig.10 Influence of turbine inlet temperature on turbo pump

图11 涡轮泵效率对涡轮泵性能影响分析<br/>Fig.11 Influence analysis of turbo efficiency on turbo performance

图11 涡轮泵效率对涡轮泵性能影响分析
Fig.11 Influence analysis of turbo efficiency on turbo performance

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备注

引言

1 系统热力循环方案选择

2 系统参数选取及优化设计方法研究

3 组合件性能特性分析

4 结论与展望

期刊信息