Start-Up Transient Simulation of a Liquid Rocket Engine
Start-Up Transient Simulation of a Liquid Rocket Engine
复制标题
液体火箭发动机的启动瞬态仿真
DOI：
10.2514/6.2011-6032
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发表时间：
2011
期刊：
影响因子：
--
通讯作者：
M. Onofri
中科院分区：
文献类型：
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作者：
F. D. Matteo;M. D. Rosa;M. Onofri
在液体火箭发动机的启动过程中，发动机的大部分部件都需要在极端的工作条件下工作;该阶段的特征是非常复杂的现象，例如燃烧不稳定性，进料管线中的水锤效应，涡轮泵远离设计条件运行，当要进行发动机的设计研究或必须进行气门开启顺序的评估时，不能忽略的阶段OWS。由于这些原因，为了减少实验测试并增加发动机的安全性和可靠性，点火瞬态阶段的模拟变得必要。本工作的主题是开发一个液体火箭发动机瞬态模型，应用它来模拟启动瞬态和验证模型与现有的液体火箭发动机（RL-10）。采用了系统方法，因为有必要考虑发动机所有部件之间的所有相互作用。如果需要对发动机瞬态行为进行详细的估计，则这种选择是基本的。该程序模拟的系统包括从贮箱到涡轮泵子系统、阀门、管道、推力室入口、推力室本身的流管道和燃烧室内的化学反应的完整供给系统。发动机模型是建立使用ESPSS，与EcosimPro，一个面向对象的工具，能够模拟各种动态系统兼容的推进系统库。发动机模型还包括作者开发的原始模型和以前的工作，如一个新的喷射器板模型，和更现实的传热系数的相关性。普惠RL-10发动机的瞬态阶段已被视为验证案例。选择该发动机有几个原因，其中包括发动机结构数据、性能和试验结果在公开文献中的良好可用性。该发动机的主要子系统模型将被描述，并将其验证。然后，整个发动机的集成模型将被描述旁边的模拟与实验数据的比较。
During the start-up of a liquid rocket engine most of the engine components are required to work at extreme operating conditions; this phase features very complex phenomena such as combustion instabilities, water hammer e ects in feed lines, turbopumps operating far from design conditions and two-phase ows that cannot be neglected when design studies of an engine are to be performed or the assessment of the valve opening sequence has to be done. For these reasons simulations of the ignition transient phase become necessary in order to reduce the experimental tests and increase the engine safety and reliability. The subject of the present work is to develop an LRE transient model, to apply it to simulate the start-up transient and to validate the model with an existing liquid rocket engine (the RL-10). A system approach has been used, since it is necessary to take into account all the interactions between all the components of an engine. This choice is fundamental if a detailed estimation of the engine transient behaviour is the task. The system simulated by the code encompasses the complete feeding system from the tanks down to the the turbopump subsystems, the valves, the pipes, the thrust chamber’s inlets, the ow ducts of the thrust chamber itself and the chemical reactions inside the combustion chamber. The engine model is built using ESPSS, the propulsion system library compatible with EcosimPro, an object oriented tool capable of modelling various kinds of dynamic systems. The engine model includes also original models developed by the authors and presented in previous works such as a new injector plate model, and more realistic heat transfer coe cient correlations. The transient phase of the Pratt&Whitney RL-10 engine has been taken as validation case. This engine has been chosen for several reasons, among which the good availability of engine construction data, performance and tests results in open literature. The main subsystem models of this engine will be described and their validation will be presented. Then the integrated model of the entire engine will be described alongside the comparison of the simulation with experimental data.