• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>International journal of aerospace engineering >Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism
【24h】

Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism

机译：不带火焰保持机构的双涡流混合火箭发动机研究

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A 250 kgf thrust hybrid rocket engine was designed, tested, and verified in this work. Due to the injection and flow pattern of this engine, this engine was named dual-vortical-flow engine. This propulsion system uses N2O as oxidizer and HDPE as fuel. This engine was numerically investigated using a CFD tool that can handle reacting flow with finite-rate chemistry and coupled with the real-fluid model. The engine was further verified via a hot-fire test for 12 s. The ground I-sp of the engine was 232 s and 221 s for numerical and hot-fire tests, respectively. An oscillation frequency with an order of 100 Hz was observed in both numerical and hot-fire tests with less than 5% of pressure oscillation. Swirling pattern on the fuel surface was also observed in both numerical and hot-fire test, which proves that this swirling dual-vortical-flow engine works exactly as designed. The averaged regression rate of the fuel surface was found to be 0.6 similar to 0.8 mm/s at the surface of disk walls and 1.5 similar to 1.7 mm/s at the surface of central core of the fuel grain.
机译：在这项工作中，设计，测试并验证了250 kgf推力混合动力火箭发动机。由于该发动机的喷射和流动模式，该发动机被称为双涡流发动机。该推进系统使用N2O作为氧化剂，使用HDPE作为燃料。使用CFD工具对该发动机进行了数值研究，该工具可以处理具有有限速率化学反应的反应流，并与实际流体模型耦合。通过热火试验进一步验证了发动机12秒钟。发动机的地面I-sp分别用于数字和热火测试，分别为232 s和221 s。在数值和热火试验中都观察到100 Hz左右的振荡频率，压力振荡小于5％。在数值和热火试验中也观察到了燃料表面的涡流模式，这证明了这种涡旋双涡流发动机完全按设计工作。发现燃料表面的平均回归速率在盘壁表面处为0.6，类似于0.8mm / s，在燃料颗粒的中心核表面处为1.5，类似于1.7mm / s。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号