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Development of a liquid oxygen facility for rocket engine injector performance testing.

机译:开发用于火箭发动机喷油器性能测试的液氧设备。

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摘要

This study demonstrated the successful operation of a new liquid oxygen-gaseous methane rocket engine test facility to characterize the performance of a swirl coaxial injector. In support of safe system functional development, an oxygen compatibility and hazards assessment was completed to identify and minimize operational risks. Facility changes were implemented to create a more fault tolerant system. Major upgrades included initiatives to manage the oxygen risk and mitigate specific oxygen ignition mechanisms. Oxygen compatible materials and facility configuration changes were instituted to achieve safer experimentation. The demonstration testing of the cryogenic propellant system employed the swirl coaxial injector element in an ongoing program to study liquid oxygen-methane injectors. The injector performance was evaluated by experimental determination of combustion efficiency. The combustion efficiency determined for the injector arrangement during the single operational test was 80% with a 95% confidence systematic standard uncertainty estimate of 4%. Random uncertainty estimation must await repeated tests.
机译:这项研究证明了新型液态氧-气态甲烷火箭发动机测试设备的成功运行,以表征涡旋同轴喷油器的性能。为了支持安全的系统功能开发,完成了氧气相容性和危害评估,以识别并最大程度降低操作风险。实施了设施变更,以创建更具容错性的系统。重大升级包括管理氧气风险和减轻特定氧气着火机制的计划。建立了与氧气兼容的材料和设施配置更改,以实现更安全的实验。低温推进剂系统的示范测试在正在进行的程序中使用了涡旋同轴注射器元件来研究液氧-甲烷注射器。通过实验确定燃烧效率来评估喷射器性能。在单次运行测试期间确定的喷油嘴布置的燃烧效率为80%,置信度为95%的系统标准不确定度估计值为4%。随机不确定性估计必须等待重复测试。

著录项

  • 作者

    Mulkey, Henry W.;

  • 作者单位

    The University of Alabama in Huntsville.;

  • 授予单位 The University of Alabama in Huntsville.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 M.S.
  • 年度 2010
  • 页码 240 p.
  • 总页数 240
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 TS97-4;
  • 关键词

  • 入库时间 2022-08-17 11:37:28

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