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根据航宇局路易斯研究中心的合同,先进空间发动机的主要组件和分系统正在进行技术研制和验证。这个发动机是为诸如载人轨道转移飞行器使用的高性能重复使用长寿命的先进发动机奠定技术基础。本文阐述了20,000磅推力的液氢/液氧先进空间发动机的技术研制和技术验证的情况。发动机是采用燃烧室压力为2,000磅/吋~2(绝对)的分级燃烧循环以及面积膨胀比为400:1的喷管,以使其性能最佳。发动机主要组件的试验已经结束,本文将给出这些试验结果。这些试验包括涡轮泵组合件试验和燃烧室系统组合件试验。最近,装有400:1喷管延伸段的全燃烧室系统的试验结果表明,实测发动机比推力为478秒。组合件的验证工作正在继续进行,系统的技术研制和验证的计划也正在进行,本文将予以讨论。
Under the contract of the NASA Lewis Research Center, major components and subsystems of advanced space engines are being developed and validated. This engine lays the foundation for the high-performance, reusable, long-life advanced engines used in manned orbiting vehicles. This article describes the technical development and technical validation of a 20,000 lb. thrust liquid hydrogen / liquid oxygen advanced space engine. The engine uses a staged combustion cycle with a combustor pressure of 2,000 psi (absolute) and a nozzle with an area expansion ratio of 400: 1 to optimize performance. The tests of the main engine components have been completed and the results of these tests are given in this paper. These tests include turbo-pump assembly testing and combustor system assembly testing. Recently, the test results for an all-combustion system equipped with a 400: 1 nozzle extension showed that the measured engine specific thrust was 478 seconds. Verification of the assembly is continuing, and the system’s technical development and validation plans are underway, as discussed in this article.