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当前航天飞机主发动机第一阶段发动机已经验证在高达104％额定功率下具有极好的飞行性能。早期在109％额定功率下作的鉴定试验表明,高压涡轮泵的工作寿命受到一定限制。第二阶段发动机研制计划自1983年以来一直在进行着,旨在提高工作寿命并提供附加余量。本文中介绍了航天飞机主发动机第一阶段发动机的研制历史和第二阶段发动机的设计和结果,以及高压涡轮泵工作寿命极限及其需大量维护的关键部件的验证情况,并概述了第二阶段发动机的设计改进、基本分析和试验结果。此外,在本文中还讨论了正式的鉴定试验计划。高压燃料涡轮泵已作了改进,以便减低涡轮工作温度,延长一、二级涡轮叶片的工作寿命并减小金属板维护工作量。高压氧化剂涡轮泵也作了改进,以便改进轴承工作寿命并消除次同步旋转问題。对于这些改进以及为了快速评估其优点而设计和使用的专用仪表都作了详细讨论。
The current phase one engine of the main shuttle of the space shuttle has been proven to have excellent flight performance at up to 104% of rated power. Early identification test at 109% of rated power shows that the working life of high-pressure turbopump is limited. The second phase of the engine development program has been under way since 1983 with the aim of increasing working life and providing additional allowances. In this paper, the development history of the first phase of the main engines of the space shuttle and the design and results of the second phase of the engines are introduced. The working life limits of the high-pressure turbopumps and the verification of the key components that need a large amount of maintenance are also introduced. The second phase Engine design improvements, basic analysis and test results. In addition, an official qualification test plan is discussed in this article. High-pressure fuel turbopumps have been improved to reduce turbine operating temperatures, extend the working life of primary and secondary turbine blades and reduce metal plate maintenance. High-pressure oxidant turbo pumps have also been refined to improve bearing operating life and eliminate sub-synchronous rotation problems. Specialized instruments designed and used for these improvements and for the quick assessment of their advantages are discussed in detail.