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CECE: Expanding the Envelope of Deep Throttling in Liquid Oxygen/Liquid Hydrogen Rocket Engines For NASA Exploration Missions

机译：CECE：为NASA探索任务扩大液氧/液氢火箭发动机的深度节流范围

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摘要

As one of the first technology development programs awarded by NASA under the Vision for Space Exploration, the Pratt & Whitney Rocketdyne (PWR) Deep Throttling, Common Extensible Cryogenic Engine (CECE) program was selected by NASA in November 2004 to begin technology development and demonstration toward a deep throttling, cryogenic engine supporting ongoing trade studies for NASA s Lunar Lander descent stage. The CECE program leverages the maturity and previous investment of a flight-proven hydrogen/oxygen expander cycle engine, the PWR RL10, to develop technology and demonstrate an unprecedented combination of reliability, safety, durability, throttlability, and restart capabilities in a high-energy cryogenic engine. The testbed selected for the deep throttling demonstration phases of this program was a minimally modified RL10 engine, allowing for maximum current production engine commonality and extensibility with minimum program cost. Three series of demonstrator engine tests, the first in April-May 2006, the second in March-April 2007 and the third in November-December 2008, have demonstrated up to 13:1 throttling (104% to 8% thrust range) of the hydrogen/oxygen expander cycle engine. The first two test series explored a propellant feed system instability ("chug") environment at low throttled power levels. Lessons learned from these two tests were successfully applied to the third test series, resulting in stable operation throughout the 13:1 throttling range. The first three tests have provided an early demonstration of an enabling cryogenic propulsion concept, accumulating over 5,000 seconds of hot fire time over 27 hot fire tests, and have provided invaluable system-level technology data toward design and development risk mitigation for the NASA Altair and future lander propulsion system applications. This paper describes the results obtained from the highly successful third test series as well as the test objectives and early results obtained from a fourth test series conducted over March-May 2010
机译：作为NASA根据太空探索远景授予的首批技术开发计划之一，普惠公司的Rocketdyne（PWR）深度节流通用可扩展低温发动机（CECE）计划于2004年11月被NASA选中，以开始技术开发和演示转向节流能力更强的低温发动机，为NASA的Lunar Lander下降阶段正在进行的贸易研究提供支持。 CECE计划利用经过飞行验证的氢气/氧气膨胀机循环发动机PWR RL10的成熟度和先前的投资来开发技术，并在高能中展示出前所未有的可靠性，安全性，耐用性，节流性和重启能力的结合低温发动机。为该程序的节流演示阶段选择的试验台是最小修改的RL10发动机，从而以最小的程序成本实现了最大的当前生产发动机通用性和可扩展性。在2006年4月至5月的第三个演示发动机试验系列，在2007年3月至2007年4月的第二个演示发动机试验以及在2008年11月至12月的第三次演示发动机试验中，发动机的节流率高达13：1（推力范围为104％至8％）。氢气/氧气膨胀机循环发动机。前两个测试系列探索了在低节流功率水平下推进剂进料系统不稳定（“突突”）环境。从这两个测试中学到的经验教训已成功应用于第三测试系列，从而在整个13：1节流范围内实现了稳定的运行。前三项测试提供了启用低温推进概念的早期演示，在27项热火测试中累积了超过5,000秒钟的热火时间，并为NASA Altair和SLA的设计和开发风险缓解提供了宝贵的系统级技术数据。未来着陆器推进系统的应用。本文介绍了从非常成功的第三个测试系列获得的结果，以及从2010年3月至5月进行的第四个测试系列获得的测试目标和早期结果

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