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Spray cooling heat transfer: Technology overview and assessment of future challenges for micro-gravity application

机译：喷雾冷却传热：技术概述和对微重力应用未来挑战的评估

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摘要

Advanced on-board flight systems for future NASA space exploration programs consist of components such as laser-diode arrays (LDA's) and multi-chip modules (MCM's). Thermal management of these systems require high heat flux cooling capability (≥100W/ cm~2), tight temperature control (approx. ±2℃), reliable start-up (on demand) and long term stability. Traditional multiphase thermal control technologies for space flight (e.g., loop heat pipes, capillary pumped loops, etc.) satisfy the temperature control, start-up and sta-bility requirements, but their heat flux removal capabilities are limited. Spray cooling can provide high heat fluxes in excess of 100 W/cm~2 using fluorinerts and over 1000 W/cm2 with water while allowing tight temperature control at low coolant fluid flow rates. Spray cooling has been flight proven in an open loop configuration through the Space shuttle's flash evaporator system (FES). However, several closed system issues require investigation to further advance the technology to a technology readiness level (TRL) appropriate for closed system space flight application. This paper provides a discussion of the current status of spray cooling technology as well as NASA's goals, current direction, and challenges associated with the implementation and practice of this technology in the micro-gravity environment.
机译：用于未来NASA太空探索计划的高级机载飞行系统由激光二极管阵列（LDA）和多芯片模块（MCM）等组件组成。这些系统的热管理要求高的热通量冷却能力（≥100W/ cm〜2），严格的温度控制（约±2℃），可靠的启动（按需）和长期稳定性。用于太空飞行的传统多相热控制技术（例如回路热管，毛细管泵回路等）满足温度控制，启动和稳定性要求，但其热通量去除能力受到限制。喷雾冷却可以使用氟提供超过100 W / cm〜2的高热通量，用水提供超过1000 W / cm2的高热通量，同时可以在低冷却液流量下严格控制温度。喷雾冷却已通过航天飞机的闪蒸器系统（FES）在开环配置中进行了飞行验证。但是，一些封闭系统问题需要进行调查，以进一步将该技术推进到适合封闭系统太空飞行应用的技术准备水平（TRL）。本文讨论了喷雾冷却技术的现状以及NASA的目标，当前方向以及在微重力环境中与该技术的实施和实践相关的挑战。

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