A swirl flow evaporative cold plate

Niggemann, R.E.; Greenlee, W. J.; Hill, David; Ellis, W. E.; Marshall, Paul F.

doi:10.2514/6.1985-920

Cited by 10 publications

(1 citation statement)

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“…This is a well-proven phenomenon that has been used to enhance boiling in high heat flux applications. The design and testing of several swirl flow evaporators is descibed Hill, (1985), Niggemann, (1985 and Sorensen, (1984).…”

Section: Swirl Flow Heat Exchangersmentioning

confidence: 99%

Two-Phase Thermal Management Systems for Space

Downing¹,

Andres²,

Nguyen³

et al. 2006

AIP Conference Proceedings

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Active two-phase thermal management systems have been shown to be weight and power effective for space platforms dissipating over 20 kWt of waste heat. A two-phase thermal management system can provide nearly isothermal heat transport at mass flows significantly lower than required for single-phase systems by employing a working fluid's latent heat rather than absorbing the heat sensibly in temperature change. Phase management issues specific to reduced gravity include pump cavitation, loop inventory control and potential dry out in the evaporator. Hamilton Sundstrand has developed and demonstrated in a reduced gravity aircraft environment, a suite of two-phase technologies that manage the liquid-vapor phase distribution. These technologies keep the liquid phase available at the pump inlet for pumping and present at heat acquisition boundaries for evaporation. This paper reviews these technologies for future high power, long duration space platforms.

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Section: Swirl Flow Heat Exchangersmentioning

confidence: 99%

Two-Phase Thermal Management Systems for Space

Downing¹,

Andres²,

Nguyen³

et al. 2006

AIP Conference Proceedings

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Advanced Two-phase Thermal Management In Spacecraft

Chang¹,

Hager²

Proceedings of the 25th Intersociety Energy Conversion Engineering Conference

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Advanced thermal control systems have been considered for spacecraft applications in the areas of heat acquisition, heat transport and heat rejection. A desirable system minimizes the temperature drop between the payload and the radiator to reduce the area and weight of the radiator. The heat pipe radiator/heat exchanger must be compact and lightweight. The heat exohanger musk be able to accommodate either mechanically pumped or capillary pumped two-phlase loops without serious operational constraints. A simple analysis shows that the amount of savings of the radiator area is a function of the heat flux applied to the payload. Nomenclature h, hi * interface heat transfer coefficient = overall heat transfer coefficient of cold plate, W/cm*-K between payload and cold plate, W/cma-K q" = heat flux, W/cmZ S = saving of radiator area, % To = cold plate condenser temperature ,K Tp = payload temperature, K Tr = radiator temperature, K T r r E = temperature of current radiator, K T,,, = temperature of new radiator, K T* =i sink temperature, K

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