Internally drained condenser for spacecraft thermal managementThis paper presents the results obtained to date in a program to develop a high heat flux condenser for use in two-phase spacecraft thermal management loops. The objective is to obtain a several fold increase in condensation heat transfer coefficient over those which can be achieved with shear-controlled or capillary-wick condensers. The internally drained condenser relies on shaped fins to develop a capillary pressure gradient over the surface of the fins and drive the condensate toward narrow drainage grooves separating the fins. The condensate then flows through a drainage network embedded in the condenser walls. Heat transfer coefficients of up to 8 W/sq cm C were measured in steam, providing a heat transfer enhancement ratio greater than a factor of 8. In the paper the proof-of-concept experiments are described and simplified models to predict the performance of the internally drained condenser are presented.
Document ID
19890055869
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Valenzuela, Javier A. (Creare, Inc. Hanover, NH, United States)
Drew, Brian C. (Creare, Inc. Hanover, NH, United States)