The objective of this thesis was to investigate the cooling performance of a 16-nozzle spray array, using FC-72 as the working fluid, in variable gravity conditions with additional emphasis on fluid management and flow stability. A flight test experiment was modified to accommodate a 16- nozzle spray array, which was then tested in the parabolic flight trajectory environment of NASA's C-9 reduced gravity aircraft. The 16-nozzle array was designed to cool a (25.4 by 25.4 mm) area on a thick film resistive heater used to simulate electronic components. Data was taken and reduced as a result of flight tests conducted over the course of two flight weeks (each week consisting of four flights, each flight consisting of 40 to 60 parabolas). The flight tests were conducted in order to examine gravity effects on spray cooling performance and to evaluate a novel liquid-vapor separator design. The mass flow rate through the 16-nozzle spray array ranged from 13.1.
Effect of Variable Gravity on the Cooling Performance of a 16- Nozzle Spray Array
2008
261 pages
Report
Keine Angabe
Englisch
Architectural Design & Environmental Engineering , Physics , Cooling , Gravity , Electronic equipment , Heat transfer , Flow rate , Temperature control , Calibration , Qualitative analysis , Heat flux , Fluid control , Mass flow , Theses , Arrays , Separators , Flight testing , Spray cooling , Nozzle spray arrays , Liquid vapor separators , Microgravity , Two phase cooling , Experimental setup , Heat conduction model , Heater losses , Nondimensionalization , Thermal management , Thick film resistors , Uncertainty analysis
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