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Convective Heat Transfer Characterization of Aviation Turbine Fuel-Metal Oxide Nanofluids

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Field Value
 
Title Convective Heat Transfer Characterization of Aviation Turbine Fuel-Metal Oxide Nanofluids
 
Creator SONAWANE, S
BHANDARKAR, U
PURANIK, B
KUMAR, SS
 
Subject EFFECTIVE THERMAL-CONDUCTIVITY
CARBON NANOTUBES
AQUEOUS SUSPENSIONS
BROWNIAN-MOTION
ENHANCEMENT
PERFORMANCE
DEPENDENCE
COOLANT
 
Description A thorough experimental investigation of the thermophysical properties (thermal conductivity, viscosity, and specific heat), heat transfer performance, and pressure drop characteristics of aviation turbine fuel (ATF)-based Al2O3, TiO2, and CuO nanofluids was carried out for potential regenerative cooling application in semicryogenic rocket engines. The effects of volume concentration, size, and material of suspended particles, as well as the effect of the temperature of the nanofluid, were investigated. Although an enhanced thermal conductivity led to an increased heat transfer coefficient, the Prandtl number was seen to ha l e a bigger influence on the heat transfer characteristics. In particular, the correlation developed for the Nusselt number showed a much higher influence of the Prandfl number than for single-phase fluids. As a result, the ATF-CuO nanofluid performed the best amongst the three metal oxide nanofluids at a given particle size, concentration, and temperature. The enhancement is seen to improve with temperature, demonstrating the suitability of such a nanofluid at the conditions encountered during the regenerative cooling of the rocket engines (similar to 150 degrees C).
 
Publisher AMER INST AERONAUTICS ASTRONAUTICS
 
Date 2014-10-14T17:39:36Z
2014-10-14T17:39:36Z
2012
 
Type Article
 
Identifier JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER, 26(4)619-628
http://dx.doi.org/10.2514/1.T3893
http://dspace.library.iitb.ac.in/jspui/handle/100/14590
 
Language en