Investigation on weight consideration of liquid coolant system for power electronics converter in future aircraft
Tong, Chin Fong
Date of Issue2016
School of Electrical and Electronic Engineering
Cooling systems significantly contribute to the total mass and volume of power electronic systems. In the case of aerospace application, it will directly increase the operating cost of the aircraft. This paper experimentally and numerically investigates the weight contribution of the liquid cooling system for power electronics converter in future aircraft. In order to investigate, a cooling system of 2 and 6 pass cold plates is designed and its cooling performance is analyzed. The weight and size contribution is discussed based on available coolants in the aircraft, flow rate ranges from 2 to 8 LPM and 1% to 3% power loss dissipation. Water is added and examined for completeness of the studies. This paper concludes that oil is inappropriate coolant for this particular case. The optimum parameters (Q = 8 LPM with 9.5 kg pump weight) for most promising coolant (fuel) that give high extraction rate with low weight contribution for the highest density cooling system are indicated.
Applied Thermal Engineering
© 2016 Elsevier Ltd. This is the author created version of a work that has been peer reviewed and accepted for publication by Applied Thermal Engineering, Elsevier Ltd. It incorporates referee’s comments but changes resulting from the publishing process, such as copyediting, structural formatting, may not be reflected in this document. The published version is available at: [http://dx.doi.org/10.1016/j.applthermaleng.2016.05.097].