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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/20133

Title: Experimental assessment of vapour chamber heat spreader implementation in avionic cooling
Authors: Jones, Andy
Chen, Rui
Murray, Angus
Issue Date: 2015
Publisher: © American Institute of Aeronautics and Astronautics
Citation: JONES, A, CHEN, R. and MURRAY, A., 2015. Experimental assessment of vapour chamber heat spreader implementation in avionic cooling. Presented at: 53rd AIAA Aerospace Sciences Meeting, AIAA SciTech, Kissimmee, Florida, USA, AIAA 2015-071.
Abstract: Avionic thermal management is quickly becoming the limiting factor of aircraft performance and reliability, particularly prevalent with ageing airframes. While the increasing power density of avionic components requires a greater heat removal capacity for a given geometric module size, supplementary generation of cooling airflow is detrimental to engine and aircraft performance. This paper looks at improving the heat removal efficiency of forced convection cooled avionic modules by reducing the thermal resistance between the avionic component and module heat exchanger. The implementation of two-phase high thermal conductivity materials, such as Vapour Chamber Heat Spreaders (VCHS), embedded within the avionic module chassis act to improve heat exchanger isothermalisation, improving the effective heat transfer area. A bespoke test rig has been manufactured to experimentally compare a pure aluminium and embedded VCHS avionic chassis for heat removal capability. When considering a single circuit card, a direct mass flow rate reduction of between 22% and 65% is achieved with embedded VCHS over a pure aluminium chassis. Base plate isothermalisation is improved by 9%, generating a reduction in component temperature of 8% to 12%. As the number of heat sources increase, the performance improvements decrease. When testing with three circuit cards mass flow rate savings are reduced to between 14% and 26%. The concluding performance characteristic of the embedded VCHS avionic base plate is the insensitivity to the way thermal energy is coupled to it. Across all testing, the localised heat removal was never further than 3.5% from the averaged plate performance.
Description: This paper was accepted for publication by the AIAA and the definitive published version is available at http://dx.doi.org/10.2514/6.2015-0712
Sponsor: The project is co-funded by EPSRC (Engineering and Physical Sciences Research Council, UK) and BAE Systems.
Version: Accepted for publication
DOI: 10.2514/6.2015-0712
URI: https://dspace.lboro.ac.uk/2134/20133
Publisher Link: http://dx.doi.org/10.2514/6.2015-0712
Appears in Collections:Conference Papers and Presentations (Aeronautical and Automotive Engineering)

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