Transpiration Cooling Systems

for Jet Engine Turbines and Hypersonic Flight

Transpiration Cooling Systems for Jet Engine Turbines and Hypersonic Flight2019-02-18T12:35:26+00:00

This programme takes a multi-disciplinary approach to make transpiration cooling recognised as the ultimate cooling technology, a reality in future UK design and manufactured jet engines and hypersonic vehicles. The research is primarily funded by an EPSRC programme grant (£6.14 million) with further funding from Rolls-Royce and other industrial partners (£1.2 million). This is a joint initiative between the University of Oxford, Imperial University, University of Southampton and the University of Birmingham bringing together a world-leading team of researchers to deliver the underpinning research to make transpiration cooling a reality.

Transpiration cooling is the introduction of a cool layer of fluid through a porous material between the component and the hot freestream flow, reducing the heat flux to the material. Ideally, the hot external gas is displaced from the surface by the introduction of the film which forms a low temperature buffer layer and also increases the overall boundary layer thickness, thus, reducing both the wall normal temperature and velocity gradients. Our approach will allow the coupling between the flow, thermal and stress fields to be researched both experimentally and numerically simultaneously in an interdisciplinary approach designed to arrive rapidly at the best transpiration cooling systems.

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