Thesis-1970-Sturgess.pdf (11.79 MB)

Wall cooling by gaseous injection for a high-performance combustion system

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posted on 17.09.2018, 15:58 by Geoffrey J. Sturgess
The literature is reviewed and the effects of certain aerothermodynamic and geometric parameters on film effectiveness and local heat transfer coefficient are assessed. A difference in form and performance is recognised between the slots commonly used in research work end these used in practice. The developing film is modelled as a transition region preceding a potential core and followed by an asymptotic main region. For practical slots, it is shown that a transition region always exists in the film regardless of the injection velocity ratio; also, that the range of interest consists of the potential core end transition regions alone. A boundary layer theory for effectiveness is developed by taking account of the potential core and the jet-like nature of the real film. The resulting blowing group is tested against eleven very different practical geometry slots and excellent correlation of data is achieved. A universal equation is obtained for practical geometries of this general class. [Continues.]


Great Britain, Ministry of Aviation (agreement no.: PD/170/06/ADM).



  • Aeronautical, Automotive, Chemical and Materials Engineering


  • Aeronautical and Automotive Engineering


© Geoffrey John Sturgess

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This work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at:

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A Doctoral Thesis. Submitted in partial fulfilment of the requirements for the award of Doctor of Philosophy at Loughborough University.




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