In the present study, an innovative annular aeroengine combustor concept is investigated. The main feature of this combustor is the staggered arrangement of the burners, which implies a helical flow pattern in the flame tube. Such a flow structure with high exit flow angle can be adopted to reduce the axial length of the combustor as well as the number of the up- and downstream vanes. In consequence, the overall performance and efficiency of such an engine can be improved due to several aerothermal and structural advantages.
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