The prediction of heat transfer characteristics in a regeneratively cooled rocket combustion chamber is one of the most important and most challenging tasks in the design work of a high performance rocket engine. This task becomes even more ambitious, when multipleuseand life capabilities ofseveral hours are requested for the engine.DASA, reyp. the design engineers of the former Boelkow rocket engine team were confronted with the problem from the very beginning of their staged combustion cycle demonstration program ( 1964-68 ), because this type of engine cycle, today well known to every rocket engineer, offers the potential of realizing chamher pressures up to 300 bar.Thisreport summarizesthe effortspentat DASAfrom thattimeup to now tocontinouslyimproveand validatethe heatflux prediction code by the information available from their combustion chamber development programs.The DASA heat transfer prediction code is now well suited for a straight forward design of hydrogedoxygen combustion chambers in thepressurerangefrom30to200harandth~stlevels from 50 to loo0 kN.However, new projects in the field of reuseable launchers and the general trend to most economic designs of space-transportation systems will require even more reliability in life prediction and therefore also further improvement of heat transfer prediction.
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