Characterisation of combustion and heat transfer using GOX/kerosene in a single-element rocket combustor

The Institute of Flight Propulsion at the Technische Universität München is operating a test facility to analyze different aspects of hydrocarbon combustion in a single-element rocket combustor. The research is done in cooperation with EADS Space Transportation, Ottobrunn. The test bed was designed to enable investigations of basic aspects concerning mixing and combustion of kerosene with gaseous oxygen in the preliminary stage of the development of a future reusable booster or expendable low cost engine. Main topics of research are the design and performance analysis of different injector elements and the effects of coking and sooting on heat transfer and cooling. Tests with different injector designs at several pressure levels and mixture ratios have been conducted. The data were analyzed with respect to combustion efficiency and heat transfer rate to a water cooled chamber wall. A comparison of tests with and without fuel film cooling promises great potential but also puts a number of questions to be answered.