The paper summarizes research that was conducted last year as part of the project of “Turbine engine with
detonation combustion chamber”. In this project, throughout 2012 and early 2013, tests were carried out on a test
stand connected to the compressed air system. Research, of the rotating detonation phenomena, was carried out for
a number of detonation chambers with different interior channel geometry. In addition, for each geometry configuration,
tests were carried out for different levels of choking of the chamber outlet and hence for different pressures conditions
inside the detonation chamber. This article presents the results of tests carried out for gaseous (hydrogen), hybrid
(hydrogen + kerosene) and liquid (Jet-A) fuels, using different types of fuel injectors and for different fuel injection
configuration settings (inside the chamber, or in front of the chamber). During these tests, parameters such as
pressure behind the detonation wave (using piezoelectric sensors), the static pressure in front of and inside the
detonation chamber and temperature: before, inside and at the outlet of the chamber, were measured. Research was
performed for the various mass flow rates of air and fuel injected into the chamber that means for the different air-fuel
equivalence ratios (Lambda). The main achievement of this study was to obtain a stable and reproducible rotating
detonation of air and heated kerosene (Jet-A) mixture, thus the results presented in this paper presents mainly these
tests as the most interesting to the reader
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