Abstract
In this study, three-dimensional numerical studies have been performed to investigate the performance of a rotating detonation combustor with a diverging nozzle downstream. The effects of a diverging nozzle on the formation and propagation process of a detonation wave and typical flow field parameters in a rotating detonation combustor are mainly discussed. The results indicate that the diverging nozzle downstream is an important factor affecting the performance and design of a rotating detonation combustor. The diverging nozzle does not affect the formation and propagation process of the rotating detonation wave, while the time of two key wave collisions are delayed during the formation process of the detonation wave. With increases of the diverging angle, the rotating detonation combustor with the diverging nozzle can still maintain a certain pressure gain performance. Both the diverging nozzle and diverging angle have great influence on the flow field parameters of the rotating detonation combustor, including reducing the high pressure and temperature load, making the distribution of the outlet parameters uniform, and changing the local supersonic flow at the outlet. Among them, the outlet static pressure is reduced by up to 88.32%, and the outlet static temperature is reduced by up to 32.12%. This evidently improves the working environment of the combustor while reducing the thermodynamic and aerodynamic loads at the outlet. In particular, the diverging nozzle does not affect the supersonic characteristics of the outlet airflow, and on this basis, the Mach number becomes coincident and enhanced.
Highlights
The gas turbine is one of the power devices widely used in aerospace, marine, electricity generation, and other fields
The changing of rotating detonation combustor (RDC) flow field parameters under a under a diverging nozzle and different diverging angles are in studied diverging nozzle and different diverging angles are studied detail.in detail
The results indicate that the chemical reaction uniform and in RDCs with diverging nozzles
Summary
The gas turbine is one of the power devices widely used in aerospace, marine, electricity generation, and other fields. Tellefsen [17] investigated the operating performance of an RDC with an aerospike nozzle and turbine He indicated that outlet structure had no obvious impact on the propagation mode and speed of rotating detonation waves and pressure gain of the RDC. Peng et al [35] achieved the methane–air RDC experiment with only a 100 mm chamber diameter by controlling the contraction ratio of the outlet Laval nozzle This undoubtedly gives us more encouragement and valuable reference for the studies of methane–air RDCs. From the above brief review, it is concluded that the downstream nozzle is one of the main factors that should be considered during the design of the RDC, especially for methane–air RDCs. to the best of the authors’ knowledge, the present published investigations still cannot fully explain the following questions. The changing of RDC flow field parameters under a under a diverging nozzle and different diverging angles are in studied diverging nozzle and different diverging angles are studied detail.in detail
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