Abstract
Aiming at the coupling problem between rotating detonation combustor and turbine components, this paper uses methane recuperation gas as fuel and adopts two-dimensional numerical simulation to study the working process after coupling between rotating detonation combustor and turbine stator blades. The results show that with the increase of methane conversion, the propagation mode changes from single wave mode to unstable single wave mode. Under the two modes, after the oblique shock wave sweep, the turbine stator blade outlet Mach number suddenly rises to 2.5. In addition, the flow field structure of a single turbine blade is also analyzed, and it is found that after oblique shock wave sweep, the flow field structure changes, and boundary layer separation occurs at the trailing edge of turbine stator blades. Turbine stator blades have a certain inhibition effect on the pressure oscillation at the combustion chamber outlet, and the disturbance generated by detonation wave extinguishing in unstable single-wave mode will be transmitted through turbine stator blades to the outlet. With the increase of fuel activity, turbine stator blade pressure loss gradually increases. The total pressure loss coefficient of single-wave mode is 9%, and the total pressure loss coefficient of unstable single-wave mode is 4%–6% higher than that of single-wave mode.
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