US Patent 8341932 Rotary air valve firing patterns for resonance detuning

An engine contains a compressor stage, a plurality of pulse detonation combustors and a rotary inlet valve structure having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage. Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer.