Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.

Abstract: A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess.

Abstract: A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess.

Abstract: An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the combustor tube being oriented transverse to a central axis of the engine.

Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.

Abstract: A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess.

Abstract: An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the combustor tube being oriented transverse to a central axis of the engine.

Abstract: The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12).