The invention relates to a rocket engine with the multi-stage combustion of a mixture of propellants, having at least one pre-combustion chamber and a main combustion chamber, a propellant mixture supply system to these chambers, including a fuel and oxida...

In one embodiment, a pulse detonation tube (10) includes a continuous base tube (12) having a substantially uniform wall thickness (56). The pulse detonation tube (10) also includes a local flexural wave modifying feature configured to locally vary a flexu...

The microcombustor (1) comprises an essentially tubular body (2) with a closed end (2a) close to which is defined a chamber (4) for supply and ignition of a fuel mixture, which communicates with a duct (8) within the body (2) having a length very much grea...

A pulse detonation system for a gas turbine includes a rotatable cylindrical member (42) having a forward surface (44), an aft surface (46), and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages (52)...

A shock wave reflector (10) includes a number of reflective units (1) positioned along a longitudinal direction (2) and separated by a gap G. Each reflective unit has a length L. The length L and the gap G are governed by a relationship L + G ≥ lambda . ...