Abstract: A fuel preconditioning system for use with a pulse detonation combustor (PDC) makes use of a heat source to pyrolyze fuel prior to injecting it into the PDC for detonation. The fuel is decomposed into a more detonable form by pyrolysis in a conditioner that applies heat to the fuel in the absence of oxidizer. The heat may be provided by a hot section of the engine, including the walls of the PDC itself. The conditioned fuel is fed to the PDC and detonated.

Abstract: A gas cooking system having a gas cooking burner that includes a gas line, a first gas port coupled to the gas line, and a second gas port disposed downstream from the first gas port, wherein at least one of the first and second gas ports comprises a non-circular geometry adapted to increase air entrainment, the second gas port further being non-rectangular if the first gas port has a circular geometry.

Abstract: A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.

Abstract: A power system includes a fuel preconditioner adapted to convert a fuel to at least one conditioned fuel, a pulse detonation combustor, and a turbine. The pulse detonation combustor is adapted to receive the conditioned fuel and a primary oxidizer and to detonate a mixture including the conditioned fuel and the primary oxidizer and exhaust a number of detonation products. The turbine is positioned downstream from and in flow communication with the pulse detonation combustor. A power plant includes at least one fuel preconditioner and a number of power systems. Each power system includes a pulse detonation combustor and a turbine positioned downstream from and in flow communication with the pulse detonation combustor.