A wave rotor combustor includes an inlet plate, an outlet plate, and a rotor drum assembly positioned therebetween. The inlet plate is formed to include an inlet port arranged to receive a mixture of fuel and air. The outlet plate is formed to include an outlet port arranged to receive combusted gasses flowing out of the wave rotor combustor. The rotor drum assembly is arranged to rotate relative to the inlet and outlet plates and to combust the fuel and air mixture as part of a combustion process. Conditioned air is passed through the wave rotor combustor to regulate a temperature distribution of the wave rotor combustor.

The invention relates to a pulsed combustor assembly (A) for dehydration and/or granulation of a wet feedstock, in particular a viscous feedstock such as a feedstock containing natural fibers, sugars and/or vegetable starches, comprising a combustion chamber (16), at least one fuel supply line (23), at least one air supply line (26), and at least one pulsed air generator, wherein the pulsed air generator is connected to the air supply line (26) for generating at least a first pulsed air stream with a pulse frequency f1 entering the combustion chamber (16).

The invention relates to a pulsed combustor assembly (A) for dehydration and/or granulation of a wet feedstock, in particular a viscous feedstock such as a feedstock containing natural fibers, sugars and/or vegetable starches, comprising a combustion chamber (16), at least one fuel supply line (23), at least one air supply line (26), and at least one pulsed air generator, wherein the pulsed air generator is connected to the air supply line (26) for generating at least a first pulsed air stream with a pulse frequency f1 entering the combustion chamber (16).

The invention refers to an infrasound generator for enhancing the combustion of solid fuels burning in a combustion chamber. The infrasound is generated by one or more set(-s) of each two vibrating plates, vibrating in the same direction with the same displacement amplitude but in antiphase. The infrasound generator does not cause vibrations and is not sensitive to ash and heat from the combustion.

A cooking grate combining the cooking surface and the venting surface for a cooking appliance. The venting surface of the cooking grate may include one or more vanes. The vanes of the venting surface may direct air towards the cooking surface. The venting surface of the cooking grate may include a depending skirt defining a cavity therein. One or more cooking grates may be used in a variety of applications.

A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.

A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.

A pressure gain combustor comprises a detonation chamber, a pre-combustion chamber, an oxidant swirl generator, an expansion-deflection (E-D) nozzle, and an ignition source. The detonation chamber has an upstream intake end and a downstream discharge end, and is configured to allow a supersonic combustion event to propagate therethrough. The pre-combustion chamber has a downstream end in fluid communication with the detonation chamber intake end, an upstream end in communication with a fuel delivery pathway, and a circumferential perimeter between the upstream and downstream ends with an annular opening in communication with an annular oxidant delivery pathway. The oxidant swirl generator is located in the oxidant delivery pathway and comprises vanes configured to cause oxidant flowing past the vanes to flow tangentially into the pre-combustion chamber thereby creating a high swirl velocity zone around the annular opening and a low swirl velocity zone in a central portion of the pre-combustion chamber. The E-D nozzle is positioned in between the pre-combustion chamber and detonation chamber and provides a diffusive fluid pathway therebetween. The ignition source is in communication with the low swirl velocity zone of the pre-combustion chamber. This configuration is expected to provide a combustor with a relatively low total run-up DDT distance and time, thereby enabling high operating frequencies and corresponding high combustor performance.

A pressure gain combustor comprises a detonation chamber, a pre-combustion chamber, an oxidant swirl generator, an expansion-deflection (E-D) nozzle, and an ignition source. The detonation chamber has an upstream intake end and a downstream discharge end, and is configured to allow a supersonic combustion event to propagate therethrough. The pre-combustion chamber has a downstream end in fluid communication with the detonation chamber intake end, an upstream end in communication with a fuel delivery pathway, and a circumferential perimeter between the upstream and downstream ends with an annular opening in communication with an annular oxidant delivery pathway. The oxidant swirl generator is located in the oxidant delivery pathway and comprises vanes configured to cause oxidant flowing past the vanes to flow tangentially into the pre-combustion chamber thereby creating a high swirl velocity zone around the annular opening and a low swirl velocity zone in a central portion of the pre-combustion chamber. The E-D nozzle is positioned in between the pre-combustion chamber and detonation chamber and provides a diffusive fluid pathway therebetween. The ignition source is in communication with the low swirl velocity zone of the pre-combustion chamber. This configuration is expected to provide a combustor with a relatively low total run-up DDT distance and time, thereby enabling high operating frequencies and corresponding high combustor performance.

A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.