In one embodiment, a power generation system includes a pulse detonation engine including a combustion chamber, a linear power generator including a working chamber, and a nozzle positioned between the combustion chamber and the working chamber that expands exhaust gas expelled from the combustion chamber, wherein the nozzle increases thermodynamic efficiency of the system.

In one embodiment, a power generation system includes a pulse detonation engine including a combustion chamber, a linear power generator including a working chamber, and a nozzle positioned between the combustion chamber and the working chamber that expands exhaust gas expelled from the combustion chamber, wherein the nozzle increases thermodynamic efficiency of the system.

A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.

A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.

The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an axis, each chamber (12A, 12B, 12C) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18); and an ignition means that triggers combustion in the combustion chambers (12A, 12B, 12C). The module (10) comprises at least one duct (80) which establishes a communication between a first combustion chamber (12A) and at least one second combustion chamber (12B) in order to inject burnt gases from the first combustion chamber (12A) into the second combustion chamber (12B) so as to trigger combustion in the second combustion chamber (12B).

The invention relates to a turbine engine combustion module (10), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers (12A, 12B) arranged about an axis, each chamber (12A, 12B, 12C) comprising a compressed gas intake port (16) and a burnt gas exhaust port (18); and an ignition means that triggers combustion in the combustion chambers (12A, 12B, 12C). The module (10) comprises at least one duct (80) which establishes a communication between a first combustion chamber (12A) and at least one second combustion chamber (12B) in order to inject burnt gases from the first combustion chamber (12A) into the second combustion chamber (12B) so as to trigger combustion in the second combustion chamber (12B).

A compressor and method are provided, the compressor having elliptically-shaped combustion chambers including a first chamber having a first inlet and a first outlet, and a last chamber having an inlet and outlet. The first inlet is in communication with a low pressure plenum, the first outlet is in communication with the inlet of the last chamber, and the outlet of the last chamber is in communication with a high pressure plenum to define a flow pathway. A volume of gas is introduced into the first chamber at a first pressure. A fuel is injected into the first chamber, alternately at the foci, and ignited to advance the volume of gas along the flow pathway. A fuel is injected into the last chamber, alternately at the foci, and ignited on a schedule synchronized with ignition in the first chamber to further advance the volume of gas along the flow pathway.

A compressor and method are provided, the compressor having elliptically-shaped combustion chambers including a first chamber having a first inlet and a first outlet, and a last chamber having an inlet and outlet. The first inlet is in communication with a low pressure plenum, the first outlet is in communication with the inlet of the last chamber, and the outlet of the last chamber is in communication with a high pressure plenum to define a flow pathway. A volume of gas is introduced into the first chamber at a first pressure. A fuel is injected into the first chamber, alternately at the foci, and ignited to advance the volume of gas along the flow pathway. A fuel is injected into the last chamber, alternately at the foci, and ignited on a schedule synchronized with ignition in the first chamber to further advance the volume of gas along the flow pathway.

A constant-volume combustion system for a turbomachine includes a plurality of combustion chambers distributed in an annular manner about an axis defining an axial direction, each combustion chamber including an intake port and an exhaust port; a selective closure member rotationally movable about the axis with respect to the combustion chambers, the selective closure member including a ferrule facing the intake and exhaust ports of the combustion chambers, the ferrule containing at least one intake aperture intended to cooperate with the exhaust port of each chamber and at least one exhaust aperture intended to cooperate with the exhaust port of each chamber. Each intake aperture and each exhaust aperture are segmented by at least one segment extending in each aperture in the axial direction.

A constant-volume combustion system for a turbomachine includes a plurality of combustion chambers distributed in an annular manner about an axis defining an axial direction, each combustion chamber including an intake port and an exhaust port; a selective closure member rotationally movable about the axis with respect to the combustion chambers, the selective closure member including a ferrule facing the intake and exhaust ports of the combustion chambers, the ferrule containing at least one intake aperture intended to cooperate with the exhaust port of each chamber and at least one exhaust aperture intended to cooperate with the exhaust port of each chamber. Each intake aperture and each exhaust aperture are segmented by at least one segment extending in each aperture in the axial direction.