Abstract: An annular combustion chamber of the continuous detonation wave type enabling a mixture of a fuel and an oxidizer injected in an axial direction F to be used to deliver continuous production of hot gas from detonation waves, the combustion chamber including electrodes powered by an electricity generator and between which NRP electric discharges are generated, the combustion chamber including at the upstream ends of its outer and inner walls, a plurality of electrode pairs angularly distributed in two concentric rings, the electrodes of a pair each belonging to a different ring and being in radial alignment, and the electricity generator being configured to power at least one electrode pair to generate at least one discharge zone, and to power sequentially each of the electrode pairs following to the electrode pair and enable a detonation wave to travel around the annular combustion chamber.

Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.

Abstract: An annular combustion chamber for a turbine engine, the chamber including an inner wall and an outer wall forming surfaces of revolution, the walls being connected together by a chamber end wall fitted with a fuel injection mechanism, each of the inner and outer walls including primary holes and dilution holes situated downstream from the primary holes in a gas flow direction, the primary and dilution holes being regularly distributed around the circumference of the inner and outer walls. The outer wall has a greater number of dilution holes than the inner wall.

Abstract: A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising: a first channel for passing a flow of an air/fuel pre-mixture towards the combustion chamber, the first channel opening out into the center of the injector nose via an outlet opening for the air/fuel pre-mixture; an electrical insulator surrounding said outlet opening for the air/fuel pre-mixture; a plasma generator system disposed inside said electrical insulation and downstream from said outlet opening for the air/fuel pre-mixture in order to control ignition and combustion of the air/fuel pre-mixture; a second channel for passing a flow of fuel towards the combustion chamber, the second channel opening out outside said electrical insulation; and a third channel for passing a flow of fuel towards the combustion chamber, this third channel opening out outside the second ch

Abstract: A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.

Abstract: A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.

Abstract: The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. The inner wall has a plurality of inner steps each extending radially towards the outside of the inner wall, the circumferential spacing between two adjacent inner steps defining an inner cavity. The outer wall includes a plurality of outer steps each extending radially towards the inside of the outer wall, the circumferential spacing between two adjacent inner steps defining an outer cavity. At least some of the inner and outer cavities are fed with air from outside the combustion chamber in a common direction that is circumferential, and with fuel in a direction that is radial.

Abstract: A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell (204) and an inner annular shell (206) secured inside the outer shell by means of a plurality of radial support arms (208); an annular combustion section housed inside the casing; and an annular turbine section.

Abstract: The invention relates to the field of turbomachines and concerns a combustion chamber (4) for which the dilution supply is optimised. The invention relates more particularly to optimisation of the position of the dilution holes (30a, 30b) present on the walls (7a, 7b) of the combustion chamber.

Abstract: The invention applies to the field of turbomachines and relates to a combustion chamber in which the supply of dilution air and cooling air is optimized. The invention is concerned more particularly with optimizing the position of the dilution holes present on the walls of the combustion chamber.

Abstract: A fuel injector for injecting fuel into a turbomachine combustion chamber, the injector presenting an injector nose for connection to an injection system fastened to the end wall of said combustion chamber, the injector nose comprising: a first channel for passing a flow of an air/fuel pre-mixture towards the combustion chamber, the first channel opening out into the center of the injector nose via an outlet opening for the air/fuel pre-mixture; an electrical insulator surrounding said outlet opening for the air/fuel pre-mixture; a plasma generator system disposed inside said electrical insulation and downstream from said outlet opening for the air/fuel pre-mixture in order to control ignition and combustion of the air/fuel pre-mixture; a second channel for passing a flow of fuel towards the combustion chamber, the second channel opening out outside said electrical insulation; and a third channel for passing a flow of fuel towards the combustion chamber, this third channel opening out outside the second ch

Abstract: The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel injection systems. The inner wall has a plurality of inner steps each extending radially towards the outside of the inner wall, the circumferential spacing between two adjacent inner steps defining an inner cavity. The outer wall includes a plurality of outer steps each extending radially towards the inside of the outer wall, the circumferential spacing between two adjacent inner steps defining an outer cavity. At least some of the inner and outer cavities are fed with air from outside the combustion chamber in a common direction that is circumferential, and with fuel in a direction that is radial.

Abstract: The invention relates to a turbomachine combustion chamber comprising an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems comprising pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.